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2 | CN117345752 | B | 2024-05-14 | 一種航空航太用輕量化自鎖螺母、冷擠壓模具及成型方法 | invention | CN202311403191.1 | 2023-10-26 | 本發明公開了一種航空航太用輕量化自鎖螺母、冷擠壓模具及成型方法，屬於螺母加工技術領域。自鎖螺母包括螺母本體，螺母本體包括扳擰段及法蘭段，法蘭段上設有多個減重斜面結構及法蘭錐面結構，法蘭錐面結構設置在減重斜面結構之間，減重斜面結構上設有減重窩結構。冷擠壓模具包括上模機構、下模機構及聯動機構，下模機構包括陰模，陰模內設有型腔，型腔內自上而下依次設有圓柱腔段、法蘭腔段、扳擰定徑帶腔段及扳擰腔段，法蘭腔段設有斜面結構及錐面結構，斜面結構上設有凸球。本發明自鎖螺母冷擠壓使得自鎖螺母的金屬纖維連續流暢流動及材料冷變形冷作硬化特性，使其基體組織緊密且強度大幅提升，使得該自鎖螺母同時具備減重且高承載特性。; | 1.一種航空航太用輕量化自鎖螺母冷擠壓成型方法，採用航空航太用輕量化自鎖螺母冷擠壓模具，所述航空航太用輕量化自鎖螺母冷擠壓模具包括上模機構、下模機構及聯動機構，所述航空航太用輕量化自鎖螺母包括螺母本體，所述螺母本體內設有螺孔，所述螺母本體包括扳擰段及法蘭段，所述扳擰段的外表面設有扳擰結構（101），所述法蘭段的外表面上設有多個減重斜面結構（102）及多個法蘭錐面結構（104），所述法蘭錐面結構（104）設置在相鄰的所述減重斜面結構（102）之間，每個所述減重斜面結構（102）上設有減重窩結構（103）；其特徵在於，所述上模機構包括上範本（2）、設置在上範本（2）上的上模套（3）及通過定位機構設置在所述上模套（3）上的沖頭（4）；所述下模機構包括下範本（6）、設置在下範本（6）上的下模座（7）、設置在下模座（7）上的陰模（8），所述陰模（8）內設有型腔，所述型腔內自上而下依次設有圓柱腔段（801）、法蘭腔段（802）、扳擰定徑帶腔段（803）及扳擰腔段（804），所述法蘭腔段（802）的內壁上設有多個斜面結構（8021）及錐面結構（8023），相鄰的所述斜面結構（8021）之間設有所述錐面結構（8023），所述斜面結構（8021）上設有凸球（8022），所述扳擰定徑帶腔段（803）的尺寸小於所述扳擰腔段（804）的尺寸，所述扳擰定徑帶腔段（803）及扳擰腔段（804）的形狀與所述扳擰結構（101）的形狀相適配；所述凸球（8022）活動式設置在所述陰模（8）內，所述陰模（8）的內壁上設有用於定位所述凸球（8022）的球定位槽；所述聯動機構包括頂杆、退料杆（11）、退料板（12）及一對拉杆，所述頂杆的上部伸入所述型腔內，且其上部的形狀與所述扳擰定徑帶腔段（803）的形狀相適配，所述頂杆的下部設有頂杆限位件（100），所述下範本（6）或下模座（7）上設有頂杆限位台肩，所述退料杆（11）設於所述頂杆的下方，所述退料板（12）設於所述退料杆（11）的下方，所述退料板（12）與所述拉杆的下部連接，所述拉杆的上部穿過所述下範本（6）、上範本（2）且其上端設有拉杆限位件（130），所述上範本（2）上設有拉杆限位台肩；成型步驟如下：1）準備坯料（24），坯料（24）呈圓柱形，圓柱形坯料（24）的外徑與自鎖螺母（1）法蘭段的外徑一致；2）將坯料（24）放入型腔內；3）壓力機動作，帶動上模機構下行，沖頭（4）伸入型腔與坯料（24）接觸，在壓力作用下坯料（24）在陰模（8）內下移，坯料（24）在沖頭（4）及頂杆作用下冷擠壓成型；4）壓力機回程，帶動拉杆向上運動，通過退料板（12）、退料杆（11）及頂杆聯動將向上的推出力傳遞給成型零件，將成型零件推出完成退料；5）等待下一個坯料（24）。 | 1.一種航空航太用輕量化自鎖螺母冷擠壓成型方法，採用航空航太用輕量化自鎖螺母冷擠壓模具，所述航空航太用輕量化自鎖螺母冷擠壓模具包括上模機構、下模機構及聯動機構，所述航空航太用輕量化自鎖螺母包括螺母本體，所述螺母本體內設有螺孔，所述螺母本體包括扳擰段及法蘭段，所述扳擰段的外表面設有扳擰結構（101），所述法蘭段的外表面上設有多個減重斜面結構（102）及多個法蘭錐面結構（104），所述法蘭錐面結構（104）設置在相鄰的所述減重斜面結構（102）之間，每個所述減重斜面結構（102）上設有減重窩結構（103）；其特徵在於，所述上模機構包括上範本（2）、設置在上範本（2）上的上模套（3）及通過定位機構設置在所述上模套（3）上的沖頭（4）；所述下模機構包括下範本（6）、設置在下範本（6）上的下模座（7）、設置在下模座（7）上的陰模（8），所述陰模（8）內設有型腔，所述型腔內自上而下依次設有圓柱腔段（801）、法蘭腔段（802）、扳擰定徑帶腔段（803）及扳擰腔段（804），所述法蘭腔段（802）的內壁上設有多個斜面結構（8021）及錐面結構（8023），相鄰的所述斜面結構（8021）之間設有所述錐面結構（8023），所述斜面結構（8021）上設有凸球（8022），所述扳擰定徑帶腔段（803）的尺寸小於所述扳擰腔段（804）的尺寸，所述扳擰定徑帶腔段（803）及扳擰腔段（804）的形狀與所述扳擰結構（101）的形狀相適配；所述凸球（8022）活動式設置在所述陰模（8）內，所述陰模（8）的內壁上設有用於定位所述凸球（8022）的球定位槽；所述聯動機構包括頂杆、退料杆（11）、退料板（12）及一對拉杆，所述頂杆的上部伸入所述型腔內，且其上部的形狀與所述扳擰定徑帶腔段（803）的形狀相適配，所述頂杆的下部設有頂杆限位件（100），所述下範本（6）或下模座（7）上設有頂杆限位台肩，所述退料杆（11）設於所述頂杆的下方，所述退料板（12）設於所述退料杆（11）的下方，所述退料板（12）與所述拉杆的下部連接，所述拉杆的上部穿過所述下範本（6）、上範本（2）且其上端設有拉杆限位件（130），所述上範本（2）上設有拉杆限位台肩；成型步驟如下：1）準備坯料（24），坯料（24）呈圓柱形，圓柱形坯料（24）的外徑與自鎖螺母（1）法蘭段的外徑一致；2）將坯料（24）放入型腔內；3）壓力機動作，帶動上模機構下行，沖頭（4）伸入型腔與坯料（24）接觸，在壓力作用下坯料（24）在陰模（8）內下移，坯料（24）在沖頭（4）及頂杆作用下冷擠壓成型；4）壓力機回程，帶動拉杆向上運動，通過退料板（12）、退料杆（11）及頂杆聯動將向上的推出力傳遞給成型零件，將成型零件推出完成退料；5）等待下一個坯料（24）。 2.和/或所述退料杆（11）上設有退料限位件（110），所述下範本（6）或下模座（7）上設有退料限位台肩，所述退料限位件（110）的外徑小於所述頂杆限位件（100）的外徑。 3. 4. 5. 6. 7. | 東方藍天鈦金科技有限公司 | CN | 264006 山東省煙臺市高新區海天路9號 | 東方藍天鈦金科技有限公司 | CN | - | - | - | F16B037/00 | F16B037/00 F16B039/28 B21K001/70 B21J013/02 B21J005/02 | 3 | 5 | - | - | - | - | - | - | - | - | - | - | - | 高超 申慶援 王曉亮 洪俊傑 王曉穎 王玉臣 劉雪濤 劉岩鬆 李啟學 呂年華 | 10 | - | | 蘇紅紅 煙臺上禾智慧財產權代理事務所(普通合夥) 37234 | 20240514 | - | 閆曉 | 閆曉 | CN217713287 CN217440502 CN109396208 CN101837384 CN206972725 CN103350122 | 6 | US2006160629 GB462150 | 2 | - | 2 | 0 | CN117345752B | 1 | 1 | - | CN117345752 | 2024-01-05 | 18 | 東方藍天鈦金科技有限公司 | Valid | ||||
3 | CN118855830 | B | 2024-12-13 | 一種高溫環境用的無孔耳托板螺母及其加工工藝 | invention | CN202411337936.3 | 2024-09-25 | 本發明涉及航空航太緊固件技術領域，尤其涉及一種高溫環境用的無孔耳托板螺母及其加工工藝。螺母從左至右依次包括鉚接段、托板段、主體段、過渡段以及收口段；在托板段與主體段共同形成的內孔中設置有內螺紋；收口段內壁為尾部敞開式內錐面，所述收口段的內錐面用於與螺釘尾部的錐面進行接觸密封。相對于現有技術中採用尾部全封閉的防塵螺母而言，由於本發明採用尾部敞開式內錐面與螺釘的尾部錐面相接觸密封，裝配後的螺紋副不存在封閉空腔，因此在高溫情況下不會形成高壓氣室，有效避免了高溫氣體突然沖出危害其他零件的風險。採用本發明所提供的加工工藝製備得到的無孔耳托板螺母具有良好的高溫性能，適用於在高溫環境下進行零件緊固連接。; | 1.一種高溫環境用的無孔耳托板螺母的加工工藝，用於製作一種高溫環境用的無孔耳托板螺母，其特徵在於，所述高溫環境用的無孔耳托板螺母從左至右依次包括鉚接段（1）、托板段（2）、主體段（3）、過渡段（4）以及收口段（5）；在所述托板段（2）與主體段（3）共同形成的內孔中設置有內螺紋（6）；所述收口段（5）內壁為尾部敞開式內錐面，所述收口段（5）的內錐面用於與螺釘（105）尾部的錐面進行接觸密封；在所述鉚接段（1）外周面設置有滾花（1a），在所述鉚接段（1）端面的棱邊上設置有倒斜角（1b）；在所述鉚接段（1）與托板段（2）之間設置有環形空開槽（7）；所述過渡段（4）的內徑大於所述內螺紋（6）直徑，所述過渡段（4）的內周面與所述內螺紋（6）之間採用過渡錐面（4a）進行過渡；在所述過渡段（4）的內周面位置處形成環形讓位槽（8）；所述鉚接段（1）的內孔的直徑大於所述內螺紋（6）直徑；所述鉚接段（1）的內孔與所述內螺紋（6）之間通過引導錐面（1c）進行過渡；所述收口段（5）的內錐面的錐度為60°；所述收口段（5）的內錐面口部的直徑公稱值為φ4.5mm；所述螺釘（105）的螺栓長度誤差不大於0.3mm；無孔耳托板螺母的材料為GH4033；在所述托板段（2）的外周面上設置有一對切平面（2a），兩個切平面（2a）呈180°對稱設置；所述托板段（2）靠近所述鉚接段（1）的端面與所述內螺紋（6）中心線的垂直度不大於0.03；加工工藝包括如下步驟：步驟S1、備料：採用高溫鎳基合金GH4033的冷拉棒材作為原材料；步驟S2、固溶熱處理；步驟S3、數控車：車削出鉚接段（1）、托板段（2）以及主體段（3）的外圓，車削環形空開槽（7）以及倒斜角（1b）；對鉚接段（1）的外周面加工滾花（1a）；進行鑽孔及鏜孔；收口段（5）的內孔按照直孔進行鏜削；切斷；採用一次裝夾加工，保證托板段（2）的端面與中心的垂直度；步驟S4、去毛刺後，對步驟S3中得到的零件進行數控車：車削過渡段（4）及收口段（5）的外圓，收口段（5）按照圓柱面進行車削；步驟S5、數控銑：銑削托板段（2）的外周面上切平面（2a），並對切平面（2a）的棱邊進行倒角；步驟S6、去毛刺、攻絲：對托板段（2）與主體段（3）共同形成的內孔進行攻絲，形成內螺紋（6）；步驟S7、中檢：對收口段（5）收口前的尺寸進行檢查；步驟S8、收口：在數控車床上採用旋壓裝置進行收口，使得收口段（5）的內、外周面均形成錐面；步驟S9、時效熱處理；步驟S10、噴砂、回牙、清洗、總檢、包裝入庫；在所述步驟S8中，進行收口所採用的旋壓裝置包括定位軸（9）、內錐模具頭（10）、支承座（11）、連接銷軸（12）以及夾持軸（13）；所述定位軸（9）用於安裝在數控車床上，並對無孔耳托板螺母進行裝夾定位；所述夾持軸（13）的右端用於裝夾在數控車床的刀架上；支承座（11）右端的內螺紋孔旋合在所述夾持軸（13）左端的外螺紋上；連接銷軸（12）插設在所述支承座（11）的中心孔中，且連接銷軸（12）的左端從支承座（11）的中心孔伸出後插設在內錐模具頭（10）的內孔中形成可轉動配合；在支承座（11）左端面的環形槽中設置有滾珠（14），且內錐模具頭（10）的右端面抵靠在滾珠（14）上；內錐模具頭（10）的內孔左端設置有成型錐面（10a）；所述定位軸（9）的左段設置為夾持部（9a）用於裝夾在數控車床上，所述定位軸（9）的右段設置為螺杆部（9b）用於與無孔耳托板螺母的內螺紋（6）進行螺紋配合；在夾持部（9a）與螺杆部（9b）之間設置有環形限位台（9c）；在所述螺杆部（9b）的右端一體成型有支承部（9d），支承部（9d）伸入至收口段（5）的內孔中，且在所述步驟S8進行收口時，所述收口段（5）的內錐面口部邊緣抵靠在支承部（9d）的外周面上。 | 1.一種高溫環境用的無孔耳托板螺母的加工工藝，用於製作一種高溫環境用的無孔耳托板螺母，其特徵在於，所述高溫環境用的無孔耳托板螺母從左至右依次包括鉚接段（1）、托板段（2）、主體段（3）、過渡段（4）以及收口段（5）；在所述托板段（2）與主體段（3）共同形成的內孔中設置有內螺紋（6）；所述收口段（5）內壁為尾部敞開式內錐面，所述收口段（5）的內錐面用於與螺釘（105）尾部的錐面進行接觸密封；在所述鉚接段（1）外周面設置有滾花（1a），在所述鉚接段（1）端面的棱邊上設置有倒斜角（1b）；在所述鉚接段（1）與托板段（2）之間設置有環形空開槽（7）；所述過渡段（4）的內徑大於所述內螺紋（6）直徑，所述過渡段（4）的內周面與所述內螺紋（6）之間採用過渡錐面（4a）進行過渡；在所述過渡段（4）的內周面位置處形成環形讓位槽（8）；所述鉚接段（1）的內孔的直徑大於所述內螺紋（6）直徑；所述鉚接段（1）的內孔與所述內螺紋（6）之間通過引導錐面（1c）進行過渡；所述收口段（5）的內錐面的錐度為60°；所述收口段（5）的內錐面口部的直徑公稱值為φ4.5mm；所述螺釘（105）的螺栓長度誤差不大於0.3mm；無孔耳托板螺母的材料為GH4033；在所述托板段（2）的外周面上設置有一對切平面（2a），兩個切平面（2a）呈180°對稱設置；所述托板段（2）靠近所述鉚接段（1）的端面與所述內螺紋（6）中心線的垂直度不大於0.03；加工工藝包括如下步驟：步驟S1、備料：採用高溫鎳基合金GH4033的冷拉棒材作為原材料；步驟S2、固溶熱處理；步驟S3、數控車：車削出鉚接段（1）、托板段（2）以及主體段（3）的外圓，車削環形空開槽（7）以及倒斜角（1b）；對鉚接段（1）的外周面加工滾花（1a）；進行鑽孔及鏜孔；收口段（5）的內孔按照直孔進行鏜削；切斷；採用一次裝夾加工，保證托板段（2）的端面與中心的垂直度；步驟S4、去毛刺後，對步驟S3中得到的零件進行數控車：車削過渡段（4）及收口段（5）的外圓，收口段（5）按照圓柱面進行車削；步驟S5、數控銑：銑削托板段（2）的外周面上切平面（2a），並對切平面（2a）的棱邊進行倒角；步驟S6、去毛刺、攻絲：對托板段（2）與主體段（3）共同形成的內孔進行攻絲，形成內螺紋（6）；步驟S7、中檢：對收口段（5）收口前的尺寸進行檢查；步驟S8、收口：在數控車床上採用旋壓裝置進行收口，使得收口段（5）的內、外周面均形成錐面；步驟S9、時效熱處理；步驟S10、噴砂、回牙、清洗、總檢、包裝入庫；在所述步驟S8中，進行收口所採用的旋壓裝置包括定位軸（9）、內錐模具頭（10）、支承座（11）、連接銷軸（12）以及夾持軸（13）；所述定位軸（9）用於安裝在數控車床上，並對無孔耳托板螺母進行裝夾定位；所述夾持軸（13）的右端用於裝夾在數控車床的刀架上；支承座（11）右端的內螺紋孔旋合在所述夾持軸（13）左端的外螺紋上；連接銷軸（12）插設在所述支承座（11）的中心孔中，且連接銷軸（12）的左端從支承座（11）的中心孔伸出後插設在內錐模具頭（10）的內孔中形成可轉動配合；在支承座（11）左端面的環形槽中設置有滾珠（14），且內錐模具頭（10）的右端面抵靠在滾珠（14）上；內錐模具頭（10）的內孔左端設置有成型錐面（10a）；所述定位軸（9）的左段設置為夾持部（9a）用於裝夾在數控車床上，所述定位軸（9）的右段設置為螺杆部（9b）用於與無孔耳托板螺母的內螺紋（6）進行螺紋配合；在夾持部（9a）與螺杆部（9b）之間設置有環形限位台（9c）；在所述螺杆部（9b）的右端一體成型有支承部（9d），支承部（9d）伸入至收口段（5）的內孔中，且在所述步驟S8進行收口時，所述收口段（5）的內錐面口部邊緣抵靠在支承部（9d）的外周面上。 2.如權利要求1所述的一種高溫環境用的無孔耳托板螺母的加工工藝，其特徵在於，在所述步驟S2中，固溶熱處理的方法為：將原材料置於真空熱處理爐，裝爐溫度應低於300℃，加熱至850~860℃，預熱30~40min，升溫至1090～1100℃，保溫480~500min，真空度應控制在13.3Pa以下；爐內真空油冷卻，並充入氬氣冷卻；在所述步驟S9中，時效熱處理的方法為：收口後螺母置於真空熱處理爐，裝爐溫度應低於100℃，加熱至700℃±10℃，保溫960~970min，真空度應控制在13.3Pa以下；爐內充入氬氣保護冷卻。 3.如權利要求1所述的一種高溫環境用的無孔耳托板螺母的加工工藝，其特徵在於，所述連接銷軸（12）為階梯軸形狀，從左至右外徑逐漸增大，依次包括旋轉配合段（12a）、插接段（12b）以及軸向限位頭（12c）；所述插接段（12b）插設在所述支承座（11）左半段的中心孔，在支承座（11）上旋合有頂緊螺釘（16），頂緊螺釘（16）的內端頂緊在插接段（12b）的外周面上；在所述夾持軸（13）的左端面設置有容置沉孔（13a）；所述軸向限位頭（12c）設置在容置沉孔（13a）內；在旋轉配合段（12a）的外周面設置有V型環槽（12d）；所述旋轉配合段（12a）插設在內錐模具頭（10）的內孔中形成可轉動配合；在內錐模具頭（10）上旋合有軸向限位頂絲（15），且軸向限位頂絲（15）內側尖端卡在V型環槽（12d）上。 | 貴州航飛精密製造有限公司 | CN | 550014 貴州省貴陽市貴陽國家高新技術產業開發區沙文科技產業園科創南路68號 | 貴州航飛精密製造有限公司 | CN | - | - | - | F16B037/14 | F16B037/14 F16B037/06 F16B033/00 B23P015/00 B21D022/14 B21D053/24 C21D009/00 C21D006/02 C21D001/773 | 4 | 8 | - | - | - | - | - | - | - | - | - | - | - | 黃明忠 肖木全 冀翔 王佳城 鄭平平 劉禎 漆梅涵 高俊 | 8 | - | | 石勇 貴州派騰智慧財產權代理有限公司 52114 | 20241213 | - | 姚紅 | 姚紅 | CN116006565 | 1 | - | 0 | - | 1 | 0 | CN118855830B | 1 | 1 | - | CN118855830 | 2024-10-29 | 19 | 貴州航飛精密製造有限公司 | Valid | ||||
4 | CN111761019 | B | 2022-05-27 | 一種大扁圓頭鉚釘及大扁圓頭鉚釘的密封鉚接方法 | invention | CN202010534913.7 | 2020-06-12 | 本發明屬於航空裝配技術領域，公開了一種大扁圓頭鉚釘及大扁圓頭鉚釘的密封鉚接方法，基於飛機整體油箱的組、部件密封防腐的連接需求，設計了特殊的大扁圓頭鉚釘進行緊固連接，為達到連接的密封，設計了專用的配套鉚模，在鉚接的過程中達到過盈配合的效果，同時為保證強化密封效果，設計了一種配套的工藝方法。本發明有效的實現了飛機整體油箱的組、部件的密封緊固連接要求，顯著提升飛機機翼整體油箱結構及飛行性能。; | 1.一種大扁圓頭鉚釘，其特徵在於，包括鉚端和釘端，鉚端為圓盤狀，鉚端中部為圓形平臺，鉚端圓形平臺周邊有弧狀臺階，弧狀臺階圍成一個圓盤，鉚端的圓形平臺中間設有一個小圓凹槽；釘端為圓柱狀結構；釘端的圓柱狀結構直徑與鉚端中部圓形平臺的直徑相同，鉚端弧狀臺階所圍成的圓盤直徑是釘端圓柱狀結構直徑的兩倍，鉚端小圓凹槽的位於圓形平臺頂面處圓的直徑是釘端圓柱狀結構直徑的一半，鉚端的高度略大於鉚端小圓凹槽的直徑；鉚端圓形平臺相對於弧狀臺階有一個微小高度的臺階，鉚端弧狀臺階的弧度半徑略大於釘端圓柱狀結構的直徑。 | 1.一種大扁圓頭鉚釘，其特徵在於，包括鉚端和釘端，鉚端為圓盤狀，鉚端中部為圓形平臺，鉚端圓形平臺周邊有弧狀臺階，弧狀臺階圍成一個圓盤，鉚端的圓形平臺中間設有一個小圓凹槽；釘端為圓柱狀結構；釘端的圓柱狀結構直徑與鉚端中部圓形平臺的直徑相同，鉚端弧狀臺階所圍成的圓盤直徑是釘端圓柱狀結構直徑的兩倍，鉚端小圓凹槽的位於圓形平臺頂面處圓的直徑是釘端圓柱狀結構直徑的一半，鉚端的高度略大於鉚端小圓凹槽的直徑；鉚端圓形平臺相對於弧狀臺階有一個微小高度的臺階，鉚端弧狀臺階的弧度半徑略大於釘端圓柱狀結構的直徑。 2.一種大扁圓頭鉚釘的密封鉚接方法，其特徵在於，使用如權利要求1所述的一種大扁圓頭鉚釘，包括以下步驟：步驟一，預裝配整體油箱的各部件；步驟二，製作大扁圓頭鉚釘的初孔；步驟三，清洗整體油箱的各部件的金屬屑和雜物，去除初孔毛刺；步驟四，對整體油箱各部件的貼合面塗抹密封劑；步驟五，重新裝配和定位整體油箱的各部件，擰緊連接各部件的工藝螺栓；步驟六，對大扁圓頭鉚釘的初孔進行擴孔和鉸孔，得到鉚釘孔；步驟七，將大扁圓頭鉚釘放入鉚釘孔中，進行鉚接裝配。 3. 4. 5. 6. 7. 8. | 陝西飛機工業（集團）有限公司 | CN | 723213 陝西省漢中市34信箱 | 陝西飛機工業（集團）有限公司 | CN | - | - | - | B21J015/14 | B21J015/14 B21J015/38 F16B019/06 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 王聲 戴向黎 楊毅 肖望東 黃官平 甯博 范斌 吳慧 魏學志 方勇軍 王浩 周斌 | 12 | - | | 蔡麗華 貴州國防工業專利中心 52001 | 20220527 | - | 高聰娟 | 高聰娟 | - | 0 | - | 0 | - | 5 | 0 | CN111761019B | 1 | 1 | - | CN111761019 | 2020-10-13 | 15 | 陝西飛機工業（集團）有限公司 | Valid | ||||
5 | CN103557219 | B | 2015-09-30 | 輕型螺栓緊固件、其加工方法與模具 | invention | CN201310569562.3 | 2013-11-13 | 本發明涉及一種用於航空航太的輕型螺栓緊固件。其過渡部母線設計為呈近似正弦曲線的光滑曲線，過渡部錐段傾斜角相對較小，過渡部相對較短，結構比較合理；螺栓尾部的六角梅花形扳擰孔扳擰力矩較大、扳擰孔相對較短，方便了安裝，也減小了螺栓的整體長度，從而起到減重的作用；使用輕型螺栓過渡部車-滾軋R的模具，巧妙地強化了過渡部應力薄弱之處，滾軋R的模具簡單、成本低、操作簡便、效率更高；與該輕型螺栓緊固件配套使用的扳擰銷，比六方形扳擰銷能承載更大的扳擰力矩，並進一步減小了扳擰銷的長度、延長了扳擰銷的使用壽命。 | 前錐段Zt傾斜角 後錐段ZO傾 斜角 前錐段傾斜角 後錐段傾斜角 | 1.輕型螺栓緊固件，由螺栓頭、光杆段、過渡部和螺紋段組成，其 特徵在於：所述過渡部的母線設計為呈近似正弦曲線的光滑曲線，過渡 部前錐段Zt傾斜角At的角度範圍為10°≤At＜25°，過渡部後錐段ZO傾斜角A0的角度範圍為15°≤A0≤45°； 所述過渡部由第一弧段、第二弧段、前錐段、第三弧段、後錐段首 尾圓滑過渡連接而成，所述第一弧段具有相對較大的半徑，其始于光杆 段的末端並逐漸向內徑向延伸至與具有較小半徑的第二弧段相連接，所 述第二弧段與第三弧段之間由一個內公切于兩弧段之間的前錐段光滑連 接，所述第三弧段的末端逐漸向外徑向延伸並與後錐段相連，所述後錐 段經由常規的圓角過渡連接到螺紋段的相鄰端； 所述過渡部前錐段傾斜角At是指垂直于螺栓軸向的一條直線與過渡 部前錐段或其延伸線之間的夾角； 所述過渡部後錐段傾斜角A0是指平行于螺栓軸向的一條直線與過渡 部的後錐段或其延伸線之間的夾角。 2.如權利要求1所述輕型螺栓緊固件，其特徵在於：所述螺紋段尾 部的扳擰孔設計為內六角梅花孔； 所述內六角梅花孔的具體結構為突出的、均布於圓周方向的六個光 滑的弧狀夾緊瓣。 3.如權利要求1所述輕型螺栓緊固件，其特徵在於所述螺栓頭為平 面的平圓頭形或帶錐度的沉頭形。 4.一種加工如權利要求1所述的輕型螺栓緊固件的過渡部的方法， 其特徵在於採用先車後滾的加工工藝，即先利用車削類機床進行車削， 然後利用常規的滾軋工藝對過渡部進行滾軋，使之對過渡部應力薄弱之 處進行冷加工至滿足其物理性能要求。 5.一種應用於權利要求4所述方法的模具，其特徵在於包括通過螺 釘安裝於刀杆上的反車刀，以及通過軸承和滾軸安裝於刀柄上的滾輪。 | 東方藍天鈦金科技有限公司 | CN | 264003 山東省煙臺市高新區成海路9號 | 東方藍天鈦金科技有限公司 | CN | - | - | - | F16B035/04 | F16B035/04 F16B023/00 B23P015/00 B25B023/00 | 3 | 4 | - | - | - | 李順安 高慎金 王曉亮 李建華 | 4 | | 呂靜 煙臺雙聯專利事務所(普通合夥) 37225 | - | - | 賀燕萍 | 賀燕萍 | 0 | 0 | <text/> | 12 | 1 | CN103557219B | 1 | 1 | - | CN103557219 | 2014-02-05 | 8 | 東方藍天鈦金科技有限公司 | Valid | |||||||||||||||
6 | CN1333099 | 2007-08-22 | 形狀記憶合金防鬆螺母及其生產工藝 | invention | CN200410012262.6 | 2004-04-30 | 本發明涉及形狀記憶合金防鬆螺母及其生產工藝，其材料由以下重量份數比組份組成：C 0.01—0.05，Mn 15.0—17.0，Si 4.8—5.2，Cr8.5—9.5，Ni 6.5—7.5，P 0.01—0.03，S 0.01—0.02，N 0.03—0.05，Fe60.65—65.05，生產工藝如下：(1)按照上述要求備料，並冶煉軋製成帶外六角和內圓孔的鐵基形狀記憶合金棒料；(2)將棒料進行固溶處理：在950—1150 K下保溫30—60min；(3)將棒料進行形狀記憶訓練；(4)將棒料截成螺母毛壞，並按規定尺寸的94—96％加工內圓孔；(5)將螺母擴孔到標準尺寸，實現螺母的應力誘發馬氏體相變；(6)內螺紋的精加工，保證內螺紋具有一定的精度，減少配合的間隙，有效防止螺母加熱處理時恢復量的損失；(7)按預定力矩預緊螺母，並把螺母在500—800 K下保溫15—45min，實行恢復退火處理，然後投入使用，本發明廣泛用於機車車輛、軌道線路、機械設備、橋樑、汽車、石油化工、航空航太等領域的螺栓連接，對於保證整體結構的安全性和可靠性具有重要意義。 | 1、一種形狀記憶合金防鬆螺母，其材料由以下重量份數比組份組 成：C 0.01-0.05，Mn 15.0-17.0，Si 4.8-5.2，Cr 8.5-9.5，Ni 6.5-7.5， P 0.01-0.03，S 0.01-0.02，N 0.03-0.05，Fe 60.65-65.05。 | 1、一種形狀記憶合金防鬆螺母，其材料由以下重量份數比組份組 成：C 0.01-0.05，Mn 15.0-17.0，Si 4.8-5.2，Cr 8.5-9.5，Ni 6.5-7.5， P 0.01-0.03，S 0.01-0.02，N 0.03-0.05，Fe 60.65-65.05。 2、一種形狀記憶合金防鬆螺母生產工藝，其特徵在於： (1)按照權利要求1的成分要求備料，並冶煉軋製成帶外六角和 內圓孔的鐵基形狀記憶合金棒料； (2)將棒料進行固溶處理：在950-1150K下保溫30-60min； (3)將棒料進行形狀記憶訓練； (4)將棒料截成螺母毛壞，並按規定尺寸的94-96％加工內圓孔； (5)將螺母擴孔到標準尺寸，實現螺母的應力誘發馬氏體相變； (6)內螺紋的精加工； (7)按預定力矩預緊螺母，並把螺母在500-800K下保溫15- 45min，實行恢復退火處理，然後投入使用。 | 石家莊鐵道學院 | CN | 050043河北省石家莊市北環東路15號 | 石家莊鐵道學院 | CN | 河北 | - | - | - | C22C038/58 | C22C038/58 F16B039/00 | 2 | 2 | - | - | - | 杜彥良 孫寶臣 沈英明 李俊良 | 4 | CN | 董金國 石家莊新世紀專利商標事務所有限公司 | - | - | 王懷東 | 王懷東 | CNCN 1399002A | 1 | 0 | 21 | 10 | CN1333099 | 1 | 1 | - | CN1570185 | 2005-01-26 | 0 | 石家莊鐵道學院 | Overdue | |||||||||||||||
7 | CN109570328 | B | 2020-08-04 | 一種防鬆高溫合金止動墊圈及其製造方法 | invention | CN201811431495.8 | 2018-11-27 | 本發明屬於航空發動機製造、維修技術領域，公開了一種防鬆高溫合金止動墊圈，包括圓環部，所述圓環部左右兩側分別設置有兩個鎖緊爪，圓環部底部設置有止動爪，止動爪的長度為4‑8mm，止動墊圈採用GH3044材料製成；本發明的防鬆高溫合金止動墊圈，有效降低某型航空發動機使用過程中隔熱屏螺母脫落故障率。提升了發動機穩定性並且提高了操作者的裝配效率，保障了的飛行品質，節約了定檢、故障修理、重複試車成本。; | 1.一種防鬆高溫合金止動墊圈，其特徵在於，包括圓環部，所述圓環部左右兩側分別設置有兩個鎖緊爪，左側兩個鎖緊爪之間的夾角為60°，右側兩個鎖緊爪之間的夾角為60°，圓環部底部設置有止動爪，止動爪的長度為4-8mm，所述止動墊圈採用GH3044材料製成。 | 1.一種防鬆高溫合金止動墊圈，其特徵在於，包括圓環部，所述圓環部左右兩側分別設置有兩個鎖緊爪，左側兩個鎖緊爪之間的夾角為60°，右側兩個鎖緊爪之間的夾角為60°，圓環部底部設置有止動爪，止動爪的長度為4-8mm，所述止動墊圈採用GH3044材料製成。 2. 3.8-1mm。 4. 5.一種防鬆高溫合金止動墊圈的製造方法，製造如權利要求4所述的一種防鬆高溫合金止動墊圈，其特徵在於，包括以下步驟：步驟一：按規格尺寸下條料；步驟二：除去條料表面油污及標記；步驟三：以所述條料相鄰的一個長邊和一個短邊為基準，使用沖模沖切零件，確認止動墊圈厚度、止動爪寬度、左側兩個鎖緊爪的尖部到圓環部中心的距離、右側兩個鎖緊爪的尖部到圓環部中心的距離、圓環部內圓直徑、左側兩個鎖緊爪的尖部之間的距離、右側兩個鎖緊爪的尖部之間的距離和圓環部與止動爪的總長的尺寸；步驟四：將零件與磨料混合、攪拌，滾磨去毛刺後，將磨料與零件分開，並將零件清洗乾淨，自然晾乾或用壓縮空氣吹幹；步驟五：使用彎曲模對止動爪彎曲成型，確認彎折處到圓環部中心的距離和彎折處到止動爪末端的距離的尺寸；步驟六：對止動墊圈進行固溶處理。 6.如權利要求5所述的一種防鬆高溫合金止動墊圈的製造方法，其特徵在於，所述步驟四中的磨料為棕剛玉斜三棱柱模組，其規格為3mm×3mm×3mm的立方體，磨料與零件的體積比為3：1-4：1，滾磨時間為20min-25min。 7.如權利要求5所述的一種防鬆高溫合金止動墊圈的製造方法，其特徵在於，所述步驟四中的磨料為玻璃球，其規格為SΦ3mm-SΦ5mm的球體，磨料與零件的體積比為3：1-4：1，滾磨時間為25min-30min。 8.如權利要求5所述的一種防鬆高溫合金止動墊圈的製造方法，其特徵在於，所述步驟三中沖模的凸模選用階梯式圓形凸模，所述沖模的凸凹模均採用Cr12WoV材料製成，所述沖模的模架選用具有導向裝置的後導柱模架，沖模的固定板採用45號鋼製成，沖模的墊板採用T8A材料製成，沖模的卸料裝置選用彈性卸料裝置，所述沖模選用16噸衝床進行沖切。 9.如權利要求5所述的一種防鬆高溫合金止動墊圈的製造方法，其特徵在於，所述步驟五中彎曲模的模架選用具有導向裝置的後導柱模架，所述彎曲模選用16噸衝床進行彎曲。 | 中國航發瀋陽黎明航空發動機有限責任公司 | CN | 110043 遼寧省瀋陽市大東區東塔街6號 | 中國航發瀋陽黎明航空發動機有限責任公司 | CN | - | - | - | B21D028/14 | B21D028/14 B21D037/12 B23P015/00 B24B009/04 F16B039/24 F16B043/00 | 4 | 6 | - | - | - | - | - | - | - | - | - | - | - | 張賀 楊玉龍 張勇 孫汕民 張思秋 | 5 | - | | 李運萍 瀋陽東大智慧財產權代理有限公司 21109 | 20200804 | - | 童璐 | 童璐 | CN2799956 CN106975711 CN201891651 CN204253565 CN102996605 CN204545149 CN206329615 | 7 | JP2012112404 JP199674830 JPH0874830 | 3 | - | 7 | 2 | CN109570328B | 1 | 1 | - | CN109570328 | 2019-04-05 | 13 | 中國航發瀋陽黎明航空發動機有限責任公司 | Valid | ||||
8 | CN109372869 | B | 2020-10-02 | 一種高強度螺栓及其製造方法 | invention | CN201811161203.3 | 2018-09-30 | 本發明公開了一種高強度螺栓，由鋼絲加工而成，所述的鋼絲的化學成分的重量份數應滿足下述要求：C 0.25~0.35、Mn 0.40~0.60、Si 0.32~0.45、Cr 0.12~0.22、W 0.01~0.02、B 0.001~0.003、AI 0.01~0.05、Nb 0.05~0.1、V 0.02~0.05、Ti 0.001~0.005、Ni 0.05~0.05、P≤0.03、S≤0.02、Cu 0.20~0.35、Mo 0.25~0.40，餘量由Fe和不可避免的雜質構成，所述鋼絲通過備料‑高溫淬火‑等溫退火‑前變溫處理‑熱鍛‑拉絲‑後變溫處理來製備；該技術方案通過合理的配比，生產的螺栓強度高，可以滿足航太、石油探測等特殊行業的要求；該螺栓的強度達到13級，並且該螺栓的生產成本較低，便於大規模的推廣應用。 | 1.一種高強度螺栓，其特徵在於，由鋼絲加工而成，所述的鋼絲的化學成分的重量份數應滿足下述要求：C 0.25～0.35、Mn 0.40～0.60、Si 0.32～0.45、Cr 0.12～0.22、W 0.01～0.02、B0.001～0.003、AI 0.01～0.05、Nb 0.05～0.1、V 0.02～0.05、Ti 0.001～0.005、Ni0.05～0.05、P≤0.03、S≤0.02、Cu 0.20～0.35、Mo 0.25～0.40，餘量由Fe和不可避免的雜質構成，所述鋼絲通過備料-高溫淬火-等溫退火-前變溫處理-熱鍛-拉絲-後變溫處理來製備，所述的鋼絲的製備方法，具體步驟如下：(1)備料：將鋼料轉爐、爐外精煉、真空脫氣制得優質鐵水，將優質鐵水倒入模具中形成鋼坯；(2)高溫淬火：將鋼坯加熱至1050-1200℃後，放入到淬火液中進行高溫淬火，所述淬火液按重量份由5-10份的尿素、3-5份的碳酸氫鈉、2-4份的碳酸鈉、1-2份的硝酸銨、5-10份的聚乙烯醇、1-3份的鉬酸鉀、1-2份的丁酸、0.5-2份的丙酮、3-5份的聚丙烯-甲基丙烯酸、3-5份的聚丙烯醯胺以及30-45份的純化水在25-30℃下混合攪拌而成；(3)等溫退火：將高溫淬火後的鋼坯清洗乾淨後，在真空爐中加熱到1100-1200℃並進行奧氏體化，以80-300℃/秒的速度冷卻至500-720℃，在500-720℃的溫度中，每1mm直徑保持15-25秒進行等溫相變，之後以1-5℃的速度冷卻至120-300℃；(4)前變溫處理：將步驟(3)中的鋼坯加熱至500-600℃後取出迅速放置到-80℃的冷凍室中進行快速降溫，待鋼坯完全冷卻後，再將鋼坯以100-300℃/秒的速度加熱至500-600℃，再將加熱後的鋼坯取出迅速放置到-80℃的冷凍室中進行快速降溫，如此反復2-3次，取出鋼坯恢復至自然溫度；(5)熱鍛：初鍛溫度為950-1250℃、終鍛溫度為600-750℃，鍛造時30-45分鐘，鍛頭鍛造頻率為5-8次/分鐘；(6)拉絲：將熱鍛後的鋼坯降溫至300-400℃後，按照總斷面減縮率為35-65％的冷拉絲加工，製成鋼絲；(7)後變溫處理：將拉絲後的鋼絲加熱300-380℃後取出迅速放置到-20℃的冷凍室中進行快速降溫，待鋼坯完全冷卻後，再將鋼坯以50-100℃/秒的速度加熱至300-380℃，再將加熱後的鋼坯取出迅速放置到-20℃的冷凍室中進行快速降溫，如此反復3-5次，取出鋼絲恢復至自然溫度，將所述的鋼絲通過冷鍛成型-螺紋加工-鈍化處理-磷化處理-發黑處理來製備，具體步驟如下：(1)冷鍛成型：將鋼絲切斷至螺栓所需長度，常溫下放入模具型腔內，以鐓鍛力使之形成螺栓所需的頭部和杆部尺寸；(2)螺紋加工：在室溫下選用滾絲機進行螺紋成型；(3)鈍化處理：將螺栓螺栓放入到150-200℃的鈍化液中處理6-8分鐘，所述鈍化液按重量份由10-20份的雙氧水、5-10份的丙三醇、2-4份的骨膠、3-6份的絡蛋白、5-10份的氟化鈉、3-5份的氫氧化鈉、2-4份的矽酸鈉、2-5份的硫酸鈉、20-30份的純化水混合攪拌而成；(4)磷化處理：將鈍化處理後的螺栓放入55-75℃磷化處理液中浸泡5-7分鐘，在進行清洗、風乾，即得成品螺栓，其中磷化液按重量份由10-20份的馬日夫鹽、10-20份的磷酸二氫鋅、5-10份的氯化鋅、30-45份的磷酸、5-10份的五水硫酸銅、3-5份的硼酸、3-5份的酒石酸、50-80份的純化水混合攪拌而成；(5)發黑處理：對螺栓進行發黑處理，控制溫度90-105℃；時間15-25分鐘；再進行清洗、風乾，即得成品螺栓。 | 1.一種高強度螺栓，其特徵在於，由鋼絲加工而成，所述的鋼絲的化學成分的重量份數應滿足下述要求：C 0.25～0.35、Mn 0.40～0.60、Si 0.32～0.45、Cr 0.12～0.22、W 0.01～0.02、B0.001～0.003、AI 0.01～0.05、Nb 0.05～0.1、V 0.02～0.05、Ti 0.001～0.005、Ni0.05～0.05、P≤0.03、S≤0.02、Cu 0.20～0.35、Mo 0.25～0.40，餘量由Fe和不可避免的雜質構成，所述鋼絲通過備料-高溫淬火-等溫退火-前變溫處理-熱鍛-拉絲-後變溫處理來製備，所述的鋼絲的製備方法，具體步驟如下：(1)備料：將鋼料轉爐、爐外精煉、真空脫氣制得優質鐵水，將優質鐵水倒入模具中形成鋼坯；(2)高溫淬火：將鋼坯加熱至1050-1200℃後，放入到淬火液中進行高溫淬火，所述淬火液按重量份由5-10份的尿素、3-5份的碳酸氫鈉、2-4份的碳酸鈉、1-2份的硝酸銨、5-10份的聚乙烯醇、1-3份的鉬酸鉀、1-2份的丁酸、0.5-2份的丙酮、3-5份的聚丙烯-甲基丙烯酸、3-5份的聚丙烯醯胺以及30-45份的純化水在25-30℃下混合攪拌而成；(3)等溫退火：將高溫淬火後的鋼坯清洗乾淨後，在真空爐中加熱到1100-1200℃並進行奧氏體化，以80-300℃/秒的速度冷卻至500-720℃，在500-720℃的溫度中，每1mm直徑保持15-25秒進行等溫相變，之後以1-5℃的速度冷卻至120-300℃；(4)前變溫處理：將步驟(3)中的鋼坯加熱至500-600℃後取出迅速放置到-80℃的冷凍室中進行快速降溫，待鋼坯完全冷卻後，再將鋼坯以100-300℃/秒的速度加熱至500-600℃，再將加熱後的鋼坯取出迅速放置到-80℃的冷凍室中進行快速降溫，如此反復2-3次，取出鋼坯恢復至自然溫度；(5)熱鍛：初鍛溫度為950-1250℃、終鍛溫度為600-750℃，鍛造時30-45分鐘，鍛頭鍛造頻率為5-8次/分鐘；(6)拉絲：將熱鍛後的鋼坯降溫至300-400℃後，按照總斷面減縮率為35-65％的冷拉絲加工，製成鋼絲；(7)後變溫處理：將拉絲後的鋼絲加熱300-380℃後取出迅速放置到-20℃的冷凍室中進行快速降溫，待鋼坯完全冷卻後，再將鋼坯以50-100℃/秒的速度加熱至300-380℃，再將加熱後的鋼坯取出迅速放置到-20℃的冷凍室中進行快速降溫，如此反復3-5次，取出鋼絲恢復至自然溫度，將所述的鋼絲通過冷鍛成型-螺紋加工-鈍化處理-磷化處理-發黑處理來製備，具體步驟如下：(1)冷鍛成型：將鋼絲切斷至螺栓所需長度，常溫下放入模具型腔內，以鐓鍛力使之形成螺栓所需的頭部和杆部尺寸；(2)螺紋加工：在室溫下選用滾絲機進行螺紋成型；(3)鈍化處理：將螺栓螺栓放入到150-200℃的鈍化液中處理6-8分鐘，所述鈍化液按重量份由10-20份的雙氧水、5-10份的丙三醇、2-4份的骨膠、3-6份的絡蛋白、5-10份的氟化鈉、3-5份的氫氧化鈉、2-4份的矽酸鈉、2-5份的硫酸鈉、20-30份的純化水混合攪拌而成；(4)磷化處理：將鈍化處理後的螺栓放入55-75℃磷化處理液中浸泡5-7分鐘，在進行清洗、風乾，即得成品螺栓，其中磷化液按重量份由10-20份的馬日夫鹽、10-20份的磷酸二氫鋅、5-10份的氯化鋅、30-45份的磷酸、5-10份的五水硫酸銅、3-5份的硼酸、3-5份的酒石酸、50-80份的純化水混合攪拌而成；(5)發黑處理：對螺栓進行發黑處理，控制溫度90-105℃；時間15-25分鐘；再進行清洗、風乾，即得成品螺栓。 | 江蘇永昊高強度螺栓有限公司 | CN | 214518 江蘇省泰州市靖江市新港大道8號 | 江蘇永昊高強度螺栓有限公司 | CN | - | - | - | F16B035/00 | F16B035/00 B23P015/00 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 朱漢華 朱進 | 2 | - | | 王月霞 南京新慧恒誠智慧財產權代理有限公司 32424 | 20201002 | - | 駱雪芹 | 駱雪芹 | - | 0 | - | 0 | - | 7 | 1 | CN109372869B | 1 | 1 | - | CN109372869 | 2019-02-22 | 13 | 江蘇永昊高強度螺栓有限公司 | Valid | ||||
9 | CN111687464 | B | 2023-10-24 | 墊片製造方法和裝置 | invention | CN202010148022.8 | 2020-03-05 | 本申請公開了一種墊片製造方法和裝置。將機械工具插入到限定在兩個或更多個部件之間的墊片空間中，其中機械工具處於第一構造。機械工具不具有電子測量器件。當位於墊片空間中時修改機械工具，使得機械工具呈現第二構造，以建立相應於墊片空間的邊界表面的多個模型點。當將機械工具維持在第二構造時，從墊片空間中移除機械工具。當機械工具設置在墊片空間外部並處於第二構造時，用與工具不同的測量站電子地測量模型點的位置。基於測得的位置生成加工指令。基於生成的加工指令製造墊片。; | 1.一種製造墊片(24)的方法，其中，所述方法包括：步驟110，將機械工具(40)插入到限定在兩個或更多個部件(12、14)之間的墊片空間(20)中，其中所述機械工具處於第一構造；所述機械工具不具有電子測量器件；步驟120，當所述機械工具位於所述墊片空間中時，修改所述機械工具，使得所述機械工具呈現第二構造，以建立相應於所述墊片空間的邊界表面(22)的多個模型點(58)；步驟130，當將所述機械工具維持在所述第二構造時，從所述墊片空間中移除所述機械工具；步驟140，隨後，當所述機械工具設置在所述墊片空間外部並處於所述第二構造時，用不同於所述機械工具的測量站(60)電子地測量所述模型點相對於參考平面(47)的位置；步驟150，基於測得的位置生成加工指令；以及步驟160，基於生成的加工指令製造墊片。 | 1.一種製造墊片(24)的方法，其中，所述方法包括：步驟110，將機械工具(40)插入到限定在兩個或更多個部件(12、14)之間的墊片空間(20)中，其中所述機械工具處於第一構造；所述機械工具不具有電子測量器件；步驟120，當所述機械工具位於所述墊片空間中時，修改所述機械工具，使得所述機械工具呈現第二構造，以建立相應於所述墊片空間的邊界表面(22)的多個模型點(58)；步驟130，當將所述機械工具維持在所述第二構造時，從所述墊片空間中移除所述機械工具；步驟140，隨後，當所述機械工具設置在所述墊片空間外部並處於所述第二構造時，用不同於所述機械工具的測量站(60)電子地測量所述模型點相對於參考平面(47)的位置；步驟150，基於測得的位置生成加工指令；以及步驟160，基於生成的加工指令製造墊片。 2.基於生成的加工指令從墊片坯料(26)自動地銑削材料。 3.步驟152，基於測得的位置生成表面的虛擬模型；以及步驟154，基於所述虛擬模型生成加工指令。 4.步驟142，遠離所述墊片空間將所述機械工具插入到所述測量站中；以及步驟144，隨後，當所述機械工具處於所述第二構造時，機電地測量所述模型點相對於所述參考平面的位置。 5.其中，所述機械工具包括設置成相對於彼此間隔開的多個球狀探頭(57)；並且進一步包括：步驟124，在修改和移除之間，通過將多個所述球狀探頭鎖定在位而將所述機械工具鎖定在所述第二構造。 6.其中，每個球狀探頭安裝到通過相應的彈簧(56)偏置的相應的可滑動滑架(54)；其中，在插入期間，每個所述可滑動滑架被限制移動；並且其中，修改包括釋放所述可滑動滑架以通過相應的彈簧移動。 7.步驟146，在電子地測量之前校準所述測量站。 8.使用為線性差動變壓器的位置感測器(64)電子地測量。 9.步驟170，在製造之後，將制得的墊片插入到所述墊片空間中。 10.步驟180，此後使所述機械工具復位至所述第一構造。 11.一種製造用於飛機的龍骨梁的墊片的方法，包括：步驟110’，將機械工具(40)插入到墊片空間(20)中，其中所述機械工具處於第一構造；所述機械工具不具有電子測量器件；所述墊片空間限定在飛機的龍骨梁的後龍骨梁部分(12)和前龍骨梁部分(14)之間；步驟120，當所述機械工具位於所述墊片空間中時，修改所述機械工具，使得所述機械工具呈現第二構造，以建立相應於所述墊片空間的邊界表面(22)的多個模型點(58)；步驟124，當所述機械工具位於墊片空間中時，將所述機械工具鎖定在所述第二構造；步驟130，在鎖定之後，當將所述機械工具維持在所述第二構造時，從所述墊片空間中移除所述機械工具；步驟140，隨後，當所述機械工具設置在所述墊片空間外部並處於所述第二構造時，用不同於所述機械工具的測量站(60)電子地測量所述模型點相對於參考平面的位置；步驟150，基於測得的位置生成加工指令；以及步驟160，基於生成的加工指令製造墊片以形成所述墊片；其中，製造包括在製造機(80)處從墊片坯料自動地銑削材料。 12.步驟152，基於測得的位置生成表面的虛擬模型；以及步驟154，基於所述虛擬模型生成加工指令。 13.其中，所述機械工具包括設置成相對於彼此間隔開的多個球狀探頭(57)；並且其中，將所述機械工具鎖定在所述第二構造包括：通過將多個所述球狀探頭鎖定在位而將所述機械工具鎖定在所述第二構造。 14.其中，在插入期間，每個所述可滑動滑架被限制移動；並且其中，修改包括釋放所述可滑動滑架以通過相應的彈簧移動。 15.步驟180，此後使所述機械工具復位至所述第一構造。 16.一種用於製造插入到限定在兩個或更多個部件(12、14)之間的墊片空間(20)中的墊片(24)的系統(30)，所述系統包括：機械工具(40)，構造成能移除地插入到所述墊片空間中並在插入到其中時機械地測量所述墊片空間的邊界表面(22)；所述機械工具不具有電子測量器件；所述機械工具包括多個模型點(58)並能在第一構造和第二構造之間移動；其中，所述模型點在所述第一構造和所述第二構造之間相對於彼此不同地定位；測量站(60)，不同於所述機械工具，並構造成當所述機械工具設置在所述墊片空間外部並處於所述第二構造時電子地測量所述模型點相對於參考平面(47)的位置；處理線路(70)，構造成基於測得的位置生成加工指令；以及製造機(80)，構造成基於生成的加工指令製造所述墊片。 17. 18.基於測得的位置生成表面的虛擬模型；並且基於所述虛擬模型生成加工指令。 19. 20.多個球狀探頭(57)；以及相應的多個鎖定件(59)，操作成鎖定多個所述球狀探頭；其中，每個所述球狀探頭安裝到通過相應的彈簧(56)偏置的相應的可滑動滑架(54)；其中，所述鎖定件構造成使得：當鎖定時，相應的可滑動滑架被限制移動；並且當解鎖時，相應的可滑動滑架通過相應的彈簧而自由移動。 | 波音公司 | US | 美國伊利諾斯州 | 波音公司 | US | - | - | - | B23C003/00 | B23C003/00 G01B007/00 F16B043/00 | 3 | 3 | - | - | - | - | - | - | - | - | 16/351,693 US16/351,693 102019000351693 US102019000351693 | 2019-03-13 | US | 納森·阿方斯·塞奇 道格拉斯·阿蘭·鐘斯 布倫特·F·克雷格 | 3 | - | | 瞿藝 北京康信智慧財產權代理有限責任公司 11240 | 20250311 | - | 倉公林 | 倉公林 | CN101836092 CN106737275 CN107984007 | 3 | US8813382 US2012316666 US2008110275 US2001046323 WO2014042115 | 5 | - | 5 | 0 | CN111687464B US11396071 EP3709112B1 BR102020004195A2 | 4 | 4 | - | CN111687464 | 2020-09-22 | 15 | THE BOEING COMPANY | Valid | ||||
10 | CN114453841 | A | 2022-05-10 | 一種航空航太用耐熱鈦合金螺栓的製備方法和應用 | invention | CN202210154567.9 | 2022-02-14 | 本發明提供了一種航空航太用耐熱鈦合金Ti60螺栓加工製造方法和應用，採用Ti60鈦合金棒絲材製備；先採用三次熱鐓工藝將螺栓毛坯一端製成直徑為8‑16mm的螺栓頭，得到Ti60鈦合金螺栓一級半成品；再將其在1000℃‑1040℃下固溶處理，得到Ti60鈦合金螺栓二級半成品；對其進行尺寸加工，對尺寸加工的Ti60鈦合金螺栓二級半成品的杆部進行溫滾壓形成螺紋段，得到Ti60鈦合金螺栓三級半成品；對Ti60鈦合金螺栓三級半成品在真空熱處理爐中進行680℃‑720℃時效處理，得到Ti60鈦合金螺栓成品。本發明通過不同的加工和熱處理工藝組合，可獲得拉伸強度、剪切強度、高溫持久和室溫、高溫疲勞性能優良的鈦合金螺栓，適合在600℃～650℃範圍內使用。; | 1.一種航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於，包括以下步驟：步驟一、採用Ti60鈦合金棒絲材；步驟二、根據擬製備的Ti60鈦合金螺栓長度，截取相應長度的棒絲材作為螺栓毛坯送入多工位熱鐓機，通過三次熱鐓將螺栓毛坯一端製成直徑為8-16mm的螺栓頭，得到Ti60鈦合金螺栓一級半成品；步驟三、Ti60鈦合金螺栓一級半成品在1000℃-1040℃下進行固溶處理，得到Ti60鈦合金螺栓二級半成品；步驟四、對Ti60鈦合金螺栓二級半成品進行尺寸加工，對尺寸加工的Ti60鈦合金螺栓二級半成品的杆部進行溫滾壓形成螺紋段，滾壓溫度為500℃-600℃，得到Ti60鈦合金螺栓三級半成品；步驟五、Ti60鈦合金螺栓三級半成品在真空熱處理爐中進行時效處理，時效處理溫度為680℃-720℃，得到Ti60鈦合金螺栓成品。 | 1.一種航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於，包括以下步驟：步驟一、採用Ti60鈦合金棒絲材；步驟二、根據擬製備的Ti60鈦合金螺栓長度，截取相應長度的棒絲材作為螺栓毛坯送入多工位熱鐓機，通過三次熱鐓將螺栓毛坯一端製成直徑為8-16mm的螺栓頭，得到Ti60鈦合金螺栓一級半成品；步驟三、Ti60鈦合金螺栓一級半成品在1000℃-1040℃下進行固溶處理，得到Ti60鈦合金螺栓二級半成品；步驟四、對Ti60鈦合金螺栓二級半成品進行尺寸加工，對尺寸加工的Ti60鈦合金螺栓二級半成品的杆部進行溫滾壓形成螺紋段，滾壓溫度為500℃-600℃，得到Ti60鈦合金螺栓三級半成品；步驟五、Ti60鈦合金螺栓三級半成品在真空熱處理爐中進行時效處理，時效處理溫度為680℃-720℃，得到Ti60鈦合金螺栓成品。 2.按權利要求1所述航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於：步驟一中，採用Ti60鈦合金Φ6mm-Φ14mm直條退火態棒絲材。 3.按權利要求1所述航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於，步驟二中，所述三次熱鐓具體工藝為：一次熱鐓感應加熱工藝參數為電流1175A-1225A，保溫時間8s-16s；二次熱鐓感應加熱工藝參數為電流1125A-1175A，保溫時間8s-16s；三次熱鐓感應加熱工藝參數為電流1075A-1125A，保溫時間8s-16s。 4.按權利要求1或3所述航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於：步驟二中，一次熱鐓變形量為總變形量的45-55％；二次熱鐓變形量為總變形量的25-35％；三次熱鐓變形量為總變形量的15-25％。 5.按權利要求1所述航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於：步驟三中，所述固溶處理的保溫時間為1-3小時，固溶後油淬。 6.按權利要求1所述航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於：步驟四中，所述溫滾壓的保溫時間不低於10分鐘。 7.按權利要求1所述航空航太用耐熱鈦合金螺栓的製備方法，其特徵在於：步驟五中，所述時效處理的保溫時間為2-6小時，保溫結束後爐冷。 8.一種權利要求1所述方法在製備600℃～650℃範圍內使用的耐熱鈦合金Ti60螺栓的應用。 | 中國科學院金屬研究所 | CN | 110015 遼寧省瀋陽市沈河區文化路72號 | 中國科學院金屬研究所 | CN | - | - | - | - | B23P015/00 | B23P015/00 F16B035/00 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 朱紹祥 王清江 劉建榮 王磊 陳志勇 李文淵 趙子博 | 7 | - | | 張晨 瀋陽晨創科技專利代理有限責任公司 21001 | 20220510 | - | - | - | - | 0 | - | 0 | - | 3 | 0 | CN114453841A | 1 | 1 | - | CN114453841 | 2022-05-10 | 17 | 中國科學院金屬研究所 | Pub. | |||
11 | CN103452986 | B | 2015-11-04 | 一種輕型化抗疲勞自鎖螺母及其製造方法 | invention | CN201310344479.6 | 2013-08-08 | 本發明公開了一種輕型化抗疲勞自鎖螺母，包括帶有內螺紋的螺母本體，所述螺母本體由扳擰段和承載段組成，在扳擰段與承載段之間設置有斷頸槽，在扳擰段內部沿螺母本體長度方向設有減輕槽；本發明還公開了一種用於製造輕型化抗疲勞自鎖螺母的方法，該方法是利用鍛件、棒材或板材作為自鎖螺母的基材直接模壓或鍛壓成型成螺母本體和減輕槽，所述自鎖螺母的基材材料為高溫合金、鈦合金、高強度鋼或超高強度鋼。本發明結構簡單，預緊力可控制，安全可靠性高，維護方便，製造工藝簡捷，可將自鎖螺母重量減少為原來的40%左右，在緊固件螺母連接方面就能減輕相當於飛機總重的1～1.5%的重量，對飛機的載重能力將有很大的貢獻。 | 1.一種輕型化抗疲勞自鎖螺母，包括帶有內螺紋(3)的螺母本 體(6)，其特徵在於：所述螺母本體(6)由扳擰段(1)和承載段(5) 組成，在扳擰段(1)與承載段(5)之間設置有斷頸槽(4)，在扳擰 段(1)內部沿螺母本體(6)長度方向設有減輕槽(2)；所述扳擰段 (1)包括外扳擰面(101)及內扳擰面(102)，其中外扳擰面(101) 的斷面形狀為圓形、滾花形或呈3～12邊形；所述減輕槽(2)為由 內側面(201)、內扳擰面(102)及底部組成的一個環形槽，其中底 部與斷頸槽(4)靠承載段(5)的一面在同一個平面上；該自鎖螺母 的製造方法是直接通過模壓或鍛壓形成自鎖螺母，具體包括如下步 驟： a、製造螺母本體(1)和減輕槽(2)：根據待加工自鎖螺母的規 格，利用鍛件、棒材或板材作為自鎖螺母的基材直接模壓或鍛壓成型 成螺母本體(1)和減輕槽(2)； b、待步驟a所述的螺母本體(1)和減輕槽(2)模壓或鍛壓成 型後，針對上述自鎖螺母的規格依次加工外扳擰面(101)、斷頸槽(4) 和支撐面(501)； c、待步驟b所述的依次加工外扳擰面(101)、斷頸槽(4)和支 撐面(501)後，按常規螺紋加工方法加工內螺紋(3)； d、待步驟c所述的按常規螺紋加工方法加工內螺紋(3)後，在 減輕槽(2)的內側面(201)的中部向內螺紋(3)方向進行1～6點 擠壓變形。 | 1.一種輕型化抗疲勞自鎖螺母，包括帶有內螺紋(3)的螺母本 體(6)，其特徵在於：所述螺母本體(6)由扳擰段(1)和承載段(5) 組成，在扳擰段(1)與承載段(5)之間設置有斷頸槽(4)，在扳擰 段(1)內部沿螺母本體(6)長度方向設有減輕槽(2)；所述扳擰段 (1)包括外扳擰面(101)及內扳擰面(102)，其中外扳擰面(101) 的斷面形狀為圓形、滾花形或呈3～12邊形；所述減輕槽(2)為由 內側面(201)、內扳擰面(102)及底部組成的一個環形槽，其中底 部與斷頸槽(4)靠承載段(5)的一面在同一個平面上；該自鎖螺母 的製造方法是直接通過模壓或鍛壓形成自鎖螺母，具體包括如下步 驟： a、製造螺母本體(1)和減輕槽(2)：根據待加工自鎖螺母的規 格，利用鍛件、棒材或板材作為自鎖螺母的基材直接模壓或鍛壓成型 成螺母本體(1)和減輕槽(2)； b、待步驟a所述的螺母本體(1)和減輕槽(2)模壓或鍛壓成 型後，針對上述自鎖螺母的規格依次加工外扳擰面(101)、斷頸槽(4) 和支撐面(501)； c、待步驟b所述的依次加工外扳擰面(101)、斷頸槽(4)和支 撐面(501)後，按常規螺紋加工方法加工內螺紋(3)； d、待步驟c所述的按常規螺紋加工方法加工內螺紋(3)後，在 減輕槽(2)的內側面(201)的中部向內螺紋(3)方向進行1～6點 擠壓變形。 2.所述內側面(201)為圓形，內扳擰面(102)為圓形或多邊形， 且在內側面(201)的中部向內螺紋(3)方向設置有1～6個徑向擠壓 點。 3.所述減輕槽(2)的橫截面為矩形。 4.所述減輕槽(2)的橫截面為三角形或楔形。 5.所述承載段(5)上設有支撐面(501)，在支撐面(501)上設 置有齒形、平面或臺階。 6.所述步驟a中模壓或鍛壓的次數為3～6次。 | 貴州航太精工製造有限公司 | CN | 563000 貴州省遵義市紅花崗新浦鎮 | 貴州航太精工製造有限公司 | CN | - | - | - | F16B031/06 | F16B031/06 F16B037/00 F16B039/12 B23P015/00 | 2 | 4 | - | - | - | 王鵬 雷世斌 | 2 | | 谷慶紅 北京路浩智慧財產權代理有限公司 11002 | - | - | 駱雪芹 | 駱雪芹 | CN1087848 CN201180725 CN201425054 CN203453245 CN2381830 | 5 | DE10326005 | 1 | <text/> | 12 | 1 | CN103452986B | 1 | 1 | - | CN103452986 | 2013-12-18 | 8 | 貴州航太精工製造有限公司 | Valid | |||||||||||||
12 | CN113953773 | B | 2024-03-01 | 一種光杆直徑公差帶為9μm的螺栓加工控制方法 | invention | CN202111351502.5 | 2021-11-16 | 本發明提供一種光杆直徑公差帶為9μm的螺栓加工控制方法，該方法依次包括螺栓光杆直徑加工尺寸控制、螺栓螺紋滾壓加工、螺栓時效處理，其中螺栓螺紋滾壓加工與螺栓時效處理都採用現有的螺栓加工處理方式；所述螺栓光杆直徑加工尺寸控制包括以下步驟：①加工螺栓光杆直徑的上差時，在設計上差基礎上提高Nμm;所述N=d/1000，其中d為螺栓公稱直徑；②加工螺栓光杆直徑的公差帶時，按6μm進行控制；所述螺栓為GH4169應力持久型螺栓；所述螺栓光杆長度尺寸≤5mm。本發明所述方法科學合理，操作方便，有效的解決了光杆長度≤5mm的GH4169應力持久型螺栓在加工後光杆直徑實際尺寸不滿足設計要求的問題，可廣泛應用於航空發動機用光杆直徑公差帶為9μm的GH4169應力持久型螺栓的製造加工。; | 1.一種光杆直徑公差帶為9μm的螺栓加工控制方法，其特徵在於：該方法依次包括螺栓光杆直徑加工尺寸控制、螺栓螺紋滾壓加工、螺栓時效處理；所述螺栓光杆直徑加工尺寸控制包括以下步驟：①加工螺栓光杆直徑的上差時，在設計上差基礎上提高Nμm; 所述N=d/1000，其中d為螺栓公稱直徑；所述螺栓為GH4169應力持久型螺栓；所述螺栓光杆的長度尺寸≤5mm；②加工螺栓光杆直徑的公差帶時，按6μm進行控制。 | 1.一種光杆直徑公差帶為9μm的螺栓加工控制方法，其特徵在於：該方法依次包括螺栓光杆直徑加工尺寸控制、螺栓螺紋滾壓加工、螺栓時效處理；所述螺栓光杆直徑加工尺寸控制包括以下步驟：①加工螺栓光杆直徑的上差時，在設計上差基礎上提高Nμm; 所述N=d/1000，其中d為螺栓公稱直徑；所述螺栓為GH4169應力持久型螺栓；所述螺栓光杆的長度尺寸≤5mm；②加工螺栓光杆直徑的公差帶時，按6μm進行控制。 | 貴州航太精工製造有限公司 | CN | 563125 貴州省遵義市新蒲新區蝦子鎮 | 貴州航太精工製造有限公司 | CN | - | - | - | B23P015/00 | B23P015/00 B21H003/04 B24B005/22 F16B035/04 | 4 | 4 | - | - | - | - | - | - | - | - | - | - | - | 裴烈勇 樊開倫 胡隆偉 胡軍林 李祥 餘紹偉 | 6 | - | | 幸雲強 貴州昀博智慧財產權代理有限公司 52125 | 20240301 | - | 王躍琪 | 王躍琪 | CN103111808 CN103143661 CN104275358 CN106425303 CN112518254 CN113441674 CN204900482 CN207309577 CN207358143 CN214578207 | 10 | RU2350424 | 1 | 徐輔仁.修正襯套內孔公差帶消除裝配變形影響.石油機械.1988,(第11期),第15頁第1段-16頁最後1段.;丁景民,丁金福.套類零件的裝配、變形及其對策.機械設計與製造工程.2001,(第03期),全文.;鄭來辨.加工零件的尺寸中間公差的控制.設備管理與維修.1990,(第05期),全文.;聶陶蓀,李良英.影響隔膜泵導向精度的原因分析及解決辦法.中國陶瓷工業.1999,(第03期),全文.;陳春洪;.普通雙頭螺柱的滾絲機加工.金屬加工(冷加工).2010,(第17期),全文.;吳景華,鐘春敏.防止和克服薄壁襯套加工裝配變形的方法.黃石高等專科學校學報.2000,(第03期),全文. | 4 | 0 | CN113953773B | 1 | 1 | - | CN113953773 | 2022-01-21 | 16 | 貴州航太精工製造有限公司 | Valid | ||||
13 | US09803676 | B2 | 2017-10-31 | Hollow metal screw and method of making | invention | 15/079726 | 2016-03-24 | A hollow screw and related process of making is provided, wherein the hollow screw is formed from a generally circular corrosion resistant stainless steel disk cut from flat roll stock. The hollow screw includes a head and an elongated and hollow shaft having a wall thickness between about 0.2 to about 0.7 millimeters extending therefrom and defining a shank portion and a threaded portion having a plurality of threads thereon with a rotational drive mechanism configured to facilitate tightening via the threads. The process involves annealing to soften the stamped hollow screw, followed by thread rolling, and then age hardening the hollow screw. As such, the resultant hollow screw is relatively lightweight, about 50% the mass of a solid core screw made from the same material, with a sufficient thread strength to meet most aerospace applications and contributes to important aircraft fuel economy. | 1. A method for making a hollow screw, comprising the steps of: forming a shallow cup having a radially outwardly extending rough cut flange at one end thereof from a generally flat metal material;extruding an elongated and hollow body from the shallow cup;clipping and flattening the generally radially outwardly extending rough cut flange to the desired size and shape of a screw head;annealing to soften at least the elongated and hollow body;rolling a plurality of threads to at least a portion of the exterior of the softened elongated and hollow body, thereby forming the elongated and hollow body into a substantially smooth shank portion and a threaded portion; andhardening the hollow screw. | 1. A method for making a hollow screw, comprising the steps of: forming a shallow cup having a radially outwardly extending rough cut flange at one end thereof from a generally flat metal material;extruding an elongated and hollow body from the shallow cup;clipping and flattening the generally radially outwardly extending rough cut flange to the desired size and shape of a screw head;annealing to soften at least the elongated and hollow body;rolling a plurality of threads to at least a portion of the exterior of the softened elongated and hollow body, thereby forming the elongated and hollow body into a substantially smooth shank portion and a threaded portion; andhardening the hollow screw. 2. The method of claim 1, including the step of stamping a relatively circular blank from a roll stock of the flat metal material comprising a corrosion resistant A286 steel. 3. The method of claim 1, including the step of redrawing the elongated and hollow body into a shank portion and a redraw portion having an outer diameter relatively narrower than an outer diameter of the shank portion. 4. The method of claim 1, including the step of imparting an inner spline or Philips recess to the screw head. 5. The method of claim 1, wherein the annealing step includes the step of heating the hollow screw for about 1 hour at an elevated temperature of about 950-980 degrees Celsius, wherein the hollow screw comprises a hardness of about 79 Rockwell B after the annealing step. 6. The method of claim 1, including the step of inserting a stability pin into the elongated and hollow body during the rolling step, the stability pin comprising an outer diameter approximately the size of an inside diameter of the threaded portion of the elongated and hollow body, the stability pin supporting the peripheral wall thereof to prevent collapsing during the rolling step. 7. The method of claim 1, wherein the hardening step includes the step of heat treating the hollow screw by precipitation hardening for about 16 hours at a temperature of about 690-720 degrees Celsius. 8. The method of claim 1, wherein the hollow screw comprises a hardness of about 42 Rockwell C and the threads comprise a strength of about 1200-1400 MPa after the hardening step. 9. The method of claim 1, including the step of forming a rounded nose from one end of the elongated and hollow body. 10. The method of claim 1, including the step of keying a bottom formed recess into a closed end of the elongated and hollow body. 11. The method of claim 1, wherein the hollow screw comprises a weight of about ½ the weight of a solid core screw of sufficient thread strength. 12. A method for making a hollow screw, comprising the steps of: forming an elongated and hollow body having a wall thickness of about 0.2 to about 0.7 millimeters from a generally flat metal material;clipping and flattening one end of the elongated and hollow body into a desired size and shape of a screw head;annealing for about 1 hour at an ... | Physical Systems, Inc. | US | Physical Systems, Inc. | US | NV Carson City | Physical Systems, Inc. | US | - | B21K001/56 | B21K001/56 F16B023/00 C21D009/00 C21D006/02 C21D001/26 C22C038/58 C22C038/54 C22C038/50 C22C038/46 C22C038/42 C22C038/06 C22C038/02 B21D053/24 F16B033/00 F16B035/04 F16B037/02 B21H003/04 F16B035/00 F16B037/00 B21H003/02 C22C038/00 C22C038/04 C21D008/10 | 6 | 12 | - | F16B0023/00 | F16B0023/00 B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/56 C21D0001/26 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/0046 F16B0033/008 F16B0035/00 F16B0035/04 F16B0035/041 F16B0037/00 F16B0037/02 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | F16B0023/00 B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/56 C21D0001/26 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/18 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/0046 F16B0033/008 F16B0035/00 F16B0035/04 F16B0035/041 F16B0037/00 F16B0037/02 F16B0041/002 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | - | - | - | - | - | - | - | Charles G. Hutter, III | 1 | US | NV Carson City | Lowry Blixseth LLP Scott M. Lowry | - | - | Edward Tolan | Edward Tolan | US1098716 US1172406 US2151776 US2637672 US2667650 US3457573 US3615906 US3828382 US4157725 US4423616 US4824314 US4863333 US4878794 US5711711 US6526799 US6976381 US7237424 US2002/0182032 US2005/0220564 US2011/0185783 US2013/0195578 | 21 | - | 0 | “A286 technical Data” California Metal & Supply Inc. Captured on May 2, 2013. Retrieved from the Internet on Sep. 11, 2015. <http://www.californiametal.com/A286;Sheet;Plate;Pipe;Tube;Rod;Bar;Tech;Data.htm>. | 9 | 0 | EP3760335B1 KR1026075580000 KR1025491270000 KR1024521110000 EP3763458B1 CN112024631B EP3166738B1 CN106660107B JP6599971 US10161434 US09803676 US09689415 CN111889614A WO2016007557 CA2954530C RU2019118803A3 ES2928258T3 BR112017000363B1 RU2017102933A AU2020202876B2 BR122018013980B1 AU2015287923A1 CA2954530A1 RU2017102933A3 AU2020202881A1 AU2015287923B2 AU2020202881B2 RU2697536C2 CA3111258C ES2986081T3 BR112017000363A2 RU2019118803A AU2020202876A1 ES2826567T3 CA3111258A1 BR122018013986B1 | 36 | 11 | - | US20160208841 | 2016-07-21 | 11 | Physical Systems, Inc. | Valid | ||||
14 | CN115922237 | A | 2023-04-07 | 一種高韌性航空用緊固件的加工工藝 | invention | CN202211270879.2 | 2022-10-18 | 本發明公開了一種高韌性航空用緊固件的加工工藝，該加工工藝包括以下步驟：鈦合金坯料加工為適宜尺寸後，分段加工細螺紋部以及粗螺紋部，制得螺杆件；加工對應尺寸的螺母，包括鎖止螺母與底承螺母；通過設置上下兩段不同螺距的螺紋，分別為細螺紋部與粗螺紋部，配合兩組不同的鎖止螺母與底承螺母，在鎖止螺母與底承螺母分別螺紋在細螺紋部與粗螺紋部時，可致使鎖止螺母與底承螺母配合，並使底承螺母上的卡條卡接在鎖止螺母底部的卡槽內，在鎖止螺母與底承螺母產生震動或是與空氣摩擦而導致滑動時，會在卡條與卡槽的卡接效果下，限制該種運動，進而避免鎖止螺母與底承螺母脫離，有利於提高穩定性和安全性。; | 1.一種高韌性航空用緊固件的加工工藝，其特徵在於：該加工工藝包括以下步驟：步驟S1：鈦合金坯料加工為適宜尺寸後，分段加工細螺紋部（11）以及粗螺紋部（12），制得螺杆件；步驟S2：加工對應尺寸的螺母，包括鎖止螺母（13）與底承螺母（14）；步驟S3：螺紋連接鎖止螺母（13）、底承螺母（14）於步驟S1中的螺杆件上，且鎖止螺母（13）、底承螺母（14）分別螺紋連接在細螺紋部（11）與粗螺紋部（12）。 | 1.一種高韌性航空用緊固件的加工工藝，其特徵在於：該加工工藝包括以下步驟：步驟S1：鈦合金坯料加工為適宜尺寸後，分段加工細螺紋部（11）以及粗螺紋部（12），制得螺杆件；步驟S2：加工對應尺寸的螺母，包括鎖止螺母（13）與底承螺母（14）；步驟S3：螺紋連接鎖止螺母（13）、底承螺母（14）於步驟S1中的螺杆件上，且鎖止螺母（13）、底承螺母（14）分別螺紋連接在細螺紋部（11）與粗螺紋部（12）。 2.所述步驟S2中，底承螺母（14）的頂部焊接有立軸（141），且所述立軸（141）上套接有卡條（145）；所述立軸（141）上套接扭簧（146），且所述扭簧（146）的兩端卡接在底承螺母（14）與卡條（145）的相對面上；所述底承螺母（14）頂部焊接有連接片（142），且所述立軸（141）貫穿連接片（142）；所述底承螺母（14）的內側開設有凹槽（143）。 3.所述步驟S2中，鎖止螺母（13）的底部對應於卡條（145）開設有卡槽（131）；所述卡條（145）卡接在卡槽（131）內；所述卡條（145）設置四組，且四組所述卡條（145）圓周對稱佈置；所述卡槽（131）設置八組，且八組所述卡槽（131）圓周的對稱佈置；所述鎖止螺母（13）的底部契合連接在底承螺母（14）內的凹槽（143）內。 4.所述步驟S2中，在加工所述底承螺母（14）時，需要使用加工機構對底承螺母（14）與連接片（142）進行焊接。 5.所述加工機構包括底托板（21），且所述底托板（21）上開設有限位槽（22）；所述限位槽（22）內滑動連接有抵杆（24）；所述底托板（21）的底部轉動連接有傳動軸（254），且所述傳動軸（254）中部轉動連接有異形板（27）；所述傳動軸（254）底端固接有齒輪（252）。 6.所述異形板（27）的底部設置有密封殼（25），且所述密封殼（25）內開設有對稱佈置的兩組氣腔（251）；所述傳動軸（254）的底部貫穿在密封殼（25）內，且位於兩組氣腔（251）之間；所述齒輪（252）轉動連接在密封殼（25）內，且位於兩組氣腔（251）之間；所述氣腔（251）內活動連接有兩組活塞齒條（253），且兩組活塞齒條（253）中心對稱佈置；所述密封殼（25）一端連通有兩組氣嘴，且兩組所述氣嘴外端連通有氣管（26）。 7.所述底托板（21）的頂部固接有六邊形結構的護板（23），且所述護板（23）上開設有貫穿槽（231）；所述抵杆（24）設置為C型結構，且所述抵杆（24）靠近於護板（23）的一端貫穿在貫穿槽（231）內。 8.所述限位槽（22）內對立的兩端側壁上固接有限位軸（221），且所述限位軸（221）上行套接有一號彈簧（222）；所述一號彈簧（222）的兩端分別固接在限位槽（22）側壁與抵杆（24）相對面上。 9.所述抵杆（24）位於護板（23）內的一端底部固接有凸塊（244），且所述抵杆（24）位於護板（23）內的一端頂部開設有活動槽（241）；所述活動槽（241）底面上固接有二號彈簧（242），且所述二號彈簧（242）另一端固接有抵塊（243）；所述抵塊（243）貫穿抵杆（24）一側，且所述抵塊（243）突出部分的側壁上膠黏有橡膠條。 | 蕪湖天泰航空部件製造有限公司 | CN | 241000 安徽省蕪湖市灣沚區灣沚鎮北航蕪湖通航創新園5號樓9層22室 | 蕪湖天泰航空部件製造有限公司 | CN | - | - | - | - | B23P015/00 | B23P015/00 B23G001/00 F16B039/282 F16B035/04 F16B039/28 F16B037/00 | 3 | 5 | - | - | - | - | - | - | - | - | - | - | - | 張現勝 林培宗 王林信 | 3 | - | | 蔡慶新 安徽華普專利代理事務所(普通合夥) 34151 | 20230609 | - | - | - | - | 0 | - | 0 | - | 3 | 0 | CN115922237A | 1 | 1 | - | CN115922237 | 2023-04-07 | 17 | 蕪湖天泰航空部件製造有限公司 | Overdue | |||
15 | US09689415 | B2 | 2017-06-27 | Hollow metal screw and method of making | invention | 14/793651 | 2015-07-07 | A hollow screw and related process of making is provided, wherein the hollow screw is formed from a generally circular corrosion resistant stainless steel disk cut from flat roll stock. The hollow screw includes a head and an elongated and hollow shaft having a wall thickness between about 0.2 to about 0.7 millimeters extending therefrom and defining a shank portion and a threaded portion having a plurality of threads thereon with a rotational drive mechanism configured to facilitate tightening via the threads. The process involves annealing to soften the stamped hollow screw, followed by thread rolling, and then age hardening the hollow screw. As such, the resultant hollow screw is relatively lightweight, about 50% the mass of a solid core screw made from the same material, with a sufficient thread strength to meet most aerospace applications and contributes to important aircraft fuel economy. | 1. A hollow screw, comprising: a head formed from a flat stock of metal material;an elongated and hollow shaft including a cap configured to prevent flow through the hollow screw and formed from the flat stock of metal material and integrally extending from the head, the elongated and hollow shaft including a shank portion and a threaded portion having a plurality of threads thereon;an integral washer formed from the flat stock of metal material and having an enlarged horizontal surface area radially extending outwardly from the head;a captive washer positioned underneath the enlarged horizontal surface area and having an outer rim bent generally about an outer periphery of the integral washer at least partially sandwiching the integral washer therein, the captive washer being freely rotatable relative to the integral washer; anda rotational drive mechanism integrally formed from the flat stock of metal material and coupled with the head or at least a portion of the elongated and hollow shaft, and configured to facilitate tightening of the hollow screw by way of the threads. | 1. A hollow screw, comprising: a head formed from a flat stock of metal material;an elongated and hollow shaft including a cap configured to prevent flow through the hollow screw and formed from the flat stock of metal material and integrally extending from the head, the elongated and hollow shaft including a shank portion and a threaded portion having a plurality of threads thereon;an integral washer formed from the flat stock of metal material and having an enlarged horizontal surface area radially extending outwardly from the head;a captive washer positioned underneath the enlarged horizontal surface area and having an outer rim bent generally about an outer periphery of the integral washer at least partially sandwiching the integral washer therein, the captive washer being freely rotatable relative to the integral washer; anda rotational drive mechanism integrally formed from the flat stock of metal material and coupled with the head or at least a portion of the elongated and hollow shaft, and configured to facilitate tightening of the hollow screw by way of the threads. 2. The hollow screw of claim 1, wherein the shank portion and the threaded portion of the elongated and hollow shaft comprise a wall thickness between about 0.2 to about 0.7 millimeters and the captive washer comprises a conductive material having a thickness of about 0.15 to 0.30 millimeters. 3. The hollow screw of claim 1, wherein the rotational drive mechanism comprises an outer polygonal shape formed into the head from the flat stock of metal material. 4. The hollow screw of claim 1, wherein the rotational drive mechanism comprises an inner recess formed from the head. 5. The hollow screw of claim 4, wherein the inner recess comprises a spline recess. 6. The hollow screw of claim 1, wherein the rotational drive mechanism comprises an inner recess stamped into the head from the flat stock of metal material. 7. The hollow screw of claim 1, wherein the flat stock of metal material comprises a corrosion resistant metal material comprising A286 steel. 8. The hollow screw of claim 1, wherein the threads comprise a strength of about 1200 MPa to 1400 MPa. 9. The hollow screw of claim 1, including a nose formed at one end of the elongated and hollow shaft, wherein the head comprises a round head or a flat head. 10. The hollow screw of claim 1, wherein the threaded portion is relatively longer than the shank portion, and the threads have a major diameter relatively larger than an outer diameter of the shank portion. 11. The hollow screw of claim 1, including a wave washer sandwiched by the captive washer and the enlarged horizontal surface area of the integral washer. 12. A hollow screw, comprising: a head comprising a round head, a flat head, or a tapered head formed from a corrosion resistant flat stock metal material comprising A286 steel;an elongated and hollow shaft including a capped and tapered nose having a spline recess therein at an end opposite the head and ha... | Physical Systems, Inc. | US | Physical Systems, Inc. | US | NV Carson City | PHYSICAL SYSTEMS, INC. | US | - | F16B035/00 | F16B035/00 F16B023/00 C21D009/00 C21D006/02 C21D001/26 C22C038/58 C22C038/54 C22C038/50 C22C038/46 C22C038/42 C22C038/06 C22C038/02 B21D053/24 F16B033/00 F16B035/04 F16B037/02 B21H003/04 B21K001/56 F16B037/00 B21H003/02 C22C038/00 C22C038/04 C21D008/10 | 6 | 12 | - | F16B0023/00 | F16B0023/00 B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/56 C21D0001/26 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/0046 F16B0033/008 F16B0035/00 F16B0035/04 F16B0035/041 F16B0037/00 F16B0037/02 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | F16B0023/00 B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/56 C21D0001/26 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/18 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/0046 F16B0033/008 F16B0035/00 F16B0035/04 F16B0035/041 F16B0037/00 F16B0037/02 F16B0041/002 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | - | - | - | - | - | - | - | Charles G. Hutter, III | 1 | US | NV Carson City | Lowry Blixseth LLP Scott M. Lowry | - | - | Gary Estremsky | Gary Estremsky | US1098716 US1172406 US1247235 US1281174 US3424212 US3457573 US3841193 US4157725 US4414466 US4796927 US4878794 US4882925 US5052433 US5584628 US5711711 US6435791 US7445251 US8026455 US8429875 US8454290 US8753227 US2002/0182032 US2003/0042737 US2004/0172032 US2005/0220564 US2010/0047037 US2013/0195578 US2013/0213193 | 28 | - | 0 | “A286 technical Data” California Metal & Supply Inc. Retrieved from the Internet on Mar. 16, 2016. <http://www.californiametal.com/A286;Sheet;Plate;Pipe;Tube;Rod;Bar;Tech;Data;htm>. | 10 | 2 | EP3760335B1 KR1026075580000 KR1025491270000 KR1024521110000 EP3763458B1 CN112024631B EP3166738B1 CN106660107B JP6599971 US10161434 US09803676 US09689415 CN111889614A WO2016007557 CA2954530C RU2019118803A3 BR112017000363B1 ES2928258T3 RU2017102933A AU2020202876B2 BR122018013980B1 AU2015287923A1 CA2954530A1 RU2017102933A3 AU2015287923B2 AU2020202881A1 AU2020202881B2 RU2697536C2 CA3111258C ES2986081T3 BR112017000363A2 RU2019118803A AU2020202876A1 ES2826567T3 CA3111258A1 BR122018013986B1 | 36 | 11 | - | US20160003281 | 2016-01-07 | 10 | Physical Systems, Inc. | Valid | ||||
16 | CN107035753 | A | 2017-08-11 | 一種宇航結構用抗剪型十二角自鎖螺母及其加工工藝 | invention | CN201710458031.5 | 2017-06-16 | 本發明提供了一種宇航結構用抗剪型十二角自鎖螺母及其加工工藝，包括收口台、十二角支撐台和內螺紋孔，所述收口台為帶錐度的收口台，收口台的廣口端與十二角支撐台連接，且收口台與十二角支撐台同軸，以該軸線為軸心的收口臺上開有內螺紋孔，且內螺紋孔貫穿十二角支撐台。本發明所述的抗剪型十二角自鎖螺母具有扳擰力矩大、結構尺寸小、重量輕、防鬆可靠、強度高、耐熱耐蝕性能好、抗疲勞性能優異等優點，可推廣應用於航空航太、發動機、船舶、核能等武器裝備領域的重要承剪結構中。; | 1.一種宇航結構用抗剪型十二角自鎖螺母，其特徵在於：包括收口台(1)、十二角支撐台(2)和內螺紋孔(3)，所述收口台(1)為帶錐度的收口台(1)，收口台(1)的廣口端與十二角支撐台(2)的一側端面連接，且收口台(1)與十二角支撐台(2)同軸，以該軸線為軸心的收口臺上開有內螺紋孔(3)，內螺紋孔(3)貫穿十二角支撐台(2)。 | 1.一種宇航結構用抗剪型十二角自鎖螺母，其特徵在於：包括收口台(1)、十二角支撐台(2)和內螺紋孔(3)，所述收口台(1)為帶錐度的收口台(1)，收口台(1)的廣口端與十二角支撐台(2)的一側端面連接，且收口台(1)與十二角支撐台(2)同軸，以該軸線為軸心的收口臺上開有內螺紋孔(3)，內螺紋孔(3)貫穿十二角支撐台(2)。 2.所述收口台(1)的錐度為5°～15°。 3.所述收口台(1)的錐度為10°。 4.所述收口台(1)與所述十二角支撐台(2)組成的螺母的高度為內螺紋孔(3)上的內螺紋公稱直徑的0.8倍。 5.所述內螺紋孔(3)上的內螺紋為MJ或UNJ螺紋。 6.所述收口台(1)的廣口端的壁部厚度大於窄口端的壁部厚度。 7.所述十二角支撐台(2)包括支撐台，支撐台的外圓周上均勻的分佈有十二個角。 8.所述內螺紋孔(3)和收口台(1)收口後的橫截面積分別為橢圓形。 9.所述收口台(1)和十二角支撐台(2)分別為高溫合金材料製成的收口台(1)和十二角支撐台(2)。 10.一種如權利要求1-9中任一項所述的宇航結構用抗剪型十二角自鎖螺母的加工工藝，其特徵在於，包括如下加工步驟：1)、下料：單顆坯件準備，將原材料棒截斷成所需尺寸；2)、十二角頭成型：螺母的十二角區域採用熱鐓成型加工或者採用線切割加工；3)、螺紋孔加工：車床車螺母上的飛邊，車螺母端面並倒角，然後鑽鏜孔，最後對鏜孔進行攻絲；4)、錐形收口台成型：將坯件的一端加工成錐形收口台，收口台的錐度為5°～15°；5)、鎖緊區域收口加工：使用收口機對收口台的鎖緊區域進行收口，收口的標準以收口試驗合格為准；6)、熱處理：本螺母採用高溫合金材料製造而成，熱處理採用時效和穩定化處理；7)、探傷檢測：進行無損探傷檢測；8)、表面處理：對螺母表面進行鍍銀處理或者採用鍍鎘加二硫化鉬進行處理；9)、檢驗入庫。 | 航太精工股份有限公司 | CN | 300300 天津市東麗區華明工業園區濱海企業總部B06 | 航太精工股份有限公司 | CN | 天津 | - | - | - | F16B037/00 | F16B037/00 B23P015/00 | 2 | 2 | - | - | - | 黃孝慶 王川 林忠亮 劉敏麗 郭雙雙 賈曉嬌 王燕芳 | 7 | CN | | 楊慧玲 | - | - | 0 | 0 | 8 | 1 | CN107035753A | 1 | 1 | - | CN107035753 | 2017-08-11 | 12 | 航太精工股份有限公司 | Overdue | ||||||||||||||||
17 | CN103122900 | B | 2017-10-13 | 製備可高度變形的鈦和鈦合金單件緊固件的方法和由此方法製備的緊固件 | invention | CN201210467855.6 | 2012-11-19 | 一種製備可高度變形的鈦和鈦合金單件緊固件的方法和由此方法製備的緊固件。本發明涉及一種具有冷加工頭部區段、冷加工杆區段以及可延展的杆區段的緊固件，其中可延展的杆區段從冷加工杆區段延伸至緊固件的尾端部分。; | 1.一種由具有空心管腔的半管狀坯體前體形成的半管狀緊固件，所述空心管腔至少部分地延伸到所述半管狀坯體前體中，所述半管狀緊固件具有頭部和在尾端部分處終止的杆，所述頭部包括冷加工頭部區段(204)，所述杆包括冷加工杆區段(212)和可延展的杆區段(214)，所述可延展的杆區段(214)從所述冷加工杆區段(212)延伸至所述半管狀緊固件(200)的所述尾端部分(210)，所述冷加工杆區段通過在插入工具的軸杆被插入到所述空心管腔中時將擴大的杆部分的橫截面積減小2％到5％而形成，所述可延展的杆區段(214)是非冷加工的。 | 1.一種由具有空心管腔的半管狀坯體前體形成的半管狀緊固件，所述空心管腔至少部分地延伸到所述半管狀坯體前體中，所述半管狀緊固件具有頭部和在尾端部分處終止的杆，所述頭部包括冷加工頭部區段(204)，所述杆包括冷加工杆區段(212)和可延展的杆區段(214)，所述可延展的杆區段(214)從所述冷加工杆區段(212)延伸至所述半管狀緊固件(200)的所述尾端部分(210)，所述冷加工杆區段通過在插入工具的軸杆被插入到所述空心管腔中時將擴大的杆部分的橫截面積減小2％到5％而形成，所述可延展的杆區段(214)是非冷加工的。 2.所述冷加工頭部區段(204)和所述冷加工杆區段(212)具有比所述可延展的杆區段(214)高的強度。 3.所述可延展的杆區段(214)具有比所述冷加工頭部區段(204)和所述冷加工杆區段(212)高的延展性水準。 4.所述半管狀緊固件(200)具有至少一種下列材料成分：鋁、鋁合金。 5.所述半管狀緊固件(200)具有至少一種下列材料成分：鋼、鋼合金。 6.所述半管狀緊固件(200)具有至少一種下列材料成分：鈦和鈦合金。 7.所述半管狀緊固件具有超細顆粒材料成分。 8.所述冷加工頭部區段(204)和所述冷加工杆區段(212)通過冷加工工藝被形成。 9.一種裝配結構的方法，其包括如下步驟：提供由具有空心管腔的半管狀坯體前體形成的半管狀緊固件(200)，所述空心管腔至少部分地延伸到所述半管狀坯體前體中，所述半管狀緊固件具有頭部(203)和在尾端部分(210)處終止的杆(206)，所述頭部(203)包括冷加工頭部區段(204)，所述杆(206)包括冷加工杆區段(212)以及從所述冷加工杆區段(212)延伸至所述尾端部分(210)的可延展的杆區段(214)，所述冷加工杆區段通過在插入工具的軸杆被插入到所述空心管腔中時將擴大的杆部分的橫截面積減小2％到5％而形成，所述可延展的杆區段(214)是非冷加工的，所述冷加工頭部區段(204)和所述冷加工杆區段(212)具有比所述可延展的杆區段(214)高的強度；在所述結構(250)的孔眼(258)內安裝所述半管狀緊固件(200)；以及鐓鍛所述可延展的杆區段(214)的所述尾端部分(210)。 10.提供至少一種下列材料成分的所述半管狀緊固件(200)：鈦和鈦合金。 11.提供超細顆粒材料的所述半管狀緊固件(200)。 12.所述可延展的杆區段(214)具有比所述冷加工頭部區段(204)和所述冷加工杆區段(212)的延展性水準高的延展性水準。 13.所述冷加工頭部區段(204)和所述冷加工杆區段(212)通過冷加工工藝被形成。 14.提供使用耐腐蝕的、可固化有機塗層材料塗層的所述半管狀緊固件。 15.在飛機機身結構內安裝所述半管狀緊固件。 | 波音公司 | US | 美國伊利諾州 | 波音公司 | US | - | - | - | F16B015/00 | F16B015/00 F16B019/00 B23P015/00 | 2 | 3 | - | - | - | 13/299,228 US13/299,228 102011130299228 US102011130299228 | 2011-11-17 | US | S·G·琴爾 | 1 | US | 趙蓉民 北京紀凱智慧財產權代理有限公司 11245 | - | - | 周佐喜 | 周佐喜 | 0 | 0 | 13 | 0 | EP2594349B1 US10589342 JP6258580 CN103122900B US09649682 US20130125376 CA2792752C CA2792752A1 BR102012029191B1 BR102012029191A2 | 10 | 6 | - | CN103122900 | 2013-05-29 | 7 | THE BOEING COMPANY | Valid | |||||||||||||
18 | CN112539211 | B | 2022-10-04 | 一種具備絕緣駐留功能的鬆不脫螺釘及安裝方法 | invention | CN202011215782.2 | 2020-11-04 | 本發明公開了一種具備絕緣駐留功能的鬆不脫螺釘及安裝方法，屬於航天器儲能蓄電池安裝工具的領域，包括絕緣防脫套、緊固件、安裝孔墊套、駐留嵌件、防轉銷和絕緣墊；絕緣防脫套包括殼體，所述殼體的內腔包括上腔、中腔、過渡腔和底腔；底腔下埠有鉤爪；底腔的側壁開設有多個豁口；安裝孔墊套為圓柱結構，安裝孔墊套的下端面開設有下軸孔，安裝孔墊套的上端面開設有上軸孔，安裝孔墊套的側壁開設有長圓孔；駐留嵌件的側壁開設有連接防轉銷的銷孔；絕緣墊包括墊杆和墊塊；墊塊的側壁開設有多個豁口；墊塊埠設有凸爪；緊固件的頭部嵌入底腔內，緊固件的杆穿出殼體的下埠；駐留嵌件套接於緊固件的杆上；安裝孔墊套位於鉤爪和緊固件之間。; | 1.一種具備絕緣駐留功能的鬆不脫螺釘，其特徵在於，至少包括絕緣防脫套(1)、T形結構的緊固件(2)、安裝孔墊套(3)、駐留嵌件(4)、防轉銷(5)和絕緣墊(6)；其中：所述絕緣防脫套(1)包括：圓筒結構的殼體(1-1)，所述殼體(1-1)的內腔包括自上而下依次連通的圓臺形的上腔(1-2)、圓柱形的中腔(1-3)、圓臺形的過渡腔(1-4)、以及圓柱形的底腔(1-5)；所述上腔的上埠直徑大於下埠直徑；所述過渡腔的上埠直徑小於下埠直徑；在所述底腔下埠的內側向內延伸有鉤爪(1-6)；在所述底腔的側壁開設有多個縱向方向上的豁口；所述安裝孔墊套(3)為圓柱結構，在安裝孔墊套(3)的下端面開設有尺寸為R的下軸孔，在安裝孔墊套(3)的上端面開設有尺寸為r的上軸孔，其中：R大於r；且所述下軸孔和上軸孔共軸且相互連通；所述安裝孔墊套(3)的側壁開設有長圓孔；所述駐留嵌件(4)為圓環結構，在駐留嵌件(4)的側壁開設有連接防轉銷(5)的銷孔；所述絕緣墊(6)包括：一體成型的墊杆(6-1)和墊塊(6-2)；所述墊杆(6-1)和圓柱形的墊塊(6-2)均為圓筒形，且兩者為同軸關係；所述墊杆(6-1)的內徑小於墊塊(6-2)的內徑；所述墊杆(6-1)的外徑小於墊塊(6-2)的外徑；在所述墊塊(6-2)的側壁開設有多個縱向方向上的豁口；在所述墊塊(6-2)埠的內側向內延伸有凸爪；其中：所述緊固件(2)的頭部嵌入底腔(1-5)內，緊固件(2)的杆穿出殼體(1-1)的下埠；所述駐留嵌件(4)套接於緊固件(2)的杆上；所述安裝孔墊套(3)位於鉤爪(1-6)和緊固件(2)之間。 | 1.一種具備絕緣駐留功能的鬆不脫螺釘，其特徵在於，至少包括絕緣防脫套(1)、T形結構的緊固件(2)、安裝孔墊套(3)、駐留嵌件(4)、防轉銷(5)和絕緣墊(6)；其中：所述絕緣防脫套(1)包括：圓筒結構的殼體(1-1)，所述殼體(1-1)的內腔包括自上而下依次連通的圓臺形的上腔(1-2)、圓柱形的中腔(1-3)、圓臺形的過渡腔(1-4)、以及圓柱形的底腔(1-5)；所述上腔的上埠直徑大於下埠直徑；所述過渡腔的上埠直徑小於下埠直徑；在所述底腔下埠的內側向內延伸有鉤爪(1-6)；在所述底腔的側壁開設有多個縱向方向上的豁口；所述安裝孔墊套(3)為圓柱結構，在安裝孔墊套(3)的下端面開設有尺寸為R的下軸孔，在安裝孔墊套(3)的上端面開設有尺寸為r的上軸孔，其中：R大於r；且所述下軸孔和上軸孔共軸且相互連通；所述安裝孔墊套(3)的側壁開設有長圓孔；所述駐留嵌件(4)為圓環結構，在駐留嵌件(4)的側壁開設有連接防轉銷(5)的銷孔；所述絕緣墊(6)包括：一體成型的墊杆(6-1)和墊塊(6-2)；所述墊杆(6-1)和圓柱形的墊塊(6-2)均為圓筒形，且兩者為同軸關係；所述墊杆(6-1)的內徑小於墊塊(6-2)的內徑；所述墊杆(6-1)的外徑小於墊塊(6-2)的外徑；在所述墊塊(6-2)的側壁開設有多個縱向方向上的豁口；在所述墊塊(6-2)埠的內側向內延伸有凸爪；其中：所述緊固件(2)的頭部嵌入底腔(1-5)內，緊固件(2)的杆穿出殼體(1-1)的下埠；所述駐留嵌件(4)套接於緊固件(2)的杆上；所述安裝孔墊套(3)位於鉤爪(1-6)和緊固件(2)之間。 2. 3. 4. 5.一種基於權利要求1所述具備絕緣駐留功能的鬆不脫螺釘的安裝方法，其特徵在於，至少包括：S1、將安裝孔墊套(3)套進緊固件(2)；S2、將帶螺紋的駐留嵌件(4)旋入緊固件(2)，直至銷孔位置對準安裝孔套墊(3)的長圓孔；S3、將防轉銷(5)通過安裝孔套墊(3)的長圓孔插進駐留嵌件(4)的銷孔內；S4、將前述安裝好後的安裝孔墊套(3)嵌套入到絕緣墊(6)內孔；S5、將絕緣防脫套(1)嵌到安裝孔墊套(3)的溝槽內；S6、將絕緣墊(6)粘接進單機產品的結構孔內，即完成了安裝。 | 天津空間電源科技有限公司 | CN | 300384 天津市濱海新區濱海高新區華苑產業區（環外）海泰華科五路6號6幢 | 天津空間電源科技有限公司 | CN | - | - | - | F16B035/00 | F16B035/00 F16B039/04 F16B043/00 B23P021/00 H01B017/58 H01B017/56 | 3 | 5 | - | - | - | - | - | - | - | - | - | - | - | 郝永輝 吉雙澤 崔振海 | 3 | - | | 蒙建軍 天津市鼎和專利商標代理有限公司 12101 | 20221004 | - | 石偉 | 石偉 | CN205985569 CN205089768 CN209312844 CN210919733 CN207864383 | 5 | JP2005307481 | 1 | - | 5 | 0 | CN112539211B | 1 | 1 | - | CN112539211 | 2021-03-23 | 15 | 天津空間電源科技有限公司 | Valid | ||||
19 | CN115889495 | A | 2023-04-04 | 一種緊固件用Al-Mg合金線材的製備方法 | invention | CN202211627946.1 | 2022-12-16 | 一種緊固件用Al‑Mg合金線材的製備方法，涉及一種緊固件用鋁合金線材的製造方法領域。本發明是要解決Al‑Mg合金線材工業化批生產組織性能均勻性及高精度表面品質穩定性控制難度大等技術問題。目前市場上進口Al‑Mg合金線材的抗拉強度為305MPa～358MPa，本發明製備的Al‑Mg合金線材的抗拉強度為320MPa～354MPa，其性能與進口材料相當，使得該Al‑Mg合金線材不僅滿足緊固件用抽芯鉚釘的設計選材需求，將更有利於Al‑Mg合金線材在其他航空、航太和軌道交通結構件的連結上推廣使用。本發明製備的Al‑Mg合金線材用於緊固件抽芯鉚釘。; | 1.一種緊固件用Al-Mg合金線材的製備方法，其特徵在於緊固件用Al-Mg合金線材的製備方法過程如下：一、將Al-Mg合金錠坯進行擠壓、矯直和鋸切處理，得到Al-Mg合金擠壓棒材；二、將步驟一製備的Al-Mg合金擠壓棒材採用熱連軋的方式進行軋製，得到大盤重熱軋卷；三、將步驟二得到的大盤重熱軋捲進行退火，退火溫度為350℃～420℃，保溫2h～6h，出爐後空冷；四、將步驟三退火後的熱軋捲進行冷軋，加工至預定直徑線材，然後進行退火，退火溫度為350℃～420℃，保溫2h～6h，出爐後空冷，得到冷軋卷線材；五、將步驟四得到的冷軋卷線材經多道次拉拔加工至成品直徑線材，每道次拉拔前需進行退火，退火溫度為350℃～420℃，保溫2h～6h，出爐後空冷；六、將步驟五得到的成品直徑線材進行成品退火，退火溫度為100℃～300℃，保溫2h～6h，出爐後空冷，得到一種緊固件用Al-Mg合金線材。 | 1.一種緊固件用Al-Mg合金線材的製備方法，其特徵在於緊固件用Al-Mg合金線材的製備方法過程如下：一、將Al-Mg合金錠坯進行擠壓、矯直和鋸切處理，得到Al-Mg合金擠壓棒材；二、將步驟一製備的Al-Mg合金擠壓棒材採用熱連軋的方式進行軋製，得到大盤重熱軋卷；三、將步驟二得到的大盤重熱軋捲進行退火，退火溫度為350℃～420℃，保溫2h～6h，出爐後空冷；四、將步驟三退火後的熱軋捲進行冷軋，加工至預定直徑線材，然後進行退火，退火溫度為350℃～420℃，保溫2h～6h，出爐後空冷，得到冷軋卷線材；五、將步驟四得到的冷軋卷線材經多道次拉拔加工至成品直徑線材，每道次拉拔前需進行退火，退火溫度為350℃～420℃，保溫2h～6h，出爐後空冷；六、將步驟五得到的成品直徑線材進行成品退火，退火溫度為100℃～300℃，保溫2h～6h，出爐後空冷，得到一種緊固件用Al-Mg合金線材。 2.Mg為4.5％～5.6％、Mn為0.05％～0.2％、Cr為0.05％～0.2％、Ti為0.005％～0.04％、Si＜0.3％、Fe＜0.4％、餘量為Al。 3. 4. 5.A、將步驟一製備的Al-Mg合金擠壓棒材在電爐中加熱，待金屬溫度達到450℃～550℃時出爐熱連軋，軋製至預定規格大盤重熱軋卷；B、將製備的大盤重熱軋捲進行熱精紮，待金屬溫度達到450℃～550℃時出爐熱精軋，軋製至預定規格大盤重熱精軋卷。 6. 7.步驟五中的單道次冷加工率控制在25％～50％。 8. | 東北輕合金有限責任公司 | CN | 150060 黑龍江省哈爾濱市平房區新疆三道街11號 | 東北輕合金有限責任公司 | CN | - | - | - | - | B21C037/04 | B21C037/04 C22F001/047 C22C021/06 C22C021/08 C22C001/03 C21D009/52 F16B019/08 | 5 | 6 | - | - | - | - | - | - | - | - | - | - | - | 雷金琴 付金來 叢福官 吳沂哲 李婷 譚藝哲 韓明明 路麗英 呂丹 李俊乾 | 10 | - | | 李紅媛 哈爾濱市鬆花江專利商標事務所 23109 | 20230404 | - | - | - | - | 0 | - | 0 | - | 3 | 0 | CN115889495A | 1 | 1 | - | CN115889495 | 2023-04-04 | 17 | 東北輕合金有限責任公司 | Pub. | |||
20 | CN116833690 | A | 2023-10-03 | 航空耐熱螺栓的加工方法以及螺栓 | invention | CN202311121542.X | 2023-09-01 | 本發明提供了一種航空耐熱螺栓的加工方法以及螺栓，涉及航空緊固件技術領域，包括如下步驟：加工螺栓坯料形成螺栓主體；採用溫滾方式滾壓螺栓主體形成螺紋；其中，螺紋的牙頂和/或螺紋的牙底呈圓弧形設置；對螺栓的螺紋進行檢查，判斷滾壓出的螺紋是否合格；對檢驗合格的螺栓進行噴塗，在螺栓上形成防護塗層。本發明通過採用溫滾方式使得螺栓坯料的硬度降低，便於通過滾絲輪對螺栓主體進行滾壓以形成螺紋，顯著地減少了成型過程中螺紋上的裂紋及折疊紋。並且，通過使螺紋的牙頂及牙底呈圓弧形設置，使得螺紋的牙形更加飽滿、平順，更加便於後續對螺栓進行塗覆，提高了螺栓上的塗層均勻性，增加了螺栓的使用壽命。; | 1.一種航空耐熱螺栓的加工方法，其特徵在於，包括如下步驟：加工螺栓坯料形成螺栓主體；採用溫滾方式滾壓所述螺栓主體形成螺紋；其中，所述螺紋的牙頂和/或所述螺紋的牙底呈圓弧形設置；對所述螺栓的螺紋進行檢驗，判斷滾壓出的所述螺紋是否合格；對檢驗合格的所述螺栓進行噴塗，在所述螺栓上形成防護塗層。 | 1.一種航空耐熱螺栓的加工方法，其特徵在於，包括如下步驟：加工螺栓坯料形成螺栓主體；採用溫滾方式滾壓所述螺栓主體形成螺紋；其中，所述螺紋的牙頂和/或所述螺紋的牙底呈圓弧形設置；對所述螺栓的螺紋進行檢驗，判斷滾壓出的所述螺紋是否合格；對檢驗合格的所述螺栓進行噴塗，在所述螺栓上形成防護塗層。 2.如權利要求1所述的航空耐熱螺栓的加工方法，其特徵在於，所述加工螺栓坯料形成螺栓主體具體包括如下步驟：將所述螺栓胚料固定在車床上，利用所述車床的外圓車刀去除所述螺栓坯料上的多餘材料形成棒料；通過無心磨床對所述棒料的外圓進行精磨形成所述螺栓主體。 3.如權利要求1所述的航空耐熱螺栓的加工方法，其特徵在於，所述螺栓採用鎳基合金成型。 4.如權利要求3所述的航空耐熱螺栓的加工方法，其特徵在於，所述鎳基合金的成分的重量百分比為：Cr：18％-21％、Mo：3.5％-5.0％、Co：12％-15％、Al：1.2％-1.6％、Ti：2.75％-3.25％、B：0.003％-0.01％、C：0.02％-0.1％、Zr：0.02％-0.08％、Fe≥2.0％、Mn≥0.10％、Si≥0.15％、P≥0.015％、S≥0.015％、Cu≥0.10％，餘量為Ni。 5.如權利要求3所述的航空耐熱螺栓的加工方法，其特徵在於，所述鎳基合金的成分的重量百分比為：Ni：50％-55％、Cr：17％-21％、Mo：2.8％-3.3％、Nb：4.75％-5.50％、C≤0.08％、Mn≤0.35％、Si ≤0.35％、S≤0.015％、Cu≤0.30％、Al：0.20％-0.80％、Ti：0.65％-1.15％、B≤0.006％，餘量為Fe。 6.如權利要求3所述的航空耐熱螺栓的加工方法，其特徵在於，所述採用溫滾方式滾壓所述螺栓主體形成螺紋具體包括如下步驟：加熱螺栓主體的滾壓螺紋毛坯端，將所述滾壓螺紋毛坯端的溫度控制在300℃至400℃之間；利用滾絲輪滾壓所述螺栓主體形成所述螺紋。 7.如權利要求1所述的航空耐熱螺栓的加工方法，其特徵在於，所述對所述螺栓進行檢驗，判斷滾壓出的所述螺栓是否合格，具體包括如下步驟：將所述螺栓與預存的設計標準或技術圖樣進行對比，檢測所述螺栓的螺紋尺寸是否合格；對尺寸合格的所述螺栓進行檢查，剔除螺紋部位存在裂紋和折疊缺陷的所述螺栓。 8.如權利要求5所述的航空耐熱螺栓的加工方法，其特徵在於，所述對檢驗合格的所述螺栓進行噴塗，在所述螺栓上形成防護塗層，具體包括如下步驟：配製塗料；準備噴塗設備，並設置噴塗參數；利用所述噴塗設備對所述螺栓進行噴塗作業，在所述螺栓上形成所述防護塗層。 9.如權利要求8所述的航空耐熱螺栓的加工方法，其特徵在於，所述塗料通過鋁塗料和溶劑配置而成，所述溶劑為乙二醇乙醚醋酸酯，所述鋁塗料和所述溶劑的體積之比為1：3.8。 10.如權利要求8所述的航空耐熱螺栓的加工方法，其特徵在於，所述塗料通過二硫化鉬塗料和溶劑配置而成，所述溶劑為丙酮，所述二硫化鉬塗料和所述溶劑的品質之比為1：3。 11.如權利要求8所述的航空耐熱螺栓的加工方法，其特徵在於，所述防護塗層的厚度為10μm -20μm。 12.一種航空耐熱螺栓，其特徵在於，包括螺栓主體以及設置在所述螺栓主體上的螺紋，所述螺紋的牙頂和/或所述螺紋的牙底呈圓弧形設置，所述螺栓主體上塗覆有防護塗層。 | 北京航為高科連接技術有限公司 | CN | 100023 北京市大興區北京經濟技術開發區科創四街7號院2號樓1層101 | 北京航為高科連接技術有限公司 | CN | - | - | - | - | B23P015/00 | B23P015/00 F16B033/02 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 劉風雷 王立東 劉祥猛 孫昂 | 4 | - | | 王洪瑞 陳燁 北京三友智慧財產權代理有限公司 11127 | 20231003 | - | - | - | - | 0 | - | 0 | - | 2 | 1 | CN116833690A | 1 | 1 | - | CN116833690 | 2023-10-03 | 18 | 北京航為高科連接技術有限公司 | Pub. | |||
21 | CN102762336 | B | 2016-02-10 | 一種修理殼體凸緣的方法 | invention | CN201180008969.8 | 2011-01-28 | 本發明涉及一種修理渦輪機(諸如飛機渦輪螺旋槳發動機或渦輪噴氣發動機)的殼體(例如，鋁制殼體)凸緣(1)的方法，所述凸緣(1)包括至少一個螺栓穿過的通孔(2)，用於緊固設備，所述方法包括了如下連續步驟：在螺栓孔(2)周圍的凸緣(1)上，形成孔口平面；對孔口平面(5)的底表面(6)進行陽極氧化處理；在孔口平面(5)上置放墊圈(7)；以及採用粘合劑(8)將墊圈(7)固定到凸緣(1)上。 | 1.一種修理渦輪機鋁制殼體凸緣(1)的損壞區的方法，所述凸緣(1)包括至少 一個螺栓穿過的螺栓孔(2)，所述螺栓用於緊固設備，所述方法的特徵在於，其 包括了如下連續步驟： 在螺栓孔(2)周圍的凸緣(1)上，形成孔口平面，孔口平面的直徑大於損 壞區的直徑； 對孔口平面(5)的底表面(6)進行陽極氧化處理； 在孔口平面(5)上置放墊圈(7)，所述墊圈(7)採用硬度大於殼體材料硬度 的材料製成；以及 採用粘合劑(8)將墊圈(7)固定到凸緣(1)上。 | 1.一種修理渦輪機鋁制殼體凸緣(1)的損壞區的方法，所述凸緣(1)包括至少 一個螺栓穿過的螺栓孔(2)，所述螺栓用於緊固設備，所述方法的特徵在於，其 包括了如下連續步驟： 在螺栓孔(2)周圍的凸緣(1)上，形成孔口平面，孔口平面的直徑大於損 壞區的直徑； 對孔口平面(5)的底表面(6)進行陽極氧化處理； 在孔口平面(5)上置放墊圈(7)，所述墊圈(7)採用硬度大於殼體材料硬度 的材料製成；以及 採用粘合劑(8)將墊圈(7)固定到凸緣(1)上。 2. 3. 4. 5. 6. 7. 8. 9.一種用於渦輪發動機的殼體，所述殼體採用鋁、鋼，或複合材料製成， 並包括環形的凸緣(1)，所述凸緣採用根據權利要求1到8任一項所述方法製成， 所述凸緣包括至少一個螺栓孔(2)，該螺栓孔擴展成孔口平面(5)，所述孔口平 面(5)用於粘結墊圈(7)。 10. | 斯奈克瑪 | FR | 法國巴黎 | 斯奈克瑪 | FR | - | - | - | B23P006/00 | B23P006/00 F01D005/00 F04D029/40 F01D025/24 F16B005/02 F16B043/00 | 4 | 6 | - | - | - | 1000555 | 2010-02-10 | FR | 雅尼斯·伯勒提斯 吉恩-路易士·卡爾迪諾 瑟奇·德 塞提斯 朱利安·特雷 | 4 | | 宋義興 中國商標專利事務所有限公司 11234 | - | - | 陳均偉 | 陳均偉 | CN1584104 | 1 | EP1959094 JP昭63-55369 JP特開平10-183087 WO2010/007323 US2006/0251521 | 5 | <text/> | 14 | 0 | EP2533938B1 US09533383 CN102762336B JP5723389 WO2011098705 RU2557803C2 CA2788927A1 BR112012019179A2 FR2956054B1 CA2788927C BR112012019179B1 FR2956054A1 RU2012138360A | 13 | 9 | - | CN102762336 | 2012-10-31 | 6 | 斯奈克瑪 | Valid | ||||||||||
22 | CN111843392 | A | 2020-10-30 | 一種抽芯鉚釘芯杆的加工工藝 | invention | CN202010751238.3 | 2020-07-30 | 本申請公開了飛機零部件製造技術領域中的一種抽芯鉚釘芯杆的加工工藝，使用衝壓模對芯杆的材料進行冷鐓衝壓，得到坯料，坯料頭部直徑大於坯料杆部直徑，坯料杆部抗拉強度≥980MPa，坯料頭部抗拉強度≤590MPa。採用冷鐓衝壓加工成型的方法，通過對材料以及原材料尺寸的調節，使得冷鐓強縮處理後的坯料能一次性解決兩段抗拉強度不同的性能要求。; | 1.一種抽芯鉚釘芯杆的加工工藝，其特徵在於：使用衝壓模對芯杆的材料進行冷鐓衝壓，得到坯料，坯料頭部直徑大於坯料杆部直徑，坯料杆部抗拉強度≥980MPa，坯料頭部抗拉強度≤590MPa。 | 1.一種抽芯鉚釘芯杆的加工工藝，其特徵在於：使用衝壓模對芯杆的材料進行冷鐓衝壓，得到坯料，坯料頭部直徑大於坯料杆部直徑，坯料杆部抗拉強度≥980MPa，坯料頭部抗拉強度≤590MPa。 2.包括以下步驟：步驟一、備料：選抗拉強度≤590MPa的不銹鋼絲材，不銹鋼絲材的直徑以產品的d1為基準，比d1大1～2mm；步驟二、潤滑：對不銹鋼絲材進行草酸鹽潤滑處理；步驟三、冷鐓強縮：使用衝壓模，衝壓模包括大端和小端，將不銹鋼絲材從大端插入衝壓模中，冷鐓衝壓得到坯料，坯料包括a段和b段，其中a段的直徑大於b段的直徑；步驟四、試驗：對坯料a段和b段進行抗拉強度試驗，確保b段抗拉強度≥980MPa，a段抗拉強度≤590MPa；步驟五、加工：按工藝要求加工總長，按工藝要求將d1外圓磨到相應尺寸，按工藝要求磨削d尺寸，按工藝要求滾L2段環形槽，按工藝要求車外圓d2、d3，刻槽d4，車15°錐度得到芯杆。 3.還包括步驟六、表面處理：在芯杆表面塗二硫化鉬。 4.所述不銹鋼絲材的型號為1Cr18Ni9Ti。 5.所述步驟五加工d1尺寸和d尺寸時，採用無心磨加工。 | 貴州精立航太科技有限公司 | CN | 563000 貴州省遵義市紅花崗區南部新區盈田工穀產業園33號樓 | 貴州精立航太科技有限公司 | CN | - | - | - | - | B23P015/00 | B23P015/00 F16B019/08 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 穆仁強 楊德鬆 李小鬆 旦其江 吳軍 王相波 費堯剛 楊林 謝鬆武 李明燕 | 10 | - | | 張顯琴 重慶強大凱創專利代理事務所(普通合夥) 50217 | 20201030 | - | - | - | - | 0 | - | 0 | - | 5 | 0 | CN111843392A | 1 | 1 | - | CN111843392 | 2020-10-30 | 15 | 貴州精立航太科技有限公司 | Overdue | |||
23 | CN107058705 | A | 2017-08-18 | 一種應用在高鐵上的緊固件的生產工藝 | invention | CN201710086663.3 | 2017-02-17 | 本發明公開了一種應用在高鐵上的緊固件的生產工藝，依次進行鋼坯製備、鋼坯預熱、鋼坯加熱、盤條製備後冷卻得到線材盤條，再通過退火、酸洗、抽線、鍛造輾制或攻絲形成成型品，最後進行熱處理與表面覆膜處理後打包。本發明的生產工藝得到的緊固件能夠廣泛應用到核電行業、高鐵運輸行業、汽車運輸行業、航空航太行業、石油化工行業等特殊行業，具有高硬度、高強度、耐腐蝕性強、抗氧化性強等性能，減少了生產成本，提高了工作效率，能夠批量生產。 | 1.一種應用在高鐵上的緊固件的生產工藝，其特徵在於，包括如下步驟：（1）鋼坯製備：準備原料冶煉鋼水，用該鋼水連鑄成鋼坯；（2）鋼坯預熱：將鋼坯預熱處理，控制預熱段溫度為750~800℃，預熱時間為0.5~1h；（3）鋼坯加熱：將預熱後的鋼坯進行加熱處理，控制加熱段溫度為1000~1100℃，加熱時間為0.5~1h；（4）盤條製備：控制溫度在950~1000℃，時間為0.5~1h，然後將鋼坯軋製成盤條並吐絲成卷；（5）線材盤條：採用斯太爾摩控冷線進行盤條的軋後冷卻，使得冷卻後的盤條溫度小於或等於250℃，得到線材盤條，該線材盤條的各個組分之間的品質份如下：C 0.5~1份、Si0.1~0.5份、Mn 0.5~1份、P 0~0.05份、S 0~0.05份、Cr 0.1~0.5份、Ni 0.1~0.2份、Cu 0~0.01份、V0.01~0.02份以及餘量的Fe和雜質；（6）將線材盤條放入加熱爐內緩慢加熱到700~800℃，並保持6~7h，再將線材盤條在加熱爐內緩慢降溫至500℃以下後，從加熱爐中拿出線材盤條自然冷卻到常溫；（7）將步驟（6）中的線材盤條放入常溫、濃度為20~25%的鹽酸液中10~15min，用清水清洗鹽酸水中的腐蝕產物，然後依次將處理完的線材盤條放入草酸液、磷酸鹽液中形成皮膜後二次用清水清洗，並將清洗完的線材盤條與金屬皂反應形成金屬皂層；（8）將步驟（7）中處理完成的線材盤條先通過連續式伸線機進行粗抽並退火，再通過抽線機冷拉至所需的線徑；（9）將線材盤條經鍛造達到半成品的形狀、長度以及厚度，再將半成品輾制或攻絲以達到所需的螺紋，形成成型品；（10）將步驟（9）中的成型品加熱到800~900℃後進行淬火處理，在200~500℃時進行高溫回火並迅速冷卻至30~40℃；（11）表面處理：在成型品的表面覆有一保護層，並進行打包處理。 | 1.一種應用在高鐵上的緊固件的生產工藝，其特徵在於，包括如下步驟：（1）鋼坯製備：準備原料冶煉鋼水，用該鋼水連鑄成鋼坯；（2）鋼坯預熱：將鋼坯預熱處理，控制預熱段溫度為750~800℃，預熱時間為0.5~1h；（3）鋼坯加熱：將預熱後的鋼坯進行加熱處理，控制加熱段溫度為1000~1100℃，加熱時間為0.5~1h；（4）盤條製備：控制溫度在950~1000℃，時間為0.5~1h，然後將鋼坯軋製成盤條並吐絲成卷；（5）線材盤條：採用斯太爾摩控冷線進行盤條的軋後冷卻，使得冷卻後的盤條溫度小於或等於250℃，得到線材盤條，該線材盤條的各個組分之間的品質份如下：C 0.5~1份、Si0.1~0.5份、Mn 0.5~1份、P 0~0.05份、S 0~0.05份、Cr 0.1~0.5份、Ni 0.1~0.2份、Cu 0~0.01份、V0.01~0.02份以及餘量的Fe和雜質；（6）將線材盤條放入加熱爐內緩慢加熱到700~800℃，並保持6~7h，再將線材盤條在加熱爐內緩慢降溫至500℃以下後，從加熱爐中拿出線材盤條自然冷卻到常溫；（7）將步驟（6）中的線材盤條放入常溫、濃度為20~25%的鹽酸液中10~15min，用清水清洗鹽酸水中的腐蝕產物，然後依次將處理完的線材盤條放入草酸液、磷酸鹽液中形成皮膜後二次用清水清洗，並將清洗完的線材盤條與金屬皂反應形成金屬皂層；（8）將步驟（7）中處理完成的線材盤條先通過連續式伸線機進行粗抽並退火，再通過抽線機冷拉至所需的線徑；（9）將線材盤條經鍛造達到半成品的形狀、長度以及厚度，再將半成品輾制或攻絲以達到所需的螺紋，形成成型品；（10）將步驟（9）中的成型品加熱到800~900℃後進行淬火處理，在200~500℃時進行高溫回火並迅速冷卻至30~40℃；（11）表面處理：在成型品的表面覆有一保護層，並進行打包處理。 2.所述步驟（5）中在採用斯太爾摩控冷線進行冷卻時，控制盤條早珠光體相變前的冷速為10℃/s，珠光體相變溫度控制在650℃，相變後冷速為2℃/s。 3.所述步驟（7）中的金屬皂為鈉皂。 4.所述步驟（9）中的鍛造為冷間鍛造或者熱間鍛造。 5.所述步驟（10）中淬火處理採用水、油或者空氣淬火。 6.所述步驟（11）中表面處理採用電鍍、熱浸鍍鋅或者機械鍍。 | 江蘇佳傑特種螺釘有限公司 | CN | 225721 江蘇省泰州市興化市戴南鎮羅顧工業集中區 | 江蘇佳傑特種螺釘有限公司 | CN | 江蘇 | - | - | - | C21D008/00 | C21D008/00 C21D008/06 C23G001/08 C21D009/00 C21D001/18 C22C038/04 C22C038/02 C22C038/42 C22C038/46 C22C038/60 F16B035/00 F16B037/00 | 4 | 7 | - | - | - | 王長玉 張衛華 張冬萍 范軍平 | 4 | CN | | 周蔚然 | - | - | 0 | 0 | 8 | 0 | CN107058705A | 1 | 1 | - | CN107058705 | 2017-08-18 | 12 | 江蘇佳傑特種螺釘有限公司 | Overdue | ||||||||||||||||
24 | CN115091136 | A | 2022-09-23 | 一種小規格合金螺釘螺紋成形加工方法 | invention | CN202210797008.X | 2022-07-08 | 本發明提供一種小規格合金螺釘螺紋成形加工方法，其步驟依次包括頭部成形、熱處理、搓絲；螺釘熱處理後，對螺釘進行鍍銅處理，在螺釘表面鍍上一層銅層，鍍銅完成，再進行搓絲，搓絲後去除銅層。本發明所述加工方法既可保證螺紋通止合格，同時可大幅度提高搓絲板的使用壽命，採用在熱處理與搓絲之間增加鍍銅工序的工藝，加工M2的螺釘，一付搓絲板可加工1200件以上，使用壽命提高達10倍以上，省時省力，提升了加工效率，大幅度降低了加工成本，可在航太用3J01螺釘的製造領域進行推廣。; | 1.一種小規格合金螺釘螺紋成形加工方法，其步驟依次包括頭部成形、熱處理、搓絲；其特徵在於：螺釘熱處理後，對螺釘進行鍍銅處理，在螺釘表面鍍上一層銅層，鍍銅完成，再進行搓絲，搓絲後去除銅層。 | 1.一種小規格合金螺釘螺紋成形加工方法，其步驟依次包括頭部成形、熱處理、搓絲；其特徵在於：螺釘熱處理後，對螺釘進行鍍銅處理，在螺釘表面鍍上一層銅層，鍍銅完成，再進行搓絲，搓絲後去除銅層。 2.所述螺釘表面銅層厚度為3～7μm。 3.所述螺釘表面銅層厚度為5μm。 4.所述小規格合金螺釘採用鎳鉻合金製成。 5.所述小規格合金螺釘採用3J01合金製成。 6.所述螺釘的規格為M2、M2.5、M3螺釘規格之一。 | 貴州航太精工製造有限公司 | CN | 563000 貴州省遵義市新蒲新區蝦子鎮 | 貴州航太精工製造有限公司 | CN | - | - | - | - | B23P015/00 | B23P015/00 B21H003/06 C23C018/38 C25D003/38 F16B035/00 | 5 | 5 | - | - | - | - | - | - | - | - | - | - | - | 樊開倫 戴愛麗 裴烈勇 劉文成 宋文俊 王文娟 宋慶華 張永香 | 8 | - | | 幸雲強 遵義浩嘉智慧財產權代理事務所(普通合夥) 52112 | 20220923 | - | - | - | - | 0 | - | 0 | - | 3 | 0 | CN115091136A | 1 | 1 | - | CN115091136 | 2022-09-23 | 17 | 貴州航太精工製造有限公司 | Overdue | |||
25 | CN114645248 | A | 2022-06-21 | 一種表面抗咬合薄膜材料及其製備方法 | invention | CN202210320728.7 | 2022-03-29 | 本發明公開了一種表面抗咬合薄膜材料及其製備方法。通過在螺母表面依次沉積Cr金屬底層、CrN過渡層及CrAlBN功能層制得薄膜。本發明製備的薄膜具有良好的膜基結合力，能夠解決航空航太發動機在拆卸過程中因螺母與螺栓、墊片出現粘結而造成的使用壽命縮短的問題。 | 1.一種抗粘結薄膜，其特徵在於：該薄膜包括依次疊層設置的金屬底層、過渡層及功能層；所述金屬底層的成分為Cr，過渡層的成分為CrN，功能層的成分為CrAlBN。 | 1.一種抗粘結薄膜，其特徵在於：該薄膜包括依次疊層設置的金屬底層、過渡層及功能層；所述金屬底層的成分為Cr，過渡層的成分為CrN，功能層的成分為CrAlBN。 2.所述金屬底層的厚度為0.2-0.5μm，過渡層的厚度為0.5-1μm、功能層的厚度為2-4μm。 3.所述薄膜採用多弧離子鍍沉積在緊固件上，膜基結合區域包括緊固件的配合面。 4.如權利要求1所述的抗粘結薄膜的製備方法，其特徵在於：包括以下步驟：1)對緊固件表面進行噴砂處理；2)在惰性氣體氛圍中，對經過噴砂處理的緊固件進行清洗，然後利用金屬靶材在緊固件表面進行金屬底層的沉積；3)在氮氣氛圍下，利用金屬靶材在所述金屬底層上進行過渡層的沉積；4)在氮氣氛圍下，利用合金靶材在所述過渡層上進行功能層的沉積，得到抗粘結薄膜。 5.所述步驟1中，噴砂處理包括以下步驟：在0.2-0.4Pa壓力下用600-1200目的白剛玉顆粒轟擊緊固件表面。 6.所述噴砂處理前對緊固件端面分別採用不同細微性的砂紙進行研磨，然後進行精細拋光。 7.所述步驟2中，清洗包括以下步驟：將緊固件置於真空腔後向該真空腔中通入Ar氣，清洗過程中真空度為1.0-2.0Pa，偏壓為800-1200V，溫度為350-400℃，清洗時間為30-60min；所述步驟2中，金屬底層的沉積條件包括：真空腔中通入Ar氣，真空度為0.4-0.6Pa，時間為30-60min，偏壓自500V逐步降低為100V，弧電流為80-120A，占空比為30％-60％；所述步驟3中，過渡層的沉積條件包括：真空度為1.0-1.5Pa，時間為15-20min，偏壓為90-150V，弧電流為80-120A，占空比為30％-60％；所述步驟4中，功能層的沉積條件包括：真空度為3-5Pa，時間為100-140min，偏壓為40-70V，弧電流為80-120A，占空比為30％-60％。 8.如權利要求1所述的抗粘結薄膜在工件緊配合面的表面強化改性中的應用。 9.所述工件選自面向苛刻服役條件的緊固件。 10.所述緊固件選自航空航太發動機螺母。 | 西安交通大學 中國航發湖南動力機械研究所 | CN | 710049 陝西省西安市咸甯西路28號 | 西安交通大學 中國航發湖南動力機械研究所 | CN | - | - | - | - | C23C014/06 | C23C014/06 C23C014/16 C23C014/02 C23C014/32 F16B033/06 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 馬大衍 李浩 周澤堂 李萍 | 4 | - | | 范巍 西安通大專利代理有限責任公司 61200 | 20220621 | - | - | - | - | 0 | - | 0 | - | 3 | 0 | CN114645248A | 1 | 1 | - | CN114645248 | 2022-06-21 | 17 | 西安交通大學,中國航發湖南動力機械研究所 | Pub. | |||
26 | CN106837969 | A | 2017-06-13 | 一種抽芯鉚釘及使用該鉚釘的鉚接方法 | invention | CN201710038077.1 | 2017-01-19 | 本發明提供一種抽芯鉚釘，由鉚釘體和鉚芯軸組成，所述鉚釘體頭部加工有尖刃，用於刺入母材，尾部設有凸台，所述凸台靠近尖刃面設有母材凹槽，用於收容鑽孔時溢出的母材；遠離尖刃面設有驅動凹槽，用於傳遞扭矩；所述鉚芯軸頭部設有軸肩，與所述鉚釘體內壁過渡配合；中部設有應力槽，在應力作用下能夠使鉚芯軸折斷；尾部設有裝夾夾緊特徵和裝夾導向特徵。本發明提供的抽芯鉚釘及使用該鉚釘的鉚接方法，解決了航空航太等空間複雜區域無法預鑽孔的單面操作的高強度鉚接問題，具有高效自動化、力學性能佳、無多餘物的特點。; | 1.一種抽芯鉚釘，其特徵在於：由鉚釘體和鉚芯軸組成，所述鉚釘體頭部加工有尖刃，用於刺入母材，尾部設有凸台，所述凸台靠近尖刃面設有母材凹槽，用於收容鑽孔時溢出的母材；遠離尖刃面設有驅動凹槽，用於傳遞扭矩；所述鉚芯軸頭部設有軸肩，與所述鉚釘體內壁過渡配合；中部設有應力槽，在應力作用下能夠使鉚芯軸折斷；尾部設有裝夾夾緊特徵和裝夾導向特徵。 | 1.一種抽芯鉚釘，其特徵在於：由鉚釘體和鉚芯軸組成，所述鉚釘體頭部加工有尖刃，用於刺入母材，尾部設有凸台，所述凸台靠近尖刃面設有母材凹槽，用於收容鑽孔時溢出的母材；遠離尖刃面設有驅動凹槽，用於傳遞扭矩；所述鉚芯軸頭部設有軸肩，與所述鉚釘體內壁過渡配合；中部設有應力槽，在應力作用下能夠使鉚芯軸折斷；尾部設有裝夾夾緊特徵和裝夾導向特徵。 2.如權利要求1所述的抽芯鉚釘，其特徵在於，所述鉚釘體的材料為易變形純鈦或不銹鋼；所述鉚芯軸選用比鉚釘體強度和硬度更高的材料。 3.如權利要求1所述的抽芯鉚釘，其特徵在於，將鉚芯軸裝入鉚釘體，經多次衝壓，使鉚釘體完全包覆鉚芯軸形成封閉體。 4.如權利要求3所述的抽芯鉚釘，其特徵在於，對抽芯鉚釘進行整體精加工，以保證同軸度。 5.一種使用如權利要求1所述抽芯鉚釘的鉚接方法，其特徵在於，包括以下步驟：S1、通過驅動凹槽，驅動鉚釘體旋轉給進，刺入母材鑽孔直到鉚釘體尾部凸台緊貼母材後急停；S2、通過裝夾夾緊特徵和裝夾導向特徵，驅動鉚芯軸旋轉並逐漸回抽，使得軸肩膨脹並鎖合母材後急停；S3、施加應力使應力槽斷裂，將多餘鉚芯杆折斷取出。 | 上海航太設備製造總廠 | CN | 200245 上海市閔行區華甯路100號 | 上海航太設備製造總廠 | CN | 上海 | - | - | - | F16B019/10 | F16B019/10 B21J015/04 | 2 | 2 | - | - | - | 李鵬 趙維剛 範振昌 董豐波 喬鳳斌 董欣 | 6 | CN | | 金家山 | - | - | 0 | 0 | 8 | 1 | CN106837969A | 1 | 1 | - | CN106837969 | 2017-06-13 | 12 | 上海航太設備製造總廠 | Pub. | ||||||||||||||||
27 | CN119122907 | A | 2024-12-13 | 抗疲勞輕量化柱形緊固件設計方法、製造方法及緊固件 | invention | CN202411007529.6 | 2024-07-25 | 本發明提供了抗疲勞輕量化柱形緊固件設計方法、製造方法及緊固件，包括以下步驟：所述柱形緊固件內設有柱形腔體；所述柱形腔體與柱形緊固件同軸線設置的；根據螺栓的螺距和螺栓的公稱直徑確定柱形腔體截面積的取值範圍。本發明有益效果：相較于普通螺栓而言，提高了緊固件的抗疲勞性能，相較於細杆螺栓而言提高了抗彎性能，且降低了緊固件的品質，使得航空飛行器獲得更高的載重。; | 1.一種抗疲勞輕量化柱形緊固件設計方法，其特徵在於，包括以下步驟：所述柱形緊固件內設有柱形腔體；所述柱形腔體與柱形緊固件同軸線設置的；根據螺栓的極限利用係數、螺栓當前的利用係數和螺栓的公稱直徑確定柱形腔體截面積的取值範圍。 | 1.一種抗疲勞輕量化柱形緊固件設計方法，其特徵在於，包括以下步驟：所述柱形緊固件內設有柱形腔體；所述柱形腔體與柱形緊固件同軸線設置的；根據螺栓的極限利用係數、螺栓當前的利用係數和螺栓的公稱直徑確定柱形腔體截面積的取值範圍。 2.所述柱形緊固件為螺栓、螺釘、雙頭螺杆中的一種；根據螺栓的極限利用係數減去螺栓當前的利用係數後除以螺栓當前的利用係數得到螺栓可利用比例值；所述柱形腔體為圓柱形腔體；圓柱形腔體的截面積與螺柱截面積的比值為截面積減少率，螺栓可利用比例值與最大截面積減少率相同；根據最大截面積減少率與螺柱截面積的乘積作為圓柱形腔體的最大截面積。 3.根據螺栓的螺杆總長度和螺栓的螺距確定柱形腔體的長度；圓柱形腔體通過鑽孔方式加工，加工尺寸需要為整數，則圓柱形腔體的直徑在最大可取值點向下取整。 4.所述螺栓包括螺栓頭，圓柱形腔體在螺栓頭的端面上設有開口；圓柱形腔體的長度為螺栓總長度的減去第一指定倍數的螺栓螺距。 5.所述螺栓包括螺栓頭，圓柱形腔體在螺柱的端面上設有開口；圓柱形腔體的長度等於螺杆長度減去第二指定倍數的螺距數值；且圓柱形腔體的長度不小於螺紋長度與第三指定倍數螺距數值的和。 6.如果使用高一個直徑規格的所述螺栓替換實心螺栓使用時，確定圓柱形腔體直徑的取值範圍的公式如下：其中，ds，HBolt為比實心螺栓高一個直徑規格的螺栓等效直徑，ds，Bolt為實心螺栓的等效直徑。 7.所述螺栓包括螺栓頭，圓柱形腔體在螺栓頭的端面上設有開口；當被連接件厚度未知時，圓柱形腔體的長度為螺栓總長度的減去第一指定倍數的螺栓螺距；當被連接件厚度確定時，圓柱形腔體的長度不小於螺栓頭厚度、被連接件厚度、第四指定倍數螺距數值的和；且圓柱形腔體的長度不大於螺栓頭厚度、被連接件厚度、第五指定倍數螺距數值的和。 8.當所述緊固件為雙頭螺柱，且採用高一個直徑規格的通孔雙頭螺柱替換實心雙頭螺柱時，通孔雙頭螺柱的圓柱形腔體的直徑計算公式如下：其中，d2，HBolt為比實心雙頭螺柱高一個直徑規格的雙頭螺柱中徑，d2，Bolt為實心雙頭螺柱的中徑。 9.一種抗疲勞輕量化柱形緊固件，其特徵在於，所述緊固件應用權利要求1-8任一所述的設計方法設計製造而來。 10.一種製造如權利要求9所述的抗疲勞輕量化柱形緊固件的抗疲勞輕量化柱形緊固件製造方法，其特徵在於，通過以下步驟製造：S1、通過打孔的方式在螺栓內鑽取圓柱形腔體；S2、對經過打孔的螺栓進行熱處理。或通過以下步驟製造：A1、對螺栓進行熱處理；A2、對經過熱處理的螺栓通過打孔的方式鑽取圓柱形腔體。 | 昊宇睿聯（天津）科技有限公司 | CN | 300192 天津市南開區科研西路天津科技廣場3號樓0325（天開園） | 昊宇睿聯（天津）科技有限公司 | CN | - | - | - | - | F16B039/00 | F16B039/00 F16B033/06 B23B035/00 | 2 | 3 | - | - | - | - | - | - | - | - | - | - | - | 王赫 劉學通 王振宇 朱旻昊 劉建華 | 5 | - | | 吳英 北京力量專利代理事務所(特殊普通合夥) 11504 | 20241213 | - | - | - | - | 0 | - | 0 | - | 1 | 0 | CN119122907A | 1 | 1 | - | CN119122907 | 2024-12-13 | 19 | 昊宇睿聯（天津）科技有限公司 | Pub. | |||
28 | CN116944373 | A | 2023-10-27 | 一種彈性自鎖插銷及其成型工藝、航太設備 | invention | CN202310852844.8 | 2023-07-12 | 本申請公開了一種彈性自鎖插銷及其成型工藝、航太設備，所述彈性自鎖插銷的成型工藝，包括：使用彈性自鎖插銷成型模具來完成對為間隔式的彈性自鎖插銷的衝壓。由於為間隔式的彈性自鎖插銷通過彈性自鎖插銷成型模具完成雛形衝壓，後期以缺口為基礎對衝壓後的鋼絲切斷，以此獲得為間隔式的彈性自鎖插銷，解決了現有技術只能對整體式的插銷進行衝壓不能對為間隔式彈性自鎖插銷進行衝壓成型的問題。; | 1.一種彈性自鎖插銷的成型工藝，其特徵在於，包括：使用彈性自鎖插銷成型模具來完成對為間隔式的彈性自鎖插銷(1)的衝壓。 | 1.一種彈性自鎖插銷的成型工藝，其特徵在於，包括：使用彈性自鎖插銷成型模具來完成對為間隔式的彈性自鎖插銷(1)的衝壓。 2.如權利要求1所述的彈性自鎖插銷的成型工藝，其特徵在於：所述彈性自鎖插銷成型模具有供鋼絲(3)纏繞的胎芯(2)、供胎芯(2)放置的模座(5)及施加壓力的上模(4)來構成，在胎芯(2)、模座(5)及上模(4)構成供彈性自鎖插銷(1)成型的成型間隙(15)。 3.如權利要求2所述的彈性自鎖插銷的成型工藝，其特徵在於：所述胎芯(2)上設有銷孔安裝有定位銷(21)，所述模座(5)也設有銷孔供定位銷(21)安裝。 4.如權利要求2所述的彈性自鎖插銷的成型工藝，其特徵在於：所述胎芯(2)上設有對彈性自鎖插銷(1)衝壓成型後的缺口(22)，通過缺口(22)切斷衝壓後的鋼絲(3)。 5.如權利要求1所述的彈性自鎖插銷的成型工藝，其特徵在於，所述彈性自鎖插銷(1)的成型工藝具體使用彈性自鎖插銷成型模具完成加工的具體步驟如下：步驟一、作為原材料的鋼絲(3)纏繞在胎芯(2)上，纏繞時以定位銷(21)依靠定位；步驟二、將纏繞有鋼絲(3)的胎芯(2)放置到模座(5)中，胎芯(2)通過定位銷(21)與模座(5)銷孔配合安裝，而後上模(4)靠向模座(5)被向下衝壓鋼絲(3)在胎芯(2)上，此時，為間隔式的彈性自鎖插銷(1)在成型間隙(15)中被衝壓呈現雛形狀態。 6.如權利要求5所述的彈性自鎖插銷的成型工藝，其特徵在於：所述步驟二之後還包括上模(4)與模座(5)分離，將帶有被衝壓鋼絲(3)的胎芯(2)一同取出模座(5)中，以缺口(22)為基礎對衝壓後的鋼絲(3)切斷，以此獲得為間隔式的彈性自鎖插銷(1)。 7.一種採用如權利要求1至6任一項所述的彈性自鎖插銷的成型工藝獲得的彈性自鎖插銷，其特徵在於，包括：為水準狀態的水準段(11)、圓弧段(12)、為圓弧波浪形狀的自鎖段(13)及傾斜段(14)。 8.如權利要求7所述的彈性自鎖插銷，其特徵在於：所述圓弧段(12)一末端與水準段(11)一末端固定，圓弧段(12)另一末端向水準段(11)另一末端圓弧回轉彎曲懸空有間隔；所述自鎖段(13)一末端與圓弧段(12)另一末端向固定，自鎖段(13)另一末端懸空間隔在水準段(11)上；所述傾斜段(14)與自鎖段(13)另一末端固定，傾斜段(14)懸空間隔在水準段(11)上並向上呈現傾斜並與水準段(11)形成外擴開口，構成為間隔式的彈性自鎖插銷(1)。 9.一種航太設備，其特徵在於：包括設有插銷孔的部件及如如權利要求1至6任一項所述的彈性自鎖插銷的成型工藝獲得的彈性自鎖插銷，彈性自鎖插銷插入部件的插銷孔中。 | 貴州航太精工製造有限公司 | CN | 563000 貴州省遵義市新蒲新區蝦子鎮 | 貴州航太精工製造有限公司 | CN | - | - | - | - | B21F001/00 | B21F001/00 B21F011/00 B21F003/00 F16B019/02 | 2 | 4 | - | - | - | - | - | - | - | - | - | - | - | 李英亮 何昌福 先世兵 劉順旭 馬江紅 黃麗 何文軍 王孝利 王科 | 9 | - | | 石慶輝 貴州派騰智慧財產權代理有限公司 52114 | 20231027 | - | - | - | - | 0 | - | 0 | - | 2 | 0 | CN116944373A | 1 | 1 | - | CN116944373 | 2023-10-27 | 18 | 貴州航太精工製造有限公司 | Pub. | |||
29 | CN104439984 | A | 2015-03-25 | 一種航空用螺絲的加工工藝 | invention | CN201410778783.6 | 2014-12-17 | 本發明揭示了一種航空用螺絲的加工工藝，包括如下步驟：1盤元；2退火；3酸洗；4抽線；5成型；6輾牙；7熱處理；8表面處理。本發明中生產的螺絲適用於航空用，耐磨損，強度高，韌性好，不易損壞，使用壽命長。 | 1.一種航空用螺絲的加工工藝,其特徵在於：包括如下步驟： 1）盤元：從原料商出購買原始盤條作為基材； 2）退火：將需要處理的產品吊放爐內，並緊蓋爐蓋，將爐內溫度緩慢升至700℃左右，並在此溫度下保持6-7小時，之後將爐內溫度緩慢降至500℃，然後隨爐冷卻至常溫； 2 4 2 2 4）抽線：將酸洗後的盤元取出，放入抽線機冷拉至所需螺絲線徑； 5）成型：通過可動剪刀單向移動，將卡於剪模內的線材切成所需胚料，之後打模固定，一沖將產品頭部初步成型，當產品為一字割溝時，一沖模為內凹、橢圓槽，產品為十字槽時，一沖模為內凹四方槽，一沖之後，沖具整體運行，二沖模移向打模正前方，同時二沖模向前運行，將產品最終成型，之後由後沖棒將胚料推出，之後放入加熱設備將胚料需成型一端加熱至白熱狀態，7/8以下加熱10-12s，7/8-1加熱17-18s，將加熱後的胚料迅速移至成型機，通過後座，夾模固定，頭模衝擊胚料，加以成型，並於束杆機上利用擠壓將產品縮杆； 6）輾牙：將一塊牙板固定，另一塊活動牙板帶動產品移動，利用擠壓使產品產生塑性變形，形成所需螺紋； 7）熱處理：之後將成型螺絲在加熱到850℃左右在油中進行淬火，之後在400-500℃左右進行高溫回火，回火後迅速冷卻； 8）表面處理：最後將螺絲浸沒溫度約為550℃的溶化鋅的鍍槽內，使得螺絲表面上的鐵鋅合金漸漸變成產品外表面上的鈍化鋅，之後在200℃以下烘焙一天左右後，即取得最後的產品。 | 1.一種航空用螺絲的加工工藝,其特徵在於：包括如下步驟： 1）盤元：從原料商出購買原始盤條作為基材； 2）退火：將需要處理的產品吊放爐內，並緊蓋爐蓋，將爐內溫度緩慢升至700℃左右，並在此溫度下保持6-7小時，之後將爐內溫度緩慢降至500℃，然後隨爐冷卻至常溫； 3）酸洗：將退火後的整個盤元分別浸入常溫的鹽酸槽中，持續放入多個鹽酸槽內，直至完全除去盤元表面的氧化膜，之後放入清水中，清除線材表面的鹽酸腐蝕產物，再放入草酸中，增加金屬的活性，最後將盤元浸入磷酸鋅溶液中，使得基材表面與處理液接觸，基材溶解生成不溶性的Zn2Fe（PO4）2·4H2O，附著在基材表面形成皮膜；之後再放入清水中，清除皮膜表面殘餘物，之後使之與鈉皂反應，生成堅硬的金屬皂層，增加其潤滑性； 4）抽線：將酸洗後的盤元取出，放入抽線機冷拉至所需螺絲線徑； 5）成型：通過可動剪刀單向移動，將卡於剪模內的線材切成所需胚料，之後打模固定，一沖將產品頭部初步成型，當產品為一字割溝時，一沖模為內凹、橢圓槽，產品為十字槽時，一沖模為內凹四方槽，一沖之後，沖具整體運行，二沖模移向打模正前方，同時二沖模向前運行，將產品最終成型，之後由後沖棒將胚料推出，之後放入加熱設備將胚料需成型一端加熱至白熱狀態，7/8以下加熱10-12s，7/8-1加熱17-18s，將加熱後的胚料迅速移至成型機，通過後座，夾模固定，頭模衝擊胚料，加以成型，並於束杆機上利用擠壓將產品縮杆； 6）輾牙：將一塊牙板固定，另一塊活動牙板帶動產品移動，利用擠壓使產品產生塑性變形，形成所需螺紋； 7）熱處理：之後將成型螺絲在加熱到850℃左右在油中進行淬火，之後在400-500℃左右進行高溫回火，回火後迅速冷卻； 8）表面處理：最後將螺絲浸沒溫度約為550℃的溶化鋅的鍍槽內，使得螺絲表面上的鐵鋅合金漸漸變成產品外表面上的鈍化鋅，之後在200℃以下烘焙一天左右後，即取得最後的產品。 2.所述退火步驟中升溫至700℃所需5小時，並且從700℃降溫至500℃時所需4小時。 3.所述酸洗步驟中鹽酸的含量為26-30%。 | 常熟市華星精密鑄件有限公司 | 215500 江蘇省蘇州市常熟市新港鎮碧溪溪南村 | 常熟市華星精密鑄件有限公司 | - | - | - | B23P015/00 | B23P015/00 F16B035/00 C21D001/26 C21D001/18 C23G001/08 C23C002/06 | 5 | 5 | - | - | - | 姚幸誕 | 1 | 劉述生 | - | - | - | 0 | 0 | 11 | 4 | CN104439984A | 1 | 1 | - | CN104439984 | 2015-03-25 | 9 | 常熟市華星精密鑄件有限公司 | Pub. | ||||||||||||||||||||
30 | CN107470789 | A | 2017-12-15 | 用於製造纖維複合部件的鉚接部分的方法 | invention | CN201710418378.7 | 2017-06-06 | 本發明提供了一種用於製造纖維複合部件的鉚接部分的方法，其包括下述步驟：以與第二部件搭接的方式定位包含纖維複合材料的第一部件；鐳射鑽出至少穿過第一部件的纖維複合材料的共用的通孔；將鉚釘插入通孔中；以及將鉚釘固定在第一和第二部件上。本發明還提供鐳射鑽孔方法用於製造纖維複合部件的鉚接部分的用途、包括這種類型的鉚接部分的結構裝置、用於製造交通工具外殼的方法以及交通工具外殼。; | 1.一種用於製造纖維複合部件的鉚接部分(17)的方法，其包括下述步驟：以與第二部件(2；2’)搭接的方式來定位包含纖維複合材料的第一部件(1)；鐳射鑽出至少穿過第一部件(1)的纖維複合材料的共用的通孔(3)；將鉚釘(4)插入通孔(3)中；以及將鉚釘(4)固定在第一和第二部件(1,2；1,2’)上。 | 1.一種用於製造纖維複合部件的鉚接部分(17)的方法，其包括下述步驟：以與第二部件(2；2’)搭接的方式來定位包含纖維複合材料的第一部件(1)；鐳射鑽出至少穿過第一部件(1)的纖維複合材料的共用的通孔(3)；將鉚釘(4)插入通孔(3)中；以及將鉚釘(4)固定在第一和第二部件(1,2；1,2’)上。 2. 3. 4. 5. 6. 7.2’)的多個共用的通孔(3)通過鐳射鑽孔形成為沿第一部件(1)的邊緣(14)延伸的直線，鉚釘(4)被插入每個通孔(3)中並且被固定到第一和第二部件(1,2；1,2’)上以形成特別均勻的連續接合線(13)。 8. 9.一種結構裝置(16)，包括：第一部件(1)，其含有纖維複合材料；以及第二部件(2；2’)，第一和第二部件使用通過根據權利要求1至8中任一項所述的方法製造的鉚接部分(17)進行連接。 10. 11.一種用於製造交通工具外殼(20)的方法，所述交通工具外殼(20)特別是用於航空器或航天器的交通工具外殼(20)，所述方法包括下述步驟：提供第一部件(1)，其為包含纖維複合材料的第一外殼部(18)的形式；提供第二部件(2；2’)，其特別為第二外殼部(19)的形式或用於將第一外殼部(18)對接連接到第二外殼部(19)的連接部(2’)的形式；以及使用通過根據權利要求1至8中任一項所述的方法製造的鉚接部分(17)將第一部件(1)連接到第二部件(2；2’)。 12.一種交通工具外殼(20)，特別是航空器或航天器的外殼，其通過根據權利要求11所述的方法製造。 13.將鐳射鑽孔方法應用于製造纖維複合部件的鉚接部分(17)的用途，特別是通過根據權利要求1至8中任一項所述的方法來製造纖維複合材料的鉚接部分的用途。 14. | 空中客車運營有限公司 | DE | 德國漢堡 | 空中客車運營有限公司 | DE | - | - | - | B23K026/382 | B23K026/382 B23K026/402 B23K026/0622 B23K026/16 F16B019/04 B29C065/60 B29L031/30 | 4 | 4 | - | - | - | 102016210115.3 DE102016210115.3 002016000210115 DE002016000210115 | 2016-06-08 | DE | 保羅·約恩 彼得·林德 | 2 | DE | | 丁文蘊 張敬強 | - | - | 0 | 0 | 8 | 0 | US10427358 US20200023590 CN107470789A DE102016210115A1 | 4 | 3 | - | CN107470789 | 2017-12-15 | 12 | 空中客車運營有限公司 | Overdue | ||||||||||||||
31 | CN116123197 | A | 2023-05-16 | 一種優化低倍流線的螺栓及其製造方法 | invention | CN202211196156.2 | 2022-09-28 | 本發明屬於螺栓製造技術領域，公開了一種優化低倍流線的螺栓，螺栓毛坯經過切削加工後，從螺栓的中心縱向截面上看，頭部支撐面到螺栓杆部的低倍流線中，被切斷的低倍流線數量小於未被切斷的低倍流線數量。本發明通過減小低倍流線的切斷，可以顯著提高螺栓的抗疲勞性能，保持螺栓的低倍流線的對稱分佈，保證螺栓使用中受力分佈均勻對稱；本發明的螺栓產品特性強，結構穩定，可靠性高，使用壽命長，可以用於飛機的各大結構件如蒙皮連接中，保證在高載荷強度下的使用安全；從全新的維度提出了新的螺栓抗疲勞性能提升方法，可以與現有的加工、熱處理方式來疊加提升螺栓的強度。; | 1.一種優化低倍流線的螺栓，其特徵在於，螺栓毛坯經過切削加工後，從螺栓的中心縱向截面上看，頭部支撐面到螺栓杆部的低倍流線中，被切斷的低倍流線數量小於未被切斷的低倍流線數量。 | 1.一種優化低倍流線的螺栓，其特徵在於，螺栓毛坯經過切削加工後，從螺栓的中心縱向截面上看，頭部支撐面到螺栓杆部的低倍流線中，被切斷的低倍流線數量小於未被切斷的低倍流線數量。 2.其中，H是被切斷流線部位的尺寸，S是頭部支撐面寬度的尺寸。 3. 4. 5. 6. 7.一種優化低倍流線的螺栓的製造方法，用於製造如權利要求2-6所述的任意一種優化低倍流線的螺栓，其特徵在於，在同一批螺栓鍛件毛坯精加工前，取出任意一個螺栓鍛件毛坯，從其中心軸線所在任意平面進行切割，得到該螺栓鍛件毛坯的低倍流線斷面；通過觀察低倍流線斷面上的低倍流線，在加工螺栓頭部支撐面的進刀方向，確定進刀距離對螺栓頭部支撐面下R角處彎折的低倍流線的切斷影響；根據該影響制定最大進刀距離，該最大進刀距離所切斷的流線部位尺寸不大於螺栓頭部支撐面寬度的一半；最後以該最大進刀距離為限將螺栓鍛件毛坯精加工成螺栓。 8. | 陝西飛機工業有限責任公司 | CN | 723213 陝西省漢中市柳林鎮 | 陝西飛機工業有限責任公司 | CN | - | - | - | - | F16B035/00 | F16B035/00 B23D079/00 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 李佳甯 徐俊輝 軒曉楠 劉迎春 霍力剛 姬玉平 王文全 夏開陽 李永鵬 姚湘明 | 10 | - | | 鄧軻 貴州國防工業專利中心 52001 | 20230516 | - | - | - | - | 0 | - | 0 | - | 3 | 0 | CN116123197A | 1 | 1 | - | CN116123197 | 2023-05-16 | 17 | 陝西飛機工業有限責任公司 | Pub. | |||
32 | US10502254 | B2 | 2019-12-10 | Integral nut-retaining cradle for a nut plate assembly and methods of manufacturing using additive manufacturing | invention | 15/659685 | 2017-07-26 | Additively manufactured parts are disclosed comprising an integral additively manufactured nut plate cradle, and methods of their manufacture and use in part and component installation and to facilitate joining parts and components to larger structures. | 1. An additively manufactured part comprising: an additively manufactured nut-retaining cradle integral with the additive manufactured part, said integral nut-retaining cradle comprising an integral cradle bed and at least one integral cradle wall, said integral cradle wall extending substantially perpendicularly from the integral cradle bed and said integral cradle wall extending from the integral cradle bed to a predetermined distance; andwherein the integral cradle wall comprises at least one integral cradle wall nut-retaining feature, said integral cradle wall nut-retaining feature configured to receive a retainer, said retainer configured to engage the integral cradle wall nut-retaining feature, said integral cradle wall nut-retaining feature further configured to establish a restricted range of movement for a nut retained in the nut-retaining cradle along at least one axis. | 1. An additively manufactured part comprising: an additively manufactured nut-retaining cradle integral with the additive manufactured part, said integral nut-retaining cradle comprising an integral cradle bed and at least one integral cradle wall, said integral cradle wall extending substantially perpendicularly from the integral cradle bed and said integral cradle wall extending from the integral cradle bed to a predetermined distance; andwherein the integral cradle wall comprises at least one integral cradle wall nut-retaining feature, said integral cradle wall nut-retaining feature configured to receive a retainer, said retainer configured to engage the integral cradle wall nut-retaining feature, said integral cradle wall nut-retaining feature further configured to establish a restricted range of movement for a nut retained in the nut-retaining cradle along at least one axis. 2. The additively manufactured part according to claim 1, wherein the integral cradle wall nut-retaining feature comprises at least one recess in at least one integral cradle wall. 3. The additively manufactured part according to claim 2, wherein the recess extends through the integral cradle wall. 4. The additively manufactured part according to claim 2, wherein the recess comprises a through-slot extending through the integral cradle wall. 5. The additively manufactured part according to claim 1, wherein the retainer is selected from the group consisting of: a clip; a pin; a continuous ring; a discontinuous ring; and combinations thereof. 6. The additively manufactured part according to claim 1, wherein the nut comprises a floating nut. 7. The additively manufactured part according to claim 1, wherein the integral cradle bed comprises at least one integral cradle bed nut-orienting feature, said integral cradle bed nut-orienting feature configured to establish a restricted range of movement for a nut retained in the integral cradle bed along at least one axis. 8. The additively manufactured part of claim 7, wherein the integral cradle bed nut-orienting feature comprises a post, said post extending a predetermined distance from the integral cradle bed. 9. The additively manufactured part according to claim 1, wherein the integral cradle bed comprises: a cradle bed upper surface, said cradle bed comprising a predetermined thickness, andwherein the integral cradle bed upper surface extends a predetermined distance from a surface of the additively manufactured part. 10. The additively manufactured part according to claim 1, wherein the integral cradle bed comprises: a cradle bed upper surface; andwherein the integral cradle bed upper surface is substantially flush with a surface of the additively manufactured part. 11. The additively manufactured part according to claim 1, wherein the additively manufactured part comprises a non-metallic material, said non-metallic material selected from the group consisting of: a thermoset plastic material; a thermoplastic materi... | The Boeing Company | US | THE BOEING COMPANY | US | IL Chicago | THE BOEING COMPANY | US | 100 NORTH RIVERSIDE PLAZA | F16B037/04 | F16B037/04 B22F003/105 B22F007/06 B33Y080/00 B33Y010/00 B33Y070/00 B23K026/342 B23K015/00 B64F005/10 B62D027/02 B63B017/00 | 7 | 11 | - | F16B0037/044 | F16B0037/044 B22F0003/1055 B22F0007/062 B23K0015/0086 B23K0026/342 B33Y0010/00 B33Y0070/00 B33Y0080/00 B62D0027/02 B63B0017/00 B64F0005/10 F16B0037/04 | F16B0037/044 B22F0007/062 B22F0010/12 B22F0010/18 B22F0010/25 B22F0010/28 B23K0015/0086 B23K0026/342 B33Y0010/00 B33Y0070/00 B33Y0080/00 B62D0027/02 B63B0017/00 B64F0005/10 F16B0037/04 Y02P0010/25 | - | - | - | - | - | - | - | Paul Dufour Michael Hand Matthew Molitor | 3 | US | MO O'Fallon CA Huntington Beach MO O'Fallon | Coats & Bennett, PLLC | - | - | Roberta S Delisle | Roberta S Delisle | US4695212 US7114900 US7575404 US7591622 US7802952 US7823262 US7921539 US8383028 US8425772 US8883064 US9939005 US2012/0308332 US2014/0086704 | 13 | EP3045739 WO2007106801 WO2012166532 | 3 | European Search Report dated Dec. 18, 2012 in re Application No. EP 18 174 340.2-1010. | 8 | 2 | EP3434916B1 CN109306993B JP7278038 US10502254 | 4 | 4 | - | US20190032697 | 2019-01-31 | 12 | THE BOEING COMPANY | Valid | ||||
33 | CN118854130 | A | 2024-10-29 | 一種高強度鋁合金鉚釘及其製備方法 | invention | CN202410853455.1 | 2024-06-28 | 本申請涉及鉚釘生產加工領域，公開了一種高強度鋁合金鉚釘，所述鉚釘由以下重量百分比的合金組成：鎂1.0％‑2.0％、鋅2.0％‑3.0％、銅1.5％‑2.5％、稀土元素0.1％‑0.5％、餘量為鋁及不可避免的雜質。本發明通過使用特定比例的鋁、鎂、鋅、銅及稀土元素的混合，實現了提高鉚釘的機械性能，達到了適用于高負載環境的技術目的。這種合金配置使得鉚釘具有更高的強度和韌性，適合在航空航太等要求嚴苛的工業領域使用，通過引入多階段冷鐓成形過程，實現了對鉚釘形狀和尺寸的精確控制，達到了提高產品一致性和減少製造缺陷的技術目的。多階段冷鐓不僅優化了鉚釘的微觀結構，還提高了生產效率，確保每個鉚釘都達到嚴格的工業標準。; | 1.一種高強度鋁合金鉚釘，其特徵在於，所述鉚釘由以下重量百分比的合金組成：鎂1.0％-2.0％、鋅2.0％-3.0％、銅1.5％-2.5％、稀土元素0.1％-0.5％、餘量為鋁及不可避免的雜質。 | 1.一種高強度鋁合金鉚釘，其特徵在於，所述鉚釘由以下重量百分比的合金組成：鎂1.0％-2.0％、鋅2.0％-3.0％、銅1.5％-2.5％、稀土元素0.1％-0.5％、餘量為鋁及不可避免的雜質。 2. 3. 4.a)合金熔煉：將鎂、鋅、銅和稀土元素與鋁在熔爐中混合並熔化，控制熔煉溫度在750℃至850℃；b)鑄造成型：將熔融合金在預熱至250℃的模具中澆鑄成坯料；c)冷鐓成形：將坯料在室溫下通過多道次冷鐓過程成形為鉚釘；d)熱處理：包括快速固溶處理和時效硬化，其中快速固溶處理在560℃進行不超過30秒，緊接著快速冷卻；時效硬化在200℃進行4小時。 5.第一階段：預成形，將鑄造好的坯料初步壓制成預定的粗略形狀，此階段主要消除鑄件的毛刺和不規則表面，準備坯料進行精密冷鐓；第二階段：精密成形，利用精確設計的模具進一步塑形鉚釘的詳細特徵，包括頭部和尾部；第三階段：細化和修整，對鉚釘的最終形狀進行精細調整和平滑處理，包括去除任何微小缺陷。 6.鉚釘均勻排列在輸送帶上，輸送帶緩慢通過爐內，確保每個鉚釘都能均勻加熱至560℃。加熱時間控制在30秒內，以避免合金成分過度氧化或晶粒粗化。 7.1，按總體積的5％至10％的比例與去離子水混合。 8.機械拋光：使用精細砂紙和拋光膏對鉚釘表面進行拋光，以消除表面的微小劃痕和不平整；清洗步驟：採用超聲波清洗機和適當去離子水徹底清潔鉚釘，去除拋光過程中產生的雜質和殘留物，確保鉚釘表面的潔淨和無污染。 | 無錫安士達五金有限公司 | CN | 214199 江蘇省無錫市錫山區東港鎮港東村 | 無錫安士達五金有限公司 | CN | - | - | - | - | C22C021/10 | C22C021/10 C22C021/18 C22C001/02 C22F001/053 C22F001/057 F16B019/04 B23P015/00 B21J005/00 B08B003/12 B24B029/02 | 7 | 8 | - | - | - | - | - | - | - | - | - | - | - | 繆建國 邱曉東 | 2 | - | | 饒思佳 無錫風創智慧財產權代理事務所(特殊普通合夥) 32461 | 20241029 | - | - | - | - | 0 | - | 0 | - | 1 | 0 | CN118854130A | 1 | 1 | - | CN118854130 | 2024-10-29 | 19 | 無錫安士達五金有限公司 | Pub. | |||
34 | US10520002 | B2 | 2019-12-31 | Barrel nut with stress reduction features | invention | 15/671513 | 2017-08-08 | A barrel nut with features for reducing tensile stresses under heavy load within the barrel nut has a partial-cylindrical body having a first planar end surface and a second planar end surface. A threaded bore extends through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface. At least one groove is formed in each of the first planar end surface and the second planar end surface, the groove having a rounded surface extending at least a part of a distance between a curved upper surface of the partial-cylindrical body to a bottom surface thereof in a direction substantially parallel to the central axis of the threaded bore. | 1. A method of reducing stress in a barrel nut comprising: forming a one-piece partial-cylindrical body having a first planar end surface and a second planar end surface;forming a threaded bore through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface; andforming at least one groove recessed into each of the first planar end surface and the second planar end surface extending at least a part of a length of the partial-cylindrical body in a direction substantially parallel to the central axis of the threaded bore. | 1. A method of reducing stress in a barrel nut comprising: forming a one-piece partial-cylindrical body having a first planar end surface and a second planar end surface;forming a threaded bore through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface; andforming at least one groove recessed into each of the first planar end surface and the second planar end surface extending at least a part of a length of the partial-cylindrical body in a direction substantially parallel to the central axis of the threaded bore. 2. The method of claim 1, further comprising forming the at least one recessed groove to have a rounded surface. 3. The method of claim 2, wherein the rounded surface has a radius in the range of about 0.015 to 0.15 times a diameter of the barrel nut. 4. The method of claim 1, further comprising aligning the at least one recessed groove in each of the first planar end surface and the second planar end surface with the central axis of the threaded bore such that the at least one recessed groove is positioned on a center line in each of the first planar end surface and the second planar end surface. 5. The method of claim 1, further comprising forming two grooves in each of the first planar end surface and the second planar end surface to extend in a direction substantially parallel to the central axis from a curved upper surface to a bottom surface of the partial-cylindrical body. 6. The method of claim 5, further comprising positioning the two grooves equidistant from a center line of each of the first planar end surface and the second planar end surface, the center line being aligned with the central axis. 7. The method of claim 6, wherein a distance between a center line of each of the two grooves is in a range of about 0.25 to 0.5 times a diameter of the barrel nut. 8. The method of claim 1, further comprising forming in a bottom surface of the partial-cylindrical body a flange surrounding the threaded bore, the flange being raised above the bottom surface and extending from a circumferential edge of the threaded bore to a side edge of the bottom surface. 9. The method of claim 8, wherein the flange at the side edge extends a curved upper surface of the partial-cylindrical body below the bottom surface in a central area, the central area having a length substantially equal to a diameter of the threaded bore. 10. A method of mounting an aircraft engine to an aircraft, comprising the steps of: inserting a barrel nut into a cylindrical bore extending through an aircraft engine mount, the barrel nut comprising a one-piece partial-cylindrical body having a first planar end surface and a second planar end surface, a threaded bore extending through the partial-cylindrical body and at least one groove recessed into each of the first planar end surface and the second planar end surface extending at least a part of a distance between a curved upper ... | The Boeing Company | US | The Boeing Company | US | IL Chicago | THE BOEING COMPANY | US | 100 N. RIVERSIDE | F16B031/06 | F16B031/06 F16B037/04 B23G009/00 | 2 | 3 | - | F16B0031/06 | F16B0031/06 B23G0009/006 F16B0037/047 | F16B0031/06 B23G0009/006 F16B0037/047 | - | - | - | - | - | - | - | Adrian Stanescu Constantine Kostakis Michael Ronald Butcher | 3 | US | WA Maple Valley WA Kirkland WA Issaquah | Ostrager Chong Flaherty & Broitman PC | - | - | John C Hong | John C Hong | US3021162 US2688355 US3208496 US3205927 US3322177 US4119130 US4861207 US4886407 US5779412 US8142123 US2010/0244342 | 11 | - | 0 | Examination Report No. 1 for standard patent application No. 2015202597, Australian Government, IP Australia, dated Jul. 31, 2018.;Printouts from http://www.shur-lok.com/ and http://www.shur-lok.com/solutions/barrel/... showing barrel nuts, printed Jun. 26, 2014.;Printouts from http://www.theharwarehut.com/catalog-product-specs.php?p_ref=302759, showing Selby 3/4″ Steel Barrel Nut, printed Jun. 26, 2014.;Search Report dated Jun. 2, 2016 in related Canadian Patent Application No. 2,892,721.;Examination Report from the Patent Office of the Cooperation Council for the Arab States of the Gulf, in related application No. GC 2015-29928, dated Jan. 28, 2019. | 8 | 0 | US10520002 US09759251 AU2015202597B2 RU2015117927A3 RU2678886C2 AU2015202597A1 CA2892723A1 RU2015117927A BR102015018911B1 BR102015018911A2 CA2892723C | 11 | 5 | - | US20170363132 | 2017-12-21 | 12 | THE BOEING COMPANY | Valid | ||||
35 | US11241728 | B2 | 2022-02-08 | Method of riveting | invention | 16/507249 | 2019-07-10 | A method of inserting a rivet into a workpiece comprises moving the rivet and workpiece relative to one another, along a longitudinal axis of the rivet, so as to drive the rivet into the workpiece. The rivet is rotated about its longitudinal axis, relative to the workpiece, for at least part of the time during which it is in contact with the workpiece. The speed of said rotation, or the speed of movement along the longitudinal axis of the rivet, is altered at least once before driving of the rivet into the workpiece is complete. One axial end of the rivet has a tip for piercing the workpiece, and the rivet has a substantially cylindrical shank extending longitudinally from the tip. The shank has one or more surface irregularities. | 1. A method of inserting a rivet into a workpiece, the method comprising moving the rivet and workpiece relative to one another, along a longitudinal axis of the rivet, so as to drive the rivet into the workpiece, wherein: the rivet is rotated about a longitudinal axis of the rivet, relative to the workpiece, for at least part of the time during which the rivet is in contact with the workpiece;the speed of said rotation, or the speed of movement along the longitudinal axis of the rivet, is altered at least once before driving of the rivet into the workpiece is complete; andthe workpiece comprises a layer made of magnesium, aircraft aluminium, ultra-high strength steel, titanium, or metal matrix composite,wherein after driving the rivet into the workpiece is complete, a body of the rivet abuts the workpiece. | 1. A method of inserting a rivet into a workpiece, the method comprising moving the rivet and workpiece relative to one another, along a longitudinal axis of the rivet, so as to drive the rivet into the workpiece, wherein: the rivet is rotated about a longitudinal axis of the rivet, relative to the workpiece, for at least part of the time during which the rivet is in contact with the workpiece;the speed of said rotation, or the speed of movement along the longitudinal axis of the rivet, is altered at least once before driving of the rivet into the workpiece is complete; andthe workpiece comprises a layer made of magnesium, aircraft aluminium, ultra-high strength steel, titanium, or metal matrix composite,wherein after driving the rivet into the workpiece is complete, a body of the rivet abuts the workpiece. 2. The method according to claim 1 wherein the workpiece comprises a further layer, made from magnesium, aircraft aluminium, ultra-high strength steel, titanium, metal matrix composite, carbon fibre composite or a polymer. 3. The method according to claim 2 wherein the workpiece comprises an additional layer made from standard grade steel or forming grade aluminium, and the rivet is inserted into the workpiece whereby the additional layer is a final layer contacted by the rivet. 4. The method according to claim 1 wherein the workpiece comprises an additional layer made from standard grade steel or forming grade aluminium, and the rivet is inserted into the workpiece whereby the additional layer is a final layer contacted by the rivet. 5. The method according to claim 1, wherein the rivet is made from aluminium, stainless steel, titanium or a ceramic. 6. The method according to claim 1, wherein: the rivet is rotated about the longitudinal axis of the rivet, relative to the workpiece, by a riveting tool; andthe riveting tool drives the rivet to rotate though one or more rotary drive components in frictional engagement with the rivet. 7. The method according to claim 6 wherein the riveting tool comprises a tool nose and a punch reciprocally disposed therein, the punch providing axial force to the rivet so as to drive the rivet into the workpiece. 8. The method according to claim 7 wherein one of said rotary drive components is the punch. 9. The method according to claim 8 wherein one of said rotary drive components is the tool nose. 10. The method according to claim 9 wherein the riveting tool comprises a pressure surface which is rotatably mounted to the nose, the pressure surface contacting the workpiece during insertion of the rivet and rotating relative to the nose for at least part of the time the rivet is in contact with the workpiece. 11. The method according to claim 7 wherein one of said rotary drive components is the tool nose. 12. The method according to claim 11 wherein the riveting tool comprises a pressure surface which is rotatably mounted to the nose, the pressure surface contacting the workpiece during insertion of the... | ATLAS COPCO IAS UK LIMITED | GB | Atlas Copco IAS UK Limited | GB | Flintshire Wales | ATLAS COPCO IAS UK LIMITED | GB | PARKWAY ONE, PARKWAY, ZONE 2, DEESIDE INDUSTRIAL PARK | B21J015/26 | B21J015/26 B21D039/03 B21J015/02 B23K020/12 B23K020/227 F16B005/08 F16H025/20 H02K041/02 B21J015/10 B23K103/08 B23K103/18 B23K103/10 B23K103/16 B23K103/20 B23K103/00 B23K103/04 B23K026/352 B23K020/233 B23K020/24 B23P019/06 B23K103/24 B23K103/14 B23K101/00 | 7 | 10 | - | B21J0015/26 | B21J0015/26 B21D0039/03 B21J0015/025 B21J0015/027 B23K0020/127 B23K0020/1265 B23K0020/227 B23K0020/2333 B23K0020/24 B23K0026/352 B23P0019/062 F16B0005/08 F16H0025/2025 H02K0041/02 B21J0015/10 B23K2101/006 B23K2103/04 B23K2103/05 B23K2103/10 B23K2103/14 B23K2103/15 B23K2103/16 B23K2103/172 B23K2103/18 B23K2103/20 B23K2103/24 B23K2103/34 B23K2103/42 Y10T0029/4984 | - | - | - | - | - | 1400725 1400734 1400736 1400761 | 2014-01-16 | GB | Stuart Edmund Blacket Wojciech Gostylla Paul Briskham | 3 | AU GB | Queensland Queensland Coventry | Michael Best & Friedrich LLP | - | - | Sarang Afzali | Sarang Afzali Darrell C Ford | US1404126 US2743623 US3127044 US4218953 US4756072 US4762261 US5183357 US5256017 US5354160 US5752305 US5829115 US6179192 US6234034 US6988862 US7032296 US7322783 US8302273 US8413532 US8549723 US10173370 US10406592 US2001/0003859 US2002/0125297 US2002/0166221 US2003/0029903 US2003/0051332 US2003/0154588 US2004/0096295 US2004/0118900 US2007/0034662 US2007/0187469 US2008/0056842 US2008/0093420 US2010/0088880 US2011/0164945 US2011/0304231 US2012/0167366 US2013/0273312 US2014/0222011 US2015/0328676 US2018/0117666 US2018/0161850 US2018/0375447 US2019/0039119 US2019/0039168 | 45 | CN1078672 CN101433935 CN201246383 CN101451599 CN101468421 CN101537252 CN101817142 CN101829903 CN102686329 CN202481711 CN103228375 CN103240564 CN103260790 CN203253869 CN103990756 DE19743277 DE102004015568 DE102010046318 FR993420 JPS594981 JPH01254342 JP2002174219 JP2002229639 JP2002364617 JP2005291382 JP2006043769 JP4517362 JP5055104 JP2013148122 KR102004090612 KR1020110036624 KR1020110131826 KR1020130070362 KR1020130134180 KR1020130140711 WO2009137868 WOWO9414554 | 37 | Lathabai et al, “Friction spot joining of an extruded Al—Mg—Si alloy,” journal (2006) pp. 899-902 Science Direct, www.actamat-journals.com.;PCT/GB2015/050085 International Search Report dated Apr. 8, 2015 (6 pages).;PCT/GB2015/050084 International Search Report dated Apr. 20, 2015 (5 pages).;PCT/GB2015/050083 International Search Report and Written Opinion dated Mar. 27, 2015 (12 pages).;PCT/GB2015/050082 International Search Report and Written Opinion dated Jun. 9, 2015 (17 pages).;Office Action from the Korean Intellectual Property Office for Application No. 10-2016-7021078 dated Jul. 10, 2017 (5 pages).;First Office Action from the State Intellectual Property Office of China for Application No. 10-2016-7021130 dated Jul. 18, 2017 (3 pages).;First Office Action from the State Intellectual Property Office of China for Application No. 10-2016-7021353 dated Jul. 18, 2017 (15 pages).;Chinese First Office action for Application No. 20150004824.9 dated Sep. 29, 2017 (8 pages English translation included).;Chinese First Office action for Application No. 201580013385.8 dated Oct. 30, 2017 (21 pages English translation included). | 6 | 1 | EP3094443B1 US11241728 EP3094430B1 EP3094428B1 JP6805376 US10751790 US10751789 KR1021351200000 JP6715184 JP6712954 US10610921 CN105916625B JP6687537 KR1020721710000 JP6588925 US10406592 CN106413937B CN105916612B KR1018603340000 KR1018603320000 KR1018343200000 EP3094427A1 CN106102956A WO2015107352 WO2015107351 WO2015107353 WO2015107350 | 27 | 6 | - | US20190344329 | 2019-11-14 | 14 | ATLAS COPCO IAS UK LIMITED | Valid | ||||
36 | US07818862 | B2 | 2010-10-26 | Unitary nut and washer and method | invention | 11/593979 | 2006-11-06 | Embodiments of the present invention provide a unitary axle nut and tang washer assembly suitable for use in an aircraft landing gear wheel and brake structure. The assembly includes an axle nut in communication with a tang washer having a retainer wire groove formed therebetween; and a retainer wire held in the retainer wire groove. | 1. A method for improving in-service aircraft landing gear maintenance comprising the steps of: providing a nut and a washer;forming an axial overlap between the nut and washer;forming a first groove portion in the nut;forming a second groove portion in the washer;positioning the first groove portion adjacent the second groove portion to form a unitary groove enclosed by the axial overlap;positioning one or more objects in the groove to hold the nut and the washer together and permit relative rotational movement thereof; andinstalling or removing the nut and washer as a single unit. | 1. A method for improving in-service aircraft landing gear maintenance comprising the steps of: providing a nut and a washer;forming an axial overlap between the nut and washer;forming a first groove portion in the nut;forming a second groove portion in the washer;positioning the first groove portion adjacent the second groove portion to form a unitary groove enclosed by the axial overlap;positioning one or more objects in the groove to hold the nut and the washer together and permit relative rotational movement thereof; andinstalling or removing the nut and washer as a single unit. 2. The method of claim 1, further comprising the steps of: preventing axial motion of the nut relative to the washer; andpermitting rotational motion of the nut relative to the washer. 3. The method of claim 1, wherein the one or more objects are selected from the group comprising: a wire;two or more pins; andtwo or more screws. 4. The method of claim 3, further comprising the steps of: forming a slot in at least one of the nut and washer; andfeeding the wire into the groove through the slot. 5. The method of claim 4, further comprising the steps of: cutting the wire to form a second end; andpassing the second end through the slot and into the groove. 6. The method of claim 1, further comprising the step of: fixing the one or more of the objects to one of the nut and washer such that the one or more of the objects extend into the groove. 7. A method for improving in-service aircraft landing gear maintenance comprising the steps of: providing an axle nut and tang washer;forming a groove in at least one of the axle nut and tang washer;forming a hole in at least one of the axle nut and tang washer;forming a slot in at least one of the axle nut and tang washer;feeding a wire into the groove through the slot;inserting an end of the wire into the hole;rotating the axle nut relative to the tang washer;pulling the wire through the slot and into the groove; andinstalling or removing the axle nut and tang washer as a single unit. 8. A method for improving in-service aircraft landing gear maintenance comprising the steps of: providing an axle nut and tang washer;forming a groove in at least one of the axle nut and tang washer;positioning a wire in the groove to hold the axle nut and tang washer together;bending a first end of the wire forming a bent end;inserting the bent end into a hole formed in one of the axle nut and tang washer;rotating the axle nut relative to the tang washer to pull the wire into the groove; andinstalling or removing the axle nut and tang washer as a single unit. 9. A method for installing a nut and washer on an axle of an aircraft landing gear, the method comprising the steps of: providing an axle nut and tang washer assembly;forming an axial overlap between the axle nut and the tang washer;positioning an object in a groove enclosed by the axial overlap between the axle nut and tang washer to prevent axial motion of the axle nut relative to the t... | Steven Thomas Arany-Kovacs | US | The Boeing Company | US | IL Chicago | THE BOEING COMPANY | US | M/C 1640-2101, 15460 LAGUNA CANYON ROAD | B23P019/04 | B23P019/04 F16B043/00 | 2 | 2 | F16B0041/002 F16B0037/00 F16B0021/16 Y10T0029/49721 Y10T0029/49815 Y10T0029/49904 | 029/402.030 | 029/402.030 029/426.100 029/469.000 411/533.000 411/337.000 | - | - | Steven Thomas Arany-Kovacs | 1 | US | WA Monroe | - | - | - | Essama Omgba | Essama Omgba | US2529343 US2679880 US3181584 US3659491 US3973611 US4031936 US4900209 US5507517 US6554552 US6976817 US7437976 US2004/0175252 US2004/0234358 US2007/0128003 | 14 | 0 | 19 | 2 | US07818862 | 1 | 1 | - | US20080107498 | 2008-05-08 | 1 | THE BOEING COMPANY | Overdue | ||||||||||||
37 | CN106414038 | A | 2017-02-15 | 複合鉚釘坯件和所述複合鉚釘坯件的安裝 | invention | CN201580012582.8 | 2015-03-06 | 本發明公開複合緊固件、相關聯坯件以及用於此類緊固件的安裝的方法和設備。所公開的示例性複合鉚釘(10)包括細長主體，所述細長主體包括編結增強纖維(14)，所述編結增強纖維嵌入所述主體內側並且支撐在基質材料(16)中。本發明還公開結構元件，所述結構元件包括複合緊固件和麵板或其他零件，所述其他零件包括複合材料和/或其他材料。; | 1.一種複合鉚釘坯件，其包括：細長主體，其具有軸線和沿所述軸線的長度，所述主體包括編結增強纖維，所述編結增強纖維嵌入所述主體內側並且支撐在基質材料中。 | 1.一種複合鉚釘坯件，其包括：細長主體，其具有軸線和沿所述軸線的長度，所述主體包括編結增強纖維，所述編結增強纖維嵌入所述主體內側並且支撐在基質材料中。 2.如權利要求1所述的坯件，其中所述編結增強纖維延伸所述主體的所述長度。 3.如權利要求1和2中任一項所述的坯件，其中所述主體沿其長度具有大致上均勻的橫向橫截面。 4.如權利要求1至3中任一項所述的坯件，其中所述基質材料包括熱塑性塑膠。 5.如權利要求1至4中任一項所述的坯件，其中所述基質材料包括以下各項中的任一個：尼龍、聚醚醯亞胺(PEI)、聚醚碸(PES)、聚苯硫醚(PPS)、聚醚醚酮(PEEK)和聚醚酮酮(PEKK)。 6.如權利要求1至5中任一項所述的坯件，其中所述纖維包括碳。 7.如權利要求1至6中任一項所述的坯件，其中所述纖維包括玻璃。 8.如權利要求1至7中任一項所述的坯件，其中所述纖維中的至少一些以從所述主體的所述軸線的介於15度與30度之間的傾斜角定向。 9.如權利要求1至7中任一項所述的坯件，其中所述纖維中的至少一些以約20度的傾斜角定向。 10.如權利要求1至9中任一項所述的坯件，其中所述主體中的增強纖維的體積分數在55％與63％之間。 11.如權利要求1至9中任一項所述的坯件，其中所述主體中的增強纖維的所述體積分數是約60％。 12.如權利要求1至11中任一項所述的坯件，其中所述主體包括拉擠杆和壓縮模制杆中的一個。 13.如權利要求1至12中任一項所述的坯件，其中所述纖維以雙軸編結佈置。 14.一種複合緊固件坯件，其包括：細長主體，其具有縱軸和沿所述軸線的長度，所述主體沿其長度具有大致上均勻的橫向橫截面，所述主體包括連續增強纖維，所述連續增強纖維嵌入所述主體內側並且延伸所述主體的所述長度，所述增強纖維支撐在基質材料中並且所述增強纖維在所述主體的所述長度內的至少部分在不平行於所述主體的所述軸線的方向上延伸。 15.如權利要求14所述的坯件，其中所述基質材料包括熱塑性塑膠。 16.如權利要求14和15中任一項所述的坯件，其中所述基質材料包括以下各項中的任一個：尼龍、聚醚醯亞胺(PEI)、聚醚碸(PES)、聚苯硫醚(PPS)、聚醚醚酮(PEEK)和聚醚酮酮(PEKK)。 17.如權利要求14至16中任一項所述的坯件，其中所述纖維包括碳。 18.如權利要求14至17中任一項所述的坯件，其中所述纖維包括玻璃。 19.如權利要求14至18中任一項所述的坯件，其中所述纖維是編結的。 20.如權利要求14至19中任一項所述的坯件，其中所述纖維以雙軸編結佈置。 21.如權利要求14至20中任一項所述的坯件，其中所述纖維中的至少一些以從所述主體的所述縱軸的介於15度與30度之間的傾斜角定向。 22.如權利要求14至20中任一項所述的坯件，其中所述纖維中的至少一些以約20度的傾斜角定向。 23.如權利要求14至22中任一項所述的坯件，其中所述主體中的增強纖維的所述體積分數在55％與63％之間。 24.如權利要求14至23中任一項所述的坯件，其中所述主體中的增強纖維的所述體積分數是約60％。 25.如權利要求14至24中任一項所述的坯件，其中所述主體包括拉擠杆和壓縮模制杆中的一個。 26.一種複合結構元件，其包括：第一零件，其中形成有第一孔洞；第二零件，其中形成有第二孔洞，所述第一零件和所述第二零件相對於彼此定位，使得所述第一孔洞至少部分地與所述第二孔洞對準；以及複合鉚釘，其通過所述第一孔洞和所述第二孔洞將所述第一零件和所述第二零件固定在一起，所述複合鉚釘包括主體，所述主體具有編結增強纖維，所述編結增強纖維嵌入所述主體內側並且支撐在基質材料中。 27.如權利要求26所述的元件，其中所述鉚釘包括與所述第一零件接合的第一精加工末端和與所述第二零件接合的第二精加工末端，所述精加工末端中的至少一個包括纖維錨定人工製品，所述纖維錨定人工製品用來在所述精加工末端中的所述至少一個的熱成型期間至少部分地控制所述纖維的變形。 28.如權利要求26和27中任一項所述的組件，其中所述基質材料包括熱塑性塑膠。 29.如權利要求26至28中任一項所述的組件，其中所述纖維包括碳。 30.如權利要求26至29中任一項所述的組件，其中所述纖維包括玻璃。 31.如權利要求26至30中任一項所述的組件，其中所述纖維以雙軸編結佈置。 32.一種複合結構元件，其包括：第一零件，其中形成有第一孔洞；第二零件，其中形成有第二孔洞，所述第一零件和所述第二零件相對於彼此定位，使得所述第一孔洞至少部分地與所述第二孔洞對準；以及複合鉚釘，其通過所述第一孔洞和所述第二孔洞將所述第一零件和所述第二零件固定在一起，所述複合鉚釘包括如權利要求1至25中任一項所述的坯件，所述坯件具有與所述第一零件接合的第一精加工末端和與所述第二零件接合的第二精加工末端。 33.一種飛機，其包括如權利要求26至32中任一項所述的結構元件。 34.一種複合鉚釘，其包括：主體，其具有編結增強纖維，所述編結增強纖維嵌入所述主體內側並且支撐在基質材料中，所述主體包括用於接合第一零件的第一精加工末端和用於接合第二零件的第二精加工末端。 35.如權利要求34所述的鉚釘，其中所述精加工末端中的至少一個包括纖維錨定人工製品，所述纖維錨定人工製品用來在所述精加工末端中的所述至少一個的精加工期間至少部分地控制所述纖維的變形。 36.如權利要求34和35中任一項所述的鉚釘，其中所述基質材料包括熱塑性塑膠。 37.如權利要求34至36中任一項所述的鉚釘，其中所述纖維包括碳。 38.如權利要求34至37中任一項所述的鉚釘，其中所述纖維包括玻璃。 39.如權利要求34至38中任一項所述的鉚釘，其中所述纖維以雙軸編結佈置。 40.一種用於安裝複合鉚釘的方法，所述方法包括：將複合鉚釘坯件插入零件中的孔洞中；在所述坯件插入所述孔洞中之後：通過熱成型所述坯件的第一末端來精加工所述坯件的所述第一末端；以及通過熱成型所述坯件的第二末端來精加工所述坯件的與所述第一末端相對的所述第二末端。 41.如權利要求40所述的方法，其中精加工所述坯件的所述第一末端包括錨定所述坯件的所述第一末端的部分，以至少部分地控制嵌入所述坯件內側的增強纖維的變形。 42.如權利要求41所述的方法，其中精加工所述坯件的所述第二末端包括錨定所述坯件的所述第二末端的部分，以至少部分地控制嵌入所述坯件中的所述纖維的所述變形。 43.如權利要求40至42中任一項所述的方法，其包括在將所述坯件插入所述孔洞中之前，將所述坯件加熱到足以允許所述第一末端和所述第二末端的所述精加工的溫度。 44.如權利要求40至42中任一項所述的方法，其包括在將所述坯件插入所述孔洞中之後，將所述坯件加熱到足以允許所述第一末端和所述第二末端的所述精加工的溫度。 45.如權利要求40至44中任一項所述的方法，其中精加工所述第二末端包括使所述第二末端變形以填充所述零件中的埋頭孔，並且精加工所述第一末端包括屈曲所述第一末端。 46.一種用於安裝複合鉚釘的設備，所述設備包括：第一精加工構件，其被配置成定位在已插入有複合鉚釘坯件的零件的第一側... | 龐巴迪公司 | CA | 加拿大，魁北克省 | 龐巴迪公司 | CA | - | - | - | B29C065/60 | B29C065/60 F16B005/04 F16B019/06 B21J015/08 B21J015/36 B29C065/18 B29C065/78 | 3 | 4 | - | - | - | 002014000949449 US002014000949449 61/949,449 US61/949,449 | 2014-03-07 | US | 保羅·特魯多 路易士·拉伯奇勒貝爾 阿蘭·蘭德裡 迪迪爾·霍斯特 | 4 | CA | | 梁曉廣 關兆輝 | - | - | 0 | 0 | 10 | 2 | US10589468 US20200171758 CN106414038A EP3113932A1 WO2015132766 CA2940448A1 | 6 | 5 | - | CN106414038 | 2017-02-15 | 10 | 龐巴迪公司 | Overdue | ||||||||||||||
38 | CN114278661 | A | 2022-04-05 | 一種鎖緊型減震墊圈及其加工與試驗方法 | invention | CN202111599119.1 | 2021-12-24 | 本發明公開了飛機零部件加工技術領域的一種鎖緊型減震墊圈，包括呈環狀的墊圈本體，所述墊圈本體的內側向墊圈本體中心延伸設有墊圈內齒部，所述墊圈內齒部上傾斜設置的倒角部，所述墊圈內齒部設有多個且呈環形陣列設置，所述墊圈本體的外側設有折彎部，所述折彎部垂直於所述墊圈本體，所述折彎部的數量設有多個。本發明還公開了上述鎖緊型減震墊圈的加工方法，包括以下步驟：備料、線切割、數控車倒角、去毛刺、表面處理和檢驗尺寸外觀。本發明解決了現有的墊圈在使用過程中會產生開裂甚至斷裂的情況，且本發明的墊圈在裝配使用過程中鎖緊性能穩定減震效果明顯，能夠在行業內廣泛使用。; | 1.一種鎖緊型減震墊圈，其特徵在於：包括呈環狀的墊圈本體，所述墊圈本體的內側向墊圈本體中心延伸設有墊圈內齒部，所述墊圈內齒部上傾斜設置的倒角部，所述墊圈內齒部設有多個且呈環形陣列設置，所述墊圈本體的外側設有折彎部，所述折彎部垂直於所述墊圈本體，所述折彎部的數量設有多個。 | 1.一種鎖緊型減震墊圈，其特徵在於：包括呈環狀的墊圈本體，所述墊圈本體的內側向墊圈本體中心延伸設有墊圈內齒部，所述墊圈內齒部上傾斜設置的倒角部，所述墊圈內齒部設有多個且呈環形陣列設置，所述墊圈本體的外側設有折彎部，所述折彎部垂直於所述墊圈本體，所述折彎部的數量設有多個。 2.所述墊圈內齒部至少設有4個。 3.所述折彎部的數量為2且基於所述墊圈本體的中心對稱設置。 4.包括以下步驟：備料、線切割、數控車倒角、去毛刺、表面處理和檢驗尺寸外觀。 5.所述表面處理為在產品上塗覆十六醇。 6.包括以下步驟：S1準備試驗工裝，所述試驗工裝包括連接杆、齒輪、調整墊片、手柄、扭力鉗工裝、扭力扳手、台虎鉗、榔頭；S2組裝試驗工裝；S3將連接杆固定到台虎鉗上；S4將扭力鉗工裝與扭力扳手連接；S5採用扭力扳手扳擰扭力鉗工裝，試驗要求：扭力到達500N·M後鎖緊型減震墊圈的墊圈內齒部未斷裂；S6將鎖緊型減震墊圈通過榔頭錘擊手柄與鎖緊型減震墊圈的折彎部連接處的平面處，試驗要求：折彎部不產生開裂。 | 貴州精立航太科技有限公司 | CN | 563000 貴州省遵義市紅花崗區盈田工穀產業園33號樓 | 貴州精立航太科技有限公司 | CN | - | - | - | - | F16B043/00 | F16B043/00 F16F001/02 B23P015/00 | 3 | 3 | - | - | - | - | - | - | - | - | - | - | - | 穆仁強 王相波 張榮生 旦其江 李明燕 張廣 楊德鬆 楊林 葉江華 | 9 | - | | 蒲定國 重慶強大凱創專利代理事務所(普通合夥) 50217 | 20220405 | - | - | - | - | 0 | - | 0 | - | 4 | 0 | CN114278661A | 1 | 1 | - | CN114278661 | 2022-04-05 | 16 | 貴州精立航太科技有限公司 | Overdue | |||
39 | CN112823218 | A | 2021-05-18 | 變形鈦合金的高強度緊固件坯料及其製造方法 | invention | CN201880097056.X | 2018-08-31 | 本發明大體涉及有色冶金領域，即涉及具有用於製造飛行器緊固件的指定機械性能的鈦合金材料。由變形鈦合金製造用於高強度緊固件的坯料，該變形鈦合金以重量百分比計含有5.5至6.5的Al、3.0至4.5的V、1.0至2.0的Mo、0.3至1.5的Fe、0.3至1.5的Cr、0.05至0.5的Zr、0.15至0.3的O、最大0.05的N、最大0.08的C、最大0.25的Si、餘量的鈦和不可避免的雜質，其鋁結構當量值[Al]eq在7.5至9.5的範圍內且鉬結構當量值[Mo]eq在6.0至8.5的範圍內，其中當量由以下等式定義：[Al]eq＝[Al]+[O]×10+[Zr]/6；[Mo]eq＝[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5。用於高強度緊固件的坯料的製造方法包括熔融鈦合金鑄錠，在β和/或α‑β相場溫度下由鑄錠生產煆造的坯錠，在β和/或α‑β相場的加熱溫度下進行熱軋以生產圓坯料，隨後在550℃至705℃(1022°F至1300°F)的溫度下將軋材退火至少0.5小時，隨後拉制以生產直徑至多為10mm(0.394英寸)的線材，隨後在550℃至705℃(1022°F至1300°F)的溫度下退火至少0.5小時。技術結果是生產用於高強度緊固件的鈦合金坯料，其具有高極限拉伸強度和雙剪切強度，同時在退火條件下保持高水準的塑性性能。12項權利要求，5個附圖。; | 1.一種由變形鈦合金製成的高強度緊固件坯料，以重量百分比計，所述變形鈦合金由以下組成：5.5至6.5的Al、3.0至4.5的V、1.0至2.0的Mo、0.3至1.5的Fe、0.3至1.5的Cr、0.05至0.5的Zr、0.2至0.3的O、最大0.05的N、最大0.08的C、最大0.25的Si以及餘量的鈦和不可避免的雜質，其特徵在於鋁結構當量值[Al]eq在7.5至9.5的範圍內並且鉬結構當量值[Mo]eq在6.0至8.5的範圍內，其中所述當量值由以下等式定義：[Al]eq＝[Al]+[O]×10+[Zr]/6；[Mo]eq＝[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5。 | 1.一種由變形鈦合金製成的高強度緊固件坯料，以重量百分比計，所述變形鈦合金由以下組成：5.5至6.5的Al、3.0至4.5的V、1.0至2.0的Mo、0.3至1.5的Fe、0.3至1.5的Cr、0.05至0.5的Zr、0.2至0.3的O、最大0.05的N、最大0.08的C、最大0.25的Si以及餘量的鈦和不可避免的雜質，其特徵在於鋁結構當量值[Al]eq在7.5至9.5的範圍內並且鉬結構當量值[Mo]eq在6.0至8.5的範圍內，其中所述當量值由以下等式定義：[Al]eq＝[Al]+[O]×10+[Zr]/6；[Mo]eq＝[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5。 2.一種緊固件坯料，以直徑為8mm至31.75mm(0.315英寸至1.25英寸)的圓軋棒的形式製備。 3.一種緊固件坯料，以直徑超過31.75mm至101.6mm(1.25英寸至4.0英寸)的圓軋棒的形式製備。 4. 5. 6. 7. 8. 9. 10. 11.一種用於權利要求1、2、3、5、6、7、8所述的緊固件坯料的製造方法，所述方法包括熔融鈦合金鑄錠，以重量百分比計，所述鈦合金鑄錠由以下組成：5.5至6.5的Al、3.0至4.5的V、1.0至2.0的Mo、0.3至1.5的Fe、0.3至1.5的Cr、0.05至0.5的Zr、0.2至0.3的O、最大0.05的N、最大0.08的C、最大0.25的Si以及餘量的鈦和不可避免的雜質，其特徵在於鋁結構當量值[Al]eq在7.5至9.0的範圍內且鉬結構當量值[Mo]eq在6.0至8.5的範圍內，其中所述當量值由以下等式定義：[Al]eq＝[Al]+[O]×10+[Zr]/6；[Mo]eq＝[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5，在β和/或α-β相場溫度下將所述鑄錠轉化為鍛造的坯錠，對所述鍛造的坯錠進行機加工，在β和/或α-β相場的加熱溫度下熱軋以生產軋製坯料，隨後在550℃至705℃(1022°F至1300°F)的溫度下將所述軋製坯料退火至少0.5小時。 12.一種用於權利要求1、4、9、10所述的緊固件坯料的製造方法，所述方法包括熔融鈦合金鑄錠，以重量百分比計，所述鈦合金鑄錠由以下組成：5.5至6.5的Al、3.0至4.5的V、1.0至2.0的Mo、0.3至1.5的Fe、0.3至1.5的Cr、0.05至0.5的Zr、0.2至0.3的O、最大0.05的N、最大0.08的C、最大0.25的Si以及餘量的鈦和不可避免的雜質，其特徵在於鋁結構當量值[Al]eq在7.5至9.0的範圍內且鉬結構當量值[Mo]eq在6.0至8.5的範圍內，其中所述當量值由以下等式定義：[Al]eq＝[Al]+[O]×10+[Zr]/6；[Mo]eq＝[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5，在β和/或α-β相場溫度下將所述鑄錠轉化為鍛造的坯錠，對所述鍛造的坯錠進行機加工，在β和/或α-β相場的加熱溫度下進行熱軋以生產直徑為6.5mm至12mm(0.256英寸至0.472英寸)的軋製坯料，隨後在550℃至705℃(1022°F至1300°F)的溫度下將所述軋製坯料退火至少0.5小時，隨後拉制以生產直徑至多為10mm(0.394英寸)的線材，以及隨後在550℃至705℃(1022°F至1300°F)的溫度下退火至少0.5小時。 | 波音公司 威森波-阿維斯瑪股份公司 | US | 美國伊利諾斯州 | 波音公司 威森波-阿維斯瑪股份公司 | US | - | - | - | - | C22F001/18 | C22F001/18 C22C014/00 F16B033/00 | 3 | 3 | - | - | - | - | - | - | - | - | - | - | - | 娜特莉婭·格奧爾基耶夫納·米特羅波爾斯卡亞 邁克爾·奧特維奇·萊德爾 伊戈·尤利耶維奇·普紮科夫 阿列克謝·謝爾蓋耶維奇·紮伊采夫 娜塔莉亞·尤爾耶夫納·塔倫科瓦 羅伯特·大衛·伯裡格斯 | 6 | - | | 張曉影 北京康信智慧財產權代理有限責任公司 11240 | 20210518 | - | - | - | - | 0 | - | 0 | - | 7 | 0 | US11920218 JP7223121 EP3844316A1 CN112823218A WO2020046161 BR112021003069A2 CA3110188C CA3110188A1 BR112021003069B1 | 9 | 7 | - | CN112823218 | 2021-05-18 | 13 | THE BOEING COMPANY,威森波-阿維斯瑪股份公司 | Pub. | |||
40 | CN119260310 | A | 2025-01-07 | 一種航空用碳鋼桶形螺母的製造方法 | invention | CN202411331953.6 | 2024-09-24 | 本發明公開了一種航空用碳鋼桶形螺母的製造方法，包括以下步驟：機加成型，熱處理，磁力探傷，表面處理，性能試驗。本發明滿足所有性能以及尺寸要求,不會出現螺紋牙產生爛牙、牙形不規則。; | 1.一種航空用碳鋼桶形螺母的製造方法，包括以下步驟：1）機加成型：將四方尺寸、外圓、鎖絲孔、總長以及螺紋底孔、螺紋一起車銑加工成型，切斷後對切斷端進行鍃孔，去毛刺，在進行收口；2）熱處理：使用真空油淬爐進行淬火，油冷，真空回火爐回火，得到σb=1100MPa-1280Mpa強度的產品；3）磁力探傷：用磁力檢測對產品表面進行探傷，確保無影響產品的性能缺陷；4）表面處理：電鍍，鍍鎘鈍化，使產品表面與空氣隔絕，增加產品耐磨和耐腐蝕性；5）性能試驗：通過載荷試驗、硬度測試、扭矩-預緊力關係測試，疲勞強度測試，滿足產品設計標準需求，達到預期效果，產品製造結束。 | 1.一種航空用碳鋼桶形螺母的製造方法，包括以下步驟：1）機加成型：將四方尺寸、外圓、鎖絲孔、總長以及螺紋底孔、螺紋一起車銑加工成型，切斷後對切斷端進行鍃孔，去毛刺，在進行收口；2）熱處理：使用真空油淬爐進行淬火，油冷，真空回火爐回火，得到σb=1100MPa-1280Mpa強度的產品；3）磁力探傷：用磁力檢測對產品表面進行探傷，確保無影響產品的性能缺陷；4）表面處理：電鍍，鍍鎘鈍化，使產品表面與空氣隔絕，增加產品耐磨和耐腐蝕性；5）性能試驗：通過載荷試驗、硬度測試、扭矩-預緊力關係測試，疲勞強度測試，滿足產品設計標準需求，達到預期效果，產品製造結束。 2.如權利要求1所述的一種航空用碳鋼桶形螺母的製造方法，其中，步驟2）中所述的淬火溫度在850±10℃。 3.如權利要求1所述的一種航空用碳鋼桶形螺母的製造方法，其中，步驟2）中所述的真空回是在480-540±10℃下回火。 | 中國航空工業標準件製造有限責任公司 | CN | 550014 貴州省貴陽市白雲區白雲南路355號 | 中國航空工業標準件製造有限責任公司 | CN | - | - | - | - | B23P015/00 | B23P015/00 F16B037/00 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 林仕偉 李幹榮 賈淑妍 譚體偉 | 4 | - | | 盧俊 貴陽東聖專利商標事務有限公司 52002 | 20250107 | - | - | - | - | 0 | - | 0 | - | 1 | 0 | CN119260310A | 1 | 1 | - | CN119260310 | 2025-01-07 | 19 | 中國航空工業標準件製造有限責任公司 | Pub. | |||
41 | CN112322954 | A | 2021-02-05 | 飛機壁板裝配間隙補償形狀記憶合金墊片及其製備、裝配方法 | invention | CN202011207127.2 | 2020-11-03 | 本發明公開一種飛機壁板裝配間隙補償形狀記憶合金墊片，墊片的材料為添加有Ni、Ti、Nb元素的形狀記憶合金，且形狀記憶合金中Ni、Ti和Nb的原子比為a：b：c，其中a的取值範圍為48.5～50.5，b的取值範圍為46.5～48.5，c的取值範圍為3.5～5.5。如此設置，墊片具有較強的超彈性和形狀記憶效應，當溫度和預緊力發生變化時，可以做出反應，使得墊板表面始終與壁板結構件內表面完全貼合，保證間隙補償效果，提高連接的穩定性和可靠性。除此之外，當飛機服役時間壁板結構件的緊固螺栓出現鬆動時，導致壓緊力變小，壁板結構件之間間隙增大，由於墊片的形狀記憶效應，墊片的厚度會有一定的恢復，進一步提高壓緊力，起到防鬆效果，保證飛機服役過程中的安全性。; | 1.一種飛機壁板裝配間隙補償形狀記憶合金墊片，其特徵在於，所述墊片的材料為添加有Ni、Ti、Nb元素的形狀記憶合金，且所述形狀記憶合金中Ni、Ti和Nb的原子比為a：b：c，其中a的取值範圍為48.5～50.5，b的取值範圍為46.5～48.5，c的取值範圍為3.5～5.5。 | 1.一種飛機壁板裝配間隙補償形狀記憶合金墊片，其特徵在於，所述墊片的材料為添加有Ni、Ti、Nb元素的形狀記憶合金，且所述形狀記憶合金中Ni、Ti和Nb的原子比為a：b：c，其中a的取值範圍為48.5～50.5，b的取值範圍為46.5～48.5，c的取值範圍為3.5～5.5。 2.47：4。 3. 4.一種飛機壁板裝配間隙補償形狀記憶合金墊片的製備方法，其特徵在於，包括步驟：熔煉合金，按照權利要求1-3任一項所述的原子比將原材料進行熔煉；第一次退火，在900-926.85℃的溫度環境下，進行18小時以上的真空退火；第二次退火，在853.25-876.85℃下將合金製成板材，然後在853.25-876.85℃溫度環境下，進行45分鐘以上的真空退火；冷卻，將所述墊片冷卻2小時以上；表面處理，採用558-600細微性的砂紙對所述墊片進行表面拋光處理；防腐蝕處理，對所述墊片表面塗覆底漆；切割，將所述墊片進行分割。 5. 6. 7. 8.一種飛機壁板裝配間隙補償形狀記憶合金墊片的裝配方法，其特徵在於，準備如權利要求1-3任一項所述的飛機壁板裝配間隙補償形狀記憶合金墊片，使所述墊片的溫度處於馬氏體相變溫度範圍之間，並且在馬氏體相變溫度範圍內拉伸所述墊片至所述墊片厚度與裝配間隙相等，將所述墊片安裝於裝配間隙內，最後提高裝配溫度至奧氏體相變溫度。 | 西北工業大學 | CN | 710072 陝西省西安市友誼西路127號 | 西北工業大學 | CN | - | - | - | - | C22C030/00 | C22C030/00 C22C019/03 C22F001/10 C22F001/02 F16B043/00 B64F005/10 | 4 | 5 | - | - | - | - | - | - | - | - | - | - | - | 張開富 王原欣 程暉 駱彬 楊語 程立鑫 馮孟飛 | 7 | - | | 王富強 北京高沃律師事務所 11569 | 20210205 | - | - | - | - | 0 | - | 0 | - | 5 | 0 | CN112322954A | 1 | 1 | - | CN112322954 | 2021-02-05 | 15 | 西北工業大學 | Overdue | |||
42 | CN103194694 | A | 2013-07-10 | 鐵基形狀記憶合金防鬆螺栓及其製造、使用方法 | invention | CN201310086225.9 | 2013-03-18 | 本發明涉及一種鐵基形狀記憶合金防鬆螺栓及其製造、使用方法。其特徵在於：其品質百分比是：Mn：16.86%～17.23%；Si：4.50%～4.7%；Cr：2.23%～10.30%；Ni：2.26%～5.29%；C：≤0.08；除去雜質外其餘成分為Fe。由鐵基形狀記憶合金制車削好的螺栓杆進行1100℃×60min處理後進行單向拉伸；通過精確控制預緊力與普通螺母組合成螺紋副後進行進行加熱、保溫，冷卻：該階段是螺栓形狀記憶效應的實現階段：通過徑向軸向和馬氏體相變變形及恢復產生軸向徑向恢復力，實現防鬆。其防鬆效果大大高於普通螺栓，且該螺栓的防鬆摩擦力矩大於相同條件下鐵基形狀記憶合金防鬆螺母。本發明適用於拆裝困難、高速運動、機械內部不易檢查的場合，可以有效地解決鏈傳動、橋樑、航太航空設備中關鍵螺紋聯接的鬆動斷裂紋體。 | 1.一種鐵基形狀記憶合金防鬆螺栓，其特徵在於:按化學成份品質百分比的組成是: Mn:16.86% 〜17.23% ； S1:4.50% 〜4.7% ； Cr:2.23% 〜10.30% ； N1:2.26%5.29% ； C:≤ 0.08 除去雜質外其餘成分為Fe。 | 1.一種鐵基形狀記憶合金防鬆螺栓，其特徵在於:按化學成份品質百分比的組成是: Mn:16.86% 〜17.23% ； S1:4.50% 〜4.7% ； Cr:2.23% 〜10.30% ； N1:2.26%5.29% ； C:≤ 0.08 除去雜質外其餘成分為Fe。 2.一種鐵基形狀記憶合金防鬆螺栓的製造工藝，其特徵在於:步驟為:按權利要求1的化學成份品質百分比的組成要求選用熔煉材料，各組分按配比混合後，在氬氣保護下於真空中頻感應熔煉爐冶煉；待原料溶化並保溫30min使其均勻後，通過金屬模澆鑄成鑄錠；為了消除鑄錠成分的不均勻性，鑄錠經1200°C均勻化退火24小時後，車去表面氧化皮，切去帽口，再加熱到1100°C保溫I小時後熱鍛成圓形棒料；其熱鍛時的始鍛溫度為1050°C，終鍛溫度不低於900°C ;然後將圓形棒料通過形狀記憶訓練後車削成略大於標準尺寸的螺栓杆；並於材料試驗機上對該螺栓杆進行單向拉伸預變形，通過採用較低切削速度和使用滲透性、抗粘結性和散熱性好的切削液，將拉伸後的螺栓杆車削螺紋，實現制得鐵基形狀記憶合金螺栓(I)。 3.如權利要求1所述的鐵基形狀記憶合金防鬆螺栓的使用方法，其使用方法的特徵在於:將經過拉伸預變形處理後的鐵基形狀記憶合金螺栓(1)，按照預緊力矩，與普通螺母(2)組合成螺紋副；通過加熱爐將螺紋副加熱到350°C，並以大於5min時間進行保溫；通過鐵基形狀記憶合金螺栓(I)自身的形狀記憶功能，使鐵基形狀記憶合金螺栓發生的徑向、軸向和牙型的ε馬氏體相變變形及恢 複，進而產生軸向、徑向的恢復力，上述的恢復力均可以轉化為螺紋副之間的自鎖摩擦力矩，實現螺紋副的防鬆。 | 大連交通大學 | CN | 116028 遼寧省大連市沙河口區黃河路794號 | 大連交通大學 | CN | 遼寧 | - | - | - | C22C038/58 | C22C038/58 F16B039/02 | 2 | 2 | - | - | - | 劉林林 林成新 郭寶喜 | 3 | CN | 曹若材 李洪福 大連東方專利代理有限責任公司 21212 | - | - | 0 | 0 | 12 | 2 | CN103194694A | 1 | 1 | - | CN103194694 | 2013-07-10 | 8 | 大連交通大學 | Overdue | |||||||||||||||||
43 | CN103240381 | A | 2013-08-14 | 汽車飛機用單面鉚接方法及沉頭單面拉鉚釘 | invention | CN201310138095.9 | 2013-04-19 | 汽車飛機用單面鉚接方法及沉頭單面拉鉚釘。步驟：1由鉚釘、套環和鎖緊環組成的沉頭單面拉鉚釘。套環由有階梯內孔的圓筒和沉頭頭部組成。鉚釘由冒頭、階梯狀光杆、鎖緊槽、拉斷槽、光杆段、滾花段及尾部拉槽段組成。2組裝：套環套在鉚釘外，圓筒向前，沉頭頭部在後，鎖緊環裝在沉頭頭部和滾花段間。3將組裝後拉鉚釘插入安裝孔，尾部插入鉚接器；4鉚接器啟動，鉚釘向後拉，圓筒前端起鼓成盤狀，夾緊被連件。5鉚釘繼續向後，鎖緊環壓到鎖緊槽內。6拉斷槽斷裂，鉚接完成。採用上述單面鉚接、沉頭頭部、鎖緊環及階梯固緊，不僅可用于被連件一側空間窄小和實現表面無突出物，完全平整美觀；且保證拉脫、壓緊性能，可用在汽車和飛機上的特殊部位。 | 1.汽車飛機用單面鉚接方法，其特徵有如下步驟: 1)製作由套環、鉚釘和鎖緊環組成的如下沉頭單面拉鉚釘:套環由有階梯內孔的圓筒(2.1)和沉頭頭部(2.2)組成；鉚釘包括從前至後的順次連接的冒頭(1.1)、階梯狀光杆(1.2)、鎖緊槽(1.3)、拉斷槽(1.4)、光杆段(1.5)滾花段(1.6)及尾部拉槽段(1.7);鎖緊環採用開口圓環； 2)在被連件週邊空間組裝沉頭單面拉鉚釘:將套環從鉚釘後側套在鉚釘外周軸向置於冒頭和滾花段之間，套環圓筒置於前方，沉頭頭部置於後方，鎖緊環裝在沉頭頭部和滾花段前段徑向間； 3)將組裝好的拉鉚釘有冒頭的前端從被連件後側插入被連接件的安裝孔(4.1)伸到前側，鉚釘尾部拉槽段插入後側的鉚接器夾瓣(6.1)內； 4)鉚接器啟動，夾瓣夾緊尾部拉槽段，帶動鉚釘向後運動，鉚接器外套前端(6.2)相對鉚釘向前運動，向鎖緊環軸向施力，使帶階梯內孔的圓筒(2.1)塑性變形，圓筒前端頂在冒頭後端面受擠壓起鼓成盤狀(2.3)，貼在前被連件表面，夾緊兩被連件； 5)鉚釘繼續向後運動，鉚接器前端繼續擠壓鎖緊環向鎖緊槽移動，直到套環變形完成，鎖緊環完全被擠壓在鎖緊槽內； 6)鉚接器繼續拉動鉚釘向後移動，鉚釘在拉斷槽處斷裂，鉚接器拆除，完成鉚接。 | 1.汽車飛機用單面鉚接方法，其特徵有如下步驟: 1)製作由套環、鉚釘和鎖緊環組成的如下沉頭單面拉鉚釘:套環由有階梯內孔的圓筒(2.1)和沉頭頭部(2.2)組成；鉚釘包括從前至後的順次連接的冒頭(1.1)、階梯狀光杆(1.2)、鎖緊槽(1.3)、拉斷槽(1.4)、光杆段(1.5)滾花段(1.6)及尾部拉槽段(1.7);鎖緊環採用開口圓環； 2)在被連件週邊空間組裝沉頭單面拉鉚釘:將套環從鉚釘後側套在鉚釘外周軸向置於冒頭和滾花段之間，套環圓筒置於前方，沉頭頭部置於後方，鎖緊環裝在沉頭頭部和滾花段前段徑向間； 3)將組裝好的拉鉚釘有冒頭的前端從被連件後側插入被連接件的安裝孔(4.1)伸到前側，鉚釘尾部拉槽段插入後側的鉚接器夾瓣(6.1)內； 4)鉚接器啟動，夾瓣夾緊尾部拉槽段，帶動鉚釘向後運動，鉚接器外套前端(6.2)相對鉚釘向前運動，向鎖緊環軸向施力，使帶階梯內孔的圓筒(2.1)塑性變形，圓筒前端頂在冒頭後端面受擠壓起鼓成盤狀(2.3)，貼在前被連件表面，夾緊兩被連件； 5)鉚釘繼續向後運動，鉚接器前端繼續擠壓鎖緊環向鎖緊槽移動，直到套環變形完成，鎖緊環完全被擠壓在鎖緊槽內； 6)鉚接器繼續拉動鉚釘向後移動，鉚釘在拉斷槽處斷裂，鉚接器拆除，完成鉚接。 2.按權利要求1所述單面鉚接方法所需的沉頭單面拉鉚釘，包括:I)鉚釘最前端為冒頭，最後段為尾部拉槽段，中部有拉斷槽；2)套環套於鉚釘外，套環圓筒置於前方，套環頭部置於後方；3)套環圓筒外徑不大於冒頭外徑，冒頭外徑小於安裝孔徑；其特徵是: O套環頭部為沉頭頭部；鉚釘拉斷槽和尾部拉槽段之間設光杆段和滾花段，在滾花段和套環沉頭頭部徑向之間增設套在鉚釘外的鎖緊環3，鎖緊環為開口圓環；2)緊接鉚釘拉斷槽前段為鉚接後與鎖緊環?#25380;壓配合的鎖緊槽；3)鉚釘鎖緊槽與冒頭間設為階梯狀光杆，階梯狀光杆與套環圓筒的階梯內孔鉚接後相擠壓配合。 | 南車眉山車輛有限公司 | CN | 620032 四川省眉山市東坡區崇仁鎮南車眉山車輛有限公司技術中心 | 南車眉山車輛有限公司 | CN | 四川 | - | - | - | B21J015/02 | B21J015/02 F16B019/08 | 2 | 2 | - | - | - | 代廣成 伏凱 胡方年 劉宇 劉洋 張榮 賈雲龍 熊光連 趙祥雲 | 9 | CN | 劉冰心 成都市輔君專利代理有限公司 51120 | - | - | 0 | 0 | 12 | 1 | CN103240381A | 1 | 1 | - | CN103240381 | 2013-08-14 | 8 | 南車眉山車輛有限公司 | Overdue | |||||||||||||||||
44 | US11293474 | B2 | 2022-04-05 | Fasteners having enhanced electrical energy dispersion properties | invention | 16/657006 | 2019-10-18 | Systems and methods are provided for fabricating fasteners. One embodiment is an apparatus that includes a fastener. The fastener includes a head, a cylindrical shank that extends from the head and is dimensioned to engage in a fit with a corresponding hole, and a coating that is discontinuously speckled around a circumference of the shank and extends axially along the shank, leaving irregular portions of a surface of the shank exposed. The coating exhibits a higher lubricity than the surface, and the coating exhibits a higher dielectric withstand voltage than the surface. | 1. A method for preparing lock bolts for installation into an aircraft comprising: acquiring a fastener in the form of a lock bolt comprising a head and a cylindrical shank that extends from the head, configured for installation into an airframe of the aircraft;applying a speckled coating around a circumference of the shank and extending axially along the shank, leaving irregular portions of a surface of the shank exposed and uncovered by the coating, wherein applying the coating comprises: determining a desired amount of surface area of the shank to be covered by the coating;adjusting a sprayer based on the desired amount of surface area; andspeckling the coating over the surface via the sprayer; andproviding the fastener for installation into the airframe of the aircraft. | 1. A method for preparing lock bolts for installation into an aircraft comprising: acquiring a fastener in the form of a lock bolt comprising a head and a cylindrical shank that extends from the head, configured for installation into an airframe of the aircraft;applying a speckled coating around a circumference of the shank and extending axially along the shank, leaving irregular portions of a surface of the shank exposed and uncovered by the coating, wherein applying the coating comprises: determining a desired amount of surface area of the shank to be covered by the coating;adjusting a sprayer based on the desired amount of surface area; andspeckling the coating over the surface via the sprayer; andproviding the fastener for installation into the airframe of the aircraft. 2. The method of claim 1 wherein: the coating exhibits a higher lubricity than the surface, andthe coating exhibits a higher dielectric withstand voltage than the surface. 3. The method of claim 1 wherein: applying the coating comprises forming an unpatterned mosaic. 4. The method of claim 1 wherein: adjusting the sprayer adjusts a size of individual speckles applied to the fastener. 5. The method of claim 1 wherein: applying the coating comprises spattering the coating over the surface. 6. The method of claim 1 wherein: the coating is speckled discontinuously around an entire circumference of the shank. 7. The method of claim 1 wherein: the coating comprises an aluminum-pigmented coating. 8. The method of claim 1 wherein: applying the coating comprises:speckling the coating over a portion of the shank dimensioned for an interference fit with a hole. 9. The method of claim 1 further comprising: anodizing a surface of the shank prior to speckling the coating over the shank. 10. The method of claim 1 wherein: applying the coating comprises discontinuously covering bare metal of the shank. 11. The method of claim 1 further comprising: heating material that will form the coating, prior to applying the coating. 12. The method of claim 1 wherein: the irregular portions are randomly shaped. 13. The method of claim 1 wherein: acquiring the fastener comprises acquiring a pull-type lock bolt. 14. The method of claim 1 wherein: acquiring the fastener comprises acquiring a stump-type lock bolt. 15. The method of claim 1 wherein: applying a speckled coating around a circumference of the shank comprises applying the speckled coating to a material selected from the group consisting of titanium, ferrous alloy, and nickel alloy. 16. The method of claim 1 wherein: acquiring the fastener comprises acquiring the fastener having lubricant covering the shank. 17. The method of claim 16 wherein: the lubricant comprises cetyl alcohol. 18. The method of claim 1 wherein: applying the speckled coating comprises covering between thirty and seventy percent of a surface area of the shank. 19. The method of claim 1 wherein: applying the speckled coating comprises discontinuously covering a... | The Boeing Company | US | The Boeing Company | US | IL Chicago | THE BOEING COMPANY | US | 100 N. RIVERSIDE | F16B033/06 | F16B033/06 C23C004/00 C25D007/00 | 3 | 3 | - | F16B0033/06 | F16B0033/06 C23C0004/00 C25D0007/00 | - | - | - | - | - | - | - | - | Tanni Sisco Antonio Carlos Rufin Richard B Tanner Dale Winter Jeffrey Alan Wilkerson Joe Heeter | 6 | US | WA Mukilteo WA Seattle WA Seattle WA Maple Valley WA Everett WA Seattle | Duft & Bornsen, PC | - | - | Moshe Wilensky | Moshe Wilensky | US2013/0183119 US2015/0147136 US2015/0337885 US2016/0169262 | 4 | CN101371052 CN102042288 EP2947015 WO2016050791 | 4 | How to Paint a Bike Frame. A video by CJ Hoyle published on YouTube on May 29, 2016. www.youtube.com/watch?v=antZgmBskMo (Year: 2016).;Affidavit of Examiner Moshe Wilensky. (Year: 2021).;www.sgvbicycles.com/products/27-2-kalloy-anodized-seat-post-html (Year: 2020).;www.amazon.com/reoug-ultralight-25-4×300mm-ultralight-carriages/dp/B089625D8S (Year: 2021).;European Search Report; Application EP19196258; dated Dec. 12, 2019.;Chinese office action, Application No. 2017111025665, dated Oct. 16, 2019. | 6 | 0 | US11293474 US10495130 JP6596050 NL2017955B1 RU2685737C2 BR122023022162A2 BR122023022172A2 BR122023022153A2 RU2017131250A TR201909487T4 RU2017131250A3 ES2733479T3 PT3321523T | 13 | 8 | - | US20200049187 | 2020-02-13 | 14 | THE BOEING COMPANY | Valid | ||||
45 | US04915559 | - | 1990-04-10 | Lightweight fastener | invention | 07/056456 | 1987-05-29 | An aerospace fastener comprises a bolt with a roll-formed thread, and a nut with a similar thread having a uniform pitch P. The bolt has a cylindrical shank, a threaded tip and a run-out zone between the shank and tip. The thread root in the run-out follows a concave curve having a radius in the range of from 2.0P to 2.7P and extends 1.58P to 1.8P from the maximum grip plane of the bolt. The nut has a convexly curved run-in truncating the crest of the nut thread complementary to the run-out to clear the root of the bolt thread when the nut is assembled on the bolt in the minimum grip condition. This permits the nut to be assembled on the bolt further than in a conventional combination, and shortening of the nut and bolt by at least 1P to save weight. | 1. A threaded fastener comprising: a head; a cylindrical shank; a tip having a roll formed thread with a uniform pitch P, a major diameter which is less than the shank diameter, and a minor diameter; a maximum grip plane defined between the shank and tip a specified length from the head; and a run-out zone between the maximum grip plane and the tip having a length in the range of from 1.58P to 2.3P, the run-out zone having a roll formed thread, the thread root in the run-out zone being tangent to the minor diameter at one end and enlarging toward the maximum grip plane along a continuous outwardly concave curve to at least a portion near the maximum grip plane. | What is claimed is: 1. 1. A threaded fastener comprising: a head; a cylindrical shank; a tip having a roll formed thread with a uniform pitch P, a major diameter which is less than the shank diameter, and a minor diameter; a maximum grip plane defined between the shank and tip a specified length from the head; and a run-out zone between the maximum grip plane and the tip having a length in the range of from 1.58P to 2.3P, the run-out zone having a roll formed thread, the thread root in the run-out zone being tangent to the minor diameter at one end and enlarging toward the maximum grip plane along a continuous outwardly concave curve to at least a portion near the maximum grip plane. 2. 2. A threaded fastener as recited in claim 1 wherein the thread root further enlarges toward the shank diameter along an outwardly convex curve adjacent to the maximum grip plane. 3. 3. A threaded fastener as recited in claim 2 including a smooth transition between the outwardly concave curve and the outwardly convex curve. 4. 4. A threaded fastener as recited in claim 1 wherein the length of the run-out is less than 1.8P. 5. 5. A threaded fastener as recited in claim 4 wherein the thread root follows a concave curve having a radius in the range of from 2.0P to 2.7P. 6. 6. A threaded fastener as recited in claim 5 wherein the continuous curve extends to at least the major diameter. 7. 7. A threaded fastener as recited in claim 5 comprising a convex lead-in between the shank diameter and the concave curve at approximately the major diameter. 8. 8. A threaded fastener as recited in claim 4 comprising a convex lead-in between the shank diameter and the concave curve at approximately the major diameter. 9. 9. A threaded fastener as recited in claim 1 wherein the continuous curve extends to at least the major diameter. 10. 10. A threaded fastener comprising: a head; a cylindrical shank; a tip having a roll formed thread with a uniform pitch P, a major diameter which is less than the shank diameter, and a major diameter; a maximum grip plane defined between the shank and tip a specified length from the head; and a run-out zone between the maximum grip plane and the tip having a roll formed thread, the thread root being tangent to the major diameter at one end and enlarging toward the maximum grip plane along an outwardly concave curve having a radius in the range of from 2.0P to 2.7P. 11. 11. A threaded fastener as recited in claim 10 comprising a convex lead-in between the shank diameter and the concave curve at approximately the major diameter. 12. 12. A threaded fastener as recited in claim 11 wherein the continuous curve extends to at least the major diameter. 13. 13. A threaded fastener as recited in claim 10 wherein the continuous curve extends to at least the major diameter. 14. 14. A threaded fastener comprising: a body a threaded hole in the body; a thread having a uniform pitch P in the hole; a counterbore at one end o... | Wheeler; Roland A. Rath; Jack | VSI Corporation | CA Culver City | VSI CORPORATION | US | 45025 AVIATION DRIVE, SUITE 400 | F16B035/00 | F16B035/00 F16B037/16 B21D053/20 B21K001/44 | 3 | 4 | - | - | - | 411/366.000 | 411/366.000 411/424.000 411/436.000 010/027.00R 010/086.00R 072/469.000 | - | - | Wheeler; Roland A. Rath; Jack | 2 | CA Los Angeles CA Los Angeles | Christie, Parker & Hale | - | - | - | Wilson; Neill R. | Wilson; Neill R. | 929027 1764053 1940617 2215930 2314390 2340706 2740136 2793884 2895367 2985898 3538739 3828422 4034586 4157725 4254809 4260005 4326825 | 17 | ATX204236 DEX843952 JPX54-106754 CHX188372 GBX685703 GBX2074280 GBX2088508 | 7 | 38 | 17 | US04915559 | 1 | 1 | - | 0 | VSI CORPORATION | Overdue | |||||||||||||
46 | US10161434 | B2 | 2018-12-25 | Hollow metal screw and method of making | invention | 15/080007 | 2016-03-24 | A hollow screw and related process of making is provided, wherein the hollow screw is formed from a generally circular corrosion resistant stainless steel disk cut from flat roll stock. The hollow screw includes a head and an elongated and hollow shaft having a wall thickness between about 0.2 to about 0.7 millimeters extending therefrom and defining a shank portion and a threaded portion having a plurality of threads thereon with a rotational drive mechanism configured to facilitate tightening via the threads. The process involves annealing to soften the stamped hollow screw, followed by thread rolling, and then age hardening the hollow screw. As such, the resultant hollow screw is relatively lightweight, about 50% the mass of a solid core screw made from the same material, with a sufficient thread strength to meet most aerospace applications and contributes to important aircraft fuel economy. | 1. A hollow nut, comprising: a body having an internally threaded core formed from a generally inwardly positioned central shaft that turns about itself to form an upwardly presented head and downwardly extending outer nut body in generally spaced apart relation relative to the inwardly positioned central shaft and terminating in a radially outwardly extending flange;a captive washer having an inner aperture including a periphery radially entirely larger than a major thread diameter of the internally threaded core to permit insertion of a threaded fastener, the captive washer being at least partially formed around the radially outwardly extending flange generally in adjacent relationship with the first end and permitting free rotation relative to the nut when attached thereto; anda wave washer sandwiched between the captive washer and the first end having the radially outwardly extending flange. | 1. A hollow nut, comprising: a body having an internally threaded core formed from a generally inwardly positioned central shaft that turns about itself to form an upwardly presented head and downwardly extending outer nut body in generally spaced apart relation relative to the inwardly positioned central shaft and terminating in a radially outwardly extending flange;a captive washer having an inner aperture including a periphery radially entirely larger than a major thread diameter of the internally threaded core to permit insertion of a threaded fastener, the captive washer being at least partially formed around the radially outwardly extending flange generally in adjacent relationship with the first end and permitting free rotation relative to the nut when attached thereto; anda wave washer sandwiched between the captive washer and the first end having the radially outwardly extending flange. 2. The hollow nut of claim 1, wherein the body is formed from a flat stock of metal material. 3. The hollow nut of claim 1, wherein the periphery of the inner aperture comprises a generally circular periphery. 4. The hollow nut of claim 1, wherein the captive washer includes a substantially outer planar surface having a size and shape for flush engagement with a substrate, the outer planar surface protecting the substrate from galling during fastener tightening. 5. The hollow nut of claim 1, wherein the captive washer comprises a substantially uniform thickness. | Physical Systems, Inc. | US | Physical Systems, Inc. | US | NV Carson City | Physical Systems, Inc. | US | - | F16B037/00 | F16B037/00 F16B023/00 C21D009/00 C21D006/02 C21D001/26 C22C038/58 C22C038/54 C22C038/50 C22C038/46 C22C038/42 C22C038/06 C22C038/02 B21D053/24 F16B033/00 F16B035/04 F16B037/02 B21H003/04 B21K001/56 F16B035/00 B21H003/02 C22C038/00 C22C038/04 C22C038/18 C21D008/10 | 6 | 12 | - | F16B0023/00 | F16B0023/00 B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/56 C21D0001/26 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/18 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/0046 F16B0033/008 F16B0035/00 F16B0035/04 F16B0035/041 F16B0037/00 F16B0037/02 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | F16B0023/00 B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/56 C21D0001/26 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/18 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/0046 F16B0033/008 F16B0035/00 F16B0035/04 F16B0035/041 F16B0037/00 F16B0037/02 F16B0041/002 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | - | - | - | - | - | - | - | Charles G. Hutter, III | 1 | US | NV Carson City | Lowry Blixseth LLP Scott M. Lowry | - | - | Gary W Estremsky | Gary W Estremsky | US1098716 US1172406 US3135154 US3144803 US3446261 US3550498 US3796123 US3877339 US3976123 US4123132 US4132145 US4157725 US4431353 US4479747 US4571135 US4878794 US4895484 US4986712 US5219255 US5244290 US5393183 US5618145 US5688091 US5711711 US6039524 US6435791 US6802681 US8403611 US8459919 US8591157 US2002/0182032 US2003/0095847 US2004/0234358 US2005/0220564 US2007/0237601 US2010/0040430 US2012/0263557 US2013/0195578 | 38 | - | 0 | “A286 technical Data” California Metal & Supply Inc. Captured on May 2, 2013. Retrieved from the Internet on Sep. 11, 2015. <http://www.californiametal.com/A286_Sheet_Plate_Pipe_Tube_Rod_Bar_Tech_Data.htm>. | 9 | 0 | EP3760335B1 KR1026075580000 KR1025491270000 KR1024521110000 EP3763458B1 CN112024631B EP3166738B1 CN106660107B JP6599971 US10161434 US09803676 US09689415 CN111889614A WO2016007557 CA2954530C RU2019118803A3 BR112017000363B1 ES2928258T3 RU2017102933A AU2020202876B2 BR122018013980B1 AU2015287923A1 CA2954530A1 RU2017102933A3 AU2015287923B2 AU2020202881A1 AU2020202881B2 RU2697536C2 CA3111258C ES2986081T3 BR112017000363A2 RU2019118803A AU2020202876A1 ES2826567T3 CA3111258A1 BR122018013986B1 | 36 | 11 | - | US20160201710 | 2016-07-14 | 11 | Physical Systems, Inc. | Valid | ||||
47 | CN119491863 | A | 2025-02-21 | 適用于高應力環境的自復位緩衝鉚釘及其製備方法 | invention | CN202411698181.X | 2024-11-26 | 本發明涉及鉚釘生產加工技術領域，公開了適用于高應力環境的自復位緩衝鉚釘及其製備方法，包括：釘杆，所述釘杆的外壁設置有緩衝定位套，所述緩衝定位套用於對釘杆起到第一緩衝，所述緩衝定位套的外壁設置有復位套，所述復位套的外壁設置有釘套，所述釘套用於對復位套固定防止滑出，所述復位套用於對釘杆和緩衝定位套起到定位並保證自動回位，所述釘杆的底端固定攔截有釘頭，所述釘頭的上表面與的下表面相貼合。通過釘杆、釘套和釘頭，使用的材料能承受高應力環境下的拉力、壓力和摩擦力，復位套和緩衝定位套的材料也分別針對各自功能進行優化，這種鉚釘能夠適應飛機飛行時的複雜應力，包括空氣動力載荷，確保結構連接的安全性。; | 1.適用于高應力環境的自重定緩衝鉚釘，其特徵在於，包括：釘杆（1），所述釘杆（1）的外壁設置有緩衝定位套（2），所述緩衝定位套（2）用於對釘杆（1）起到第一緩衝，所述緩衝定位套（2）的外壁設置有復位套（3），所述復位套（3）的外壁設置有釘套（4），所述釘套（4）用於對復位套（3）固定防止滑出，所述復位套（3）用於對釘杆（1）和緩衝定位套（2）起到定位並保證自動回位，所述釘杆（1）的底端固定攔截有釘頭（5），所述釘頭（5）的上表面與（4）的下表面相貼合。 | 1.適用于高應力環境的自重定緩衝鉚釘，其特徵在於，包括：釘杆（1），所述釘杆（1）的外壁設置有緩衝定位套（2），所述緩衝定位套（2）用於對釘杆（1）起到第一緩衝，所述緩衝定位套（2）的外壁設置有復位套（3），所述復位套（3）的外壁設置有釘套（4），所述釘套（4）用於對復位套（3）固定防止滑出，所述復位套（3）用於對釘杆（1）和緩衝定位套（2）起到定位並保證自動回位，所述釘杆（1）的底端固定攔截有釘頭（5），所述釘頭（5）的上表面與（4）的下表面相貼合。 2.所述釘套（4）、釘杆（1）和釘頭（5）的材料為：碳1.2-1.8%，錳18-20%，矽0.8-1.2%，鉻1.5-2%，鉬0.5-1.2%，釩0.2-0.4%，鈦0.1-0.2%，硼0.01-0.05%，鈮0.05-0.09%，稀土以鈰為主占0.5-1%、鑭占0.3-0.8%、釔占0.2-0.4%，其餘為鐵，採用多種材料混合製成的新型高錳鋼；所述復位套（3）的材料為：碳0.8-1%，錳10-15%，矽1-2%，鉻1-2%，鎳2-4%，鉬0.3-0.6%，釩0.1-0.3%，鎢0.2-0.4%，稀土以釹為主占0.3-0.8%、鐠占0.2-0.4%，其餘為鐵；所述緩衝定位套（2）的材料為：吡咯烷酮羧酸一三乙醇胺鹽：4%-5%，苯甲酸鈉：8%-10%，丁晴橡膠：8%-10%，三元乙丙橡膠：50%-55%，乙酸乙酯：2%-3%，膽鹼：4%-5%，石蠟：3%-4%，矽酸：5%-6%，樹脂：4%-5%，四氫苄醇：0.3%-0.4%，次氮基三乙酸鈉鹽：1.5%-2%，乙酸二氫鬆油酯：1.5%-2%，羥基丙酸：6%-8%，乙酸：5%-7%，阻燃劑：4%-5%，石墨烯：2%-3%，二硫化鉬：6%-8%，增塑劑：3%-4%，潤滑油：1.5%-2%，偶聯劑：5%-6%，古馬隆樹脂：2%-3%。 3.適用于高應力環境的自復位緩衝鉚釘及其製備方法，根據權利要求1-2任一項所述的適用于高應力環境的自重定緩衝鉚釘，其特徵在於，包括以下步驟：S1、釘杆、釘杆頭和釘套的製備：按照配方準備材料：稱取碳，錳，矽，鉻，鉬，釩，鈦，硼，鈮，稀土以鈰為主占、鑭占、釔占，其餘為鐵，將稱好的材料放入熔爐中進行熔煉，等待材料充分熔化並混合均勻，將熔煉好的鋼水倒入模具中進行鑄造，得到釘杆、釘杆頭和釘套的毛坯件；S2、復位套的製備：按照配方準備材料：稱取碳、錳、矽、鉻、鎳、鉬、釩、鎢、稀土釹、鐠和鐵，同釘杆部件的熔煉和鑄造步驟，得到重定套的毛坯件，對復位套毛坯進行熱處理，如淬火、回火，以提高其硬度、強度和韌性等性能；S3、緩衝定位套的製備：分別稱取吡咯烷酮羧酸一三乙醇胺鹽、苯甲酸鈉、丁晴橡膠、三元乙丙橡膠、乙酸乙酯、膽鹼、石蠟、矽酸、樹脂、四氫苄醇、次氮基三乙酸鈉鹽、乙酸二氫鬆油酯、羥基丙酸、乙酸、阻燃劑、石墨烯、二硫化鉬、增塑劑、潤滑油、偶聯劑和古馬隆樹脂材料，將丁晴橡膠和三元乙丙橡膠放入密煉機中進行混合，加入助劑促進劑、防老劑，將除橡膠以外的其他材料按照比例混合均勻，使用攪拌機設備進行混合，將混合好的添加劑逐漸加入橡膠材料中，繼續在密煉機或開煉機上進行混合，確保各成分充分混合均勻，並倒入模具中形成定位套的形狀；S4、篩選組裝：先將各個生產好的配件通過篩選裝置進行篩選，確保產品的外觀有無破損，產品是否合格進行篩選，通過將篩選出來的產品進行組裝先將製備好的緩衝定位套，套在釘杆上，之後將復位套套在緩衝定位套外面，最後將釘套套在復位套外面，並確保各部件安裝牢固，不會滑出；S5、表面處理：對組裝好的自復位緩衝鉚釘進行電鍍，電鍍在鉚釘表面形成一層均勻的保護膜，電鍍層還可以增加鉚釘的表面硬度，提高耐磨性，將鉚釘放入磷化液中進行處理，在其表面形成一層磷化膜，提高鉚釘的耐腐蝕性和附著力，同時起到潤滑作用，便於鉚釘的安裝和使用，表面處理完成後，對鉚釘進行最後的品質檢測，確保其各項性能指標符合要求，然後進行包裝和儲存，以便於運輸和使用。 4.S1中、熔爐的熔煉溫度為：1500-1600℃，熔煉時間為：2-3小時，加入順序為：先加入鐵開始升溫，當溫度升高到1400-1450攝氏度時，加入鉻和鉬，當溫度穩定在1450-1500℃時加入錳溫度升高在1500-1550℃時加入碳、鈮和稀土元素鈰、鑭和釔，後加入矽。 5.S2中、熔爐的熔煉溫度為：1500-1550℃，熔煉時間為：1.5-2.5小時，加入順序為：先加入鐵升溫到1400-1450℃加入鉻和鎢，之後升溫到1450-1500℃時加入猛，再進行加溫溫度達到1500-1550℃時加入鎳、鉬、釩，隨後加入碳，後加入稀土元素釹、鐠和矽，淬火加熱溫度為950-1000℃，回火溫度為150-250℃，回火時間為1.5-2.5小時。 6.S3中、先將丁晴橡膠加入密煉機，接著加入三元乙丙橡膠，以30-40轉/分鐘的速度運行密煉機，初步混合2-3分鐘，然後加入促進劑和防老劑，之後將密煉機轉子速度提高到40-60轉/分鐘，繼續混合5-8分鐘；在攪拌設備中，首先加入吡咯烷酮羧酸-三乙醇胺鹽，接著加入苯甲酸鈉，然後加入矽酸，再加入樹脂，之後加入四氫苄醇，再加入次氮基三乙酸鈉鹽，接著加入乙酸二氫鬆油酯，然後加入古馬隆樹脂，之後加入乙酸乙酯，上述材料加入時攪拌速度為1000-1200轉/分鐘，攪拌時間為10-15分鐘從加入乙酸乙酯開始計時，再加入膽鹼，接著加入羥基丙酸，然後加入乙酸，之後加入阻燃劑，再加入石墨烯，接著加入二硫化鉬，然後加入增塑劑，之後加入潤滑油，最後加入偶聯劑，繼續攪拌直至所有材料混合均勻。 7.S4中、所述篩選裝置的輸送速度為0.5-1.5米/分鐘，攝像頭高度在5-15釐米的高度，檢測大小誤差±0.1-5，照明設備的光源為：勻的白色光源，光照強度在800-1200勒克斯。 8.S5中、電解槽的材質為聚氯乙烯，陽極材料為鍍鋅板，印記材料為銅，內部溫度15-30℃，磷化液的材料包括：去離子水：1000-1500份，硫酸鎳：150-200份，檸檬酸鈉：60-150份，乳酸：20-50份，二甲基己炔醇：0.4-1份，馬日夫鹽：18-22份，硝酸鋅：15-25份，氟化鈉：16-32份，紅礬鈉：8-16份。 | 無錫安士達五金有限公司 | CN | 214199 江蘇省無錫市錫山區東港鎮港東村 | 無錫安士達五金有限公司 | CN | - | - | - | - | F16B019/06 | F16B019/06 F16F015/02 C08L023/16 C08L009/02 C08L091/06 C08K005/098 C08K003/34 C08K003/04 C22C038/38 C22C038/02 C22C038/22 C22C038/24 C22C038/28 C22C038/26 C22C038/32 | 5 | 8 | - | - | - | - | - | - | - | - | - | - | - | 邱曉東 繆建國 周科 | 3 | - | | 鄧瑞鋒 無錫風創智慧財產權代理事務所(特殊普通合夥) 32461 | 20250221 | - | - | - | - | 0 | - | 0 | - | 1 | 0 | CN119491863A | 1 | 1 | - | CN119491863 | 2025-02-21 | 19 | 無錫安士達五金有限公司 | Pub. | |||
48 | CN116921744 | A | 2023-10-24 | 主動傾斜角制孔裝置、機械連接裝置及機械連接方法 | invention | CN202310691385.X | 2023-06-12 | 本發明公開了一種主動傾斜角制孔裝置，包括用於使鑽頭通過的套筒，所述套筒的底部設有中空薄矽膠層，所述中空薄矽膠層用於限制鑽孔過程中制孔裝置與待鑽孔試件之間的相對位移，所述套筒的頂部設有帶螺紋固定器，所述帶螺紋固定器用於製備斜孔時制孔裝置與鑽床進行螺接；本發明還公開了一種機械連接裝置及機械連接方法；本發明提高了飛機結構連接靜強度和疲勞壽命。 | 1.一種主動傾斜角制孔裝置，其特徵在於，包括用於使鑽頭通過的套筒，所述套筒的底部設有中空薄矽膠層，所述中空薄矽膠層用於限制鑽孔過程中制孔裝置與待鑽孔試件之間的相對位移，所述套筒的頂部設有帶螺紋固定器，所述帶螺紋固定器用於製備斜孔時制孔裝置與鑽床進行螺接。 | 1.一種主動傾斜角制孔裝置，其特徵在於，包括用於使鑽頭通過的套筒，所述套筒的底部設有中空薄矽膠層，所述中空薄矽膠層用於限制鑽孔過程中制孔裝置與待鑽孔試件之間的相對位移，所述套筒的頂部設有帶螺紋固定器，所述帶螺紋固定器用於製備斜孔時制孔裝置與鑽床進行螺接。 2.一種主動傾斜角機械連接裝置，其特徵在於，包括帶斜孔試件和穿過所述帶斜孔試件的斜孔的緊固件，所述帶斜孔試件的斜孔由權利要求1所述的主動傾斜角制孔裝置製備斜孔，所述帶斜孔試件的頂部和所述緊固件的頂部之間設有釘頭墊圈，所述帶斜孔試件的底部和所述緊固件的底部之間設有緊固墊圈，且所述釘頭墊圈和緊固墊圈的上下表面均帶有一定夾角。 3.一種主動傾斜角機械連接方法，其特徵在於，包括：首先採用如權利要求1所述的主動傾斜角制孔裝置製備帶斜孔試件，然後採用如權利要求2所述的主動傾斜角機械連接裝置對所述帶斜孔試件進行連接，具體包括：將緊固件從釘頭墊圈底部平面圓孔塞入，再穿過帶斜孔試件，緊固件完全插入後，將緊固墊圈套入緊固件剩餘部分，使緊固墊圈頂部斜面與帶斜孔試件9接觸。 4.α＝90°-θ其中，α為帶斜孔試件斜孔軸線與帶斜孔試件表面的夾角；θ為釘頭墊圈和緊固墊圈的上下表面的夾角。 5. 6.其中，Aα為斜孔表面積；A90°為直孔表面積。 7. | 四川大學 | CN | 610000 四川省成都市一環路南一段24號 | 四川大學 | CN | - | - | - | - | B23B049/00 | B23B049/00 B23B049/02 B23Q003/00 B23B041/00 F16B005/02 F16B005/04 F16B043/02 | 3 | 5 | - | - | - | - | - | - | - | - | - | - | - | 楊天智 左楊傑 | 2 | - | | 劉士暢 北京雲嘉湃富智慧財產權代理有限公司 11678 | 20231024 | - | - | - | - | 0 | - | 0 | - | 2 | 0 | CN116921744A | 1 | 1 | - | CN116921744 | 2023-10-24 | 18 | 四川大學 | Pub. | |||
49 | US10406590 | B2 | 2019-09-10 | Hollow metal screw and method of making | invention | 15/024324 | 2015-07-07 | A hollow screw and related process of making is provided, wherein the hollow screw is formed from a generally circular corrosion resistant stainless steel disk cut from flat roll stock. The hollow screw includes a head and an elongated and hollow shaft having a wall thickness between about 0.2 to about 0.7 millimeters extending therefrom and defining a shank portion and a threaded portion having a plurality of threads thereon with a rotational drive mechanism configured to facilitate tightening via the threads. The process involves annealing to soften the stamped hollow screw, followed by thread rolling, and then age hardening the hollow screw. As such, the resultant hollow screw is relatively lightweight, about 50% the mass of a solid core screw made from the same material, with a sufficient thread strength to meet most aerospace applications and contributes to important aircraft fuel economy. | 1. A hollow screw, comprising: a head formed from a flat stock of metal material;an elongated and hollow shaft comprising a wall thickness between about 0.2 and 0.7 millimeters formed from the flat stock of metal material and integrally extending from the head, the elongated and hollow shaft including a shank portion and a threaded portion having a plurality of threads thereon; anda rotational drive mechanism comprising a hexagonal shape integrally formed from the flat stock of metal material and an inner spline recess formed from the head or the elongated and hollow shaft, and configured to facilitate tightening of the hollow screw by way of the threads. | 1. A hollow screw, comprising: a head formed from a flat stock of metal material;an elongated and hollow shaft comprising a wall thickness between about 0.2 and 0.7 millimeters formed from the flat stock of metal material and integrally extending from the head, the elongated and hollow shaft including a shank portion and a threaded portion having a plurality of threads thereon; anda rotational drive mechanism comprising a hexagonal shape integrally formed from the flat stock of metal material and an inner spline recess formed from the head or the elongated and hollow shaft, and configured to facilitate tightening of the hollow screw by way of the threads. 2. The hollow screw of claim 1, including an integral washer formed from the flat stock of metal material and extending outwardly from the head. 3. The hollow screw of claim 2, including a captive washer at least partially formed around the integral washer in a manner permitting free rotation of the captive washer relative to the integral washer, the head and the elongated and hollow shaft. 4. The hollow screw of claim 3, wherein an outer rim of the captive washer is turned upwardly and around an outer periphery of the integral washer to adjacently couple the captive washer to the integral washer. 5. The hollow screw of claim 3, wherein the captive washer comprises a thickness of about 0.15 to 0.30 millimeters. 6. The hollow screw of claim 3, wherein the captive washer comprises a conductive material. 7. The hollow screw of claim 2, including a free floating washer slidable along the shank portion and captive between the integral washer and the plurality of threads, the threaded portion having an outer diameter relatively larger than an outer diameter of the shank portion. 8. The hollow screw of claim 1, wherein the flat stock of metal material comprises a corrosion resistant metal material comprising A286 steel. 9. The hollow screw of claim 1, wherein the threads comprise a strength of about 1200 MPa to 1400 MPa. 10. The hollow screw of claim 1, including a nose formed at an end of the elongated and hollow shaft opposite the head. 11. The hollow screw of claim 1, wherein the head comprises a rounded head or a flat head. 12. The hollow screw of claim 1, wherein the elongated and hollow shaft includes a cap preventing fluid flow through an interior of the hollow screw. 13. The hollow screw of claim 1, wherein the weight of the hollow screw is approximately ½ the weight of a solid screw of similar size and shape. 14. A hollow screw, comprising: a body having a generally inwardly positioned elongated and hollow shaft formed from a flat stock of metal material that turns about itself to form an upwardly presented head and a downwardly extending outer skirt in generally spaced apart relation relative to the inwardly positioned elongated and hollow shaft and terminating in a radially outwardly extending flange, the elongated and hollow shaft including a shank portion and a threaded portio... | Physical Systems, Inc. | US | Physical Systems, Inc. | US | NV Carson City | Physical Systems, Inc. | US | - | F16B021/00 | F16B021/00 B21D053/24 B21K001/56 B21H003/02 C21D006/02 F16B023/00 C21D001/26 C21D009/00 F16B035/00 B21H003/04 C22C038/00 C22C038/02 C22C038/04 C22C038/06 C22C038/42 C22C038/46 C22C038/50 C22C038/54 C22C038/58 F16B033/00 F16B035/04 F16B037/02 B21K001/46 C21D006/00 C21D008/10 | 6 | 13 | - | B21D0053/24 | B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/46 B21K0001/56 C21D0001/26 C21D0006/00 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/42 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/00 F16B0033/008 F16B0035/00 F16B0035/041 F16B0037/02 C21D0006/004 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | B21D0053/24 B21H0003/02 B21H0003/04 B21K0001/46 B21K0001/56 C21D0001/26 C21D0006/00 C21D0006/02 C21D0009/0093 C22C0038/002 C22C0038/02 C22C0038/04 C22C0038/06 C22C0038/42 C22C0038/44 C22C0038/46 C22C0038/50 C22C0038/54 C22C0038/58 F16B0023/00 F16B0033/008 F16B0035/00 F16B0035/041 F16B0037/02 C21D0006/004 C21D0008/105 C21D2261/00 F16B0023/0053 F16B0023/0061 F16B0023/0092 | - | - | - | - | - | - | - | Charles G. Hutter, III | 1 | US | NV Carson City | Lowry Blixseth APC Scott M. Lowry | - | - | Gary W Estremsky | Gary W Estremsky | US1098716 US1172406 US1281174 US1957282 US2026859 US4157725 US4414466 US4878794 US5711711 US2002/0182032 US2003/0042737 US2005/0220564 US2011/0262241 US2013/0195578 | 14 | - | 0 | “A286 technical Data” California Metal & Supply Inc. Captured on May 2, 2013. Retrieved from the Internet on Sep. 11, 2015. <http://www.californiametal.com/A286_Sheet_Plate_Pipe_Tube_Rod_Bar_Tech_Data.htm>. | 10 | 12 | US10406590 | 1 | 1 | - | US20170282236 | 2017-10-05 | 10 | Physical Systems, Inc. | Valid | ||||
50 | US11767436 | B2 | 2023-09-26 | Thermal and cold spray plastic coating covering vehicle fasteners inside fuel tank for lightning strike and other electromagnetic protection | invention | 16/052015 | 2018-08-01 | Tunable thermoplastic polymer powder feedstock formulations and tunable conductive thermoplastic polymer powder feedstock formulations are disclosed for delivery to a high-velocity sprayer, along with tunable coatings made from the disclosed formulations and methods for coating installed fasteners, and fasteners, fastener/substrate interfaces and substrates coated with the tunable thermoplastic polymer coatings. | 1. An assembly comprising: a first substrate, said first substrate comprising a first substrate surface;a second substrate, said second substrate comprising a second substrate surface;an installed fastener positioned at a fastener/substrate interface, said installed fastener configured to join the first substrate and the second substrate to form a fastener/substrate interface perimeter, said fastener/substrate interface perimeter occurring at at least one of the first substrate surface and the second substrate surface; anda tunable electrically dissipative spray-deposited thermoplastic polymer coating material requiring no curing, said tunable electrically dissipative spray-deposited thermoplastic polymer coating material configured to directly contact and coat the installed fastener and further configured to directly contact and coat the fastener/substrate interface perimeter to form an electrically dissipative restricted access coated fastener and an electrically dissipative restricted access coated fastener/substrate interface perimeter, said tunable electrically dissipative spray-deposited thermoplastic polymer coating material consisting of: a thermoplastic polymer consisting of at least one of nylon, polyetheretherketone, polyetherketoneketone, polyamide, polyphenylsulfide, polyphenylsulfone, polysulfone, and polyetherimide;an amount of conductive material said conductive material comprising an average particle size ranging from about 5 μm to about 80 μm;wherein the relative percentage by volume of conductive material present in the tunable electrically dissipative spray-deposited thermoplastic polymer coating material ranges from about 1% to about 9% by volume;wherein the tunable electrically dissipative spray-deposited thermoplastic polymer coating material density ranges from about 1.0 to about 1.8 g/cc;wherein the tunable electrically dissipative spray-deposited thermoplastic polymer coating material has a resistivity value ranging from about 1×105 to about 1×1011 ohm-m; andwherein the tuned electrically dissipative spray-deposited thermoplastic polymer coating material has an adhesion ranging from about 5 to about 50 lbs./in wide area as determined by ASTM D6862-11(2016) Standard Test Method for 90° Peel Resistance. | 1. An assembly comprising: a first substrate, said first substrate comprising a first substrate surface;a second substrate, said second substrate comprising a second substrate surface;an installed fastener positioned at a fastener/substrate interface, said installed fastener configured to join the first substrate and the second substrate to form a fastener/substrate interface perimeter, said fastener/substrate interface perimeter occurring at at least one of the first substrate surface and the second substrate surface; anda tunable electrically dissipative spray-deposited thermoplastic polymer coating material requiring no curing, said tunable electrically dissipative spray-deposited thermoplastic polymer coating material configured to directly contact and coat the installed fastener and further configured to directly contact and coat the fastener/substrate interface perimeter to form an electrically dissipative restricted access coated fastener and an electrically dissipative restricted access coated fastener/substrate interface perimeter, said tunable electrically dissipative spray-deposited thermoplastic polymer coating material consisting of: a thermoplastic polymer consisting of at least one of nylon, polyetheretherketone, polyetherketoneketone, polyamide, polyphenylsulfide, polyphenylsulfone, polysulfone, and polyetherimide;an amount of conductive material said conductive material comprising an average particle size ranging from about 5 μm to about 80 μm;wherein the relative percentage by volume of conductive material present in the tunable electrically dissipative spray-deposited thermoplastic polymer coating material ranges from about 1% to about 9% by volume;wherein the tunable electrically dissipative spray-deposited thermoplastic polymer coating material density ranges from about 1.0 to about 1.8 g/cc;wherein the tunable electrically dissipative spray-deposited thermoplastic polymer coating material has a resistivity value ranging from about 1×105 to about 1×1011 ohm-m; andwherein the tuned electrically dissipative spray-deposited thermoplastic polymer coating material has an adhesion ranging from about 5 to about 50 lbs./in wide area as determined by ASTM D6862-11(2016) Standard Test Method for 90° Peel Resistance. 2. The assembly of claim 1 wherein the conductive material comprises at least one of titanium, nickel alloy, copper, carbon black, graphene powder, and carbon nanotubes. 3. An object comprising the assembly of claim 1. 4. The assembly of claim 1, wherein the tunable electrically dissipative spray-deposited thermoplastic coating material has a resistivity value ranging from about 1×105 to about 1×108 ohm-m. 5. An object comprising the assembly of claim 2. 6. The object of claim 3, wherein the object is a vehicle selected from the group consisting of: a manned aircraft, an unmanned aircraft, a manned spacecraft, an unmanned spacecraft, a manned rotorcraft, an unmanned rotorcraft, a manned terrestrial vehicle, a unmanned ... | THE BOEING COMPANY | US | THE BOEING COMPANY | US | VA Arlington | THE BOEING COMPANY | US | 100 NORTH RIVERSIDE PLAZA | C09D005/24 | C09D005/24 C09D161/16 C23C004/02 C23C004/04 F16B001/00 B60K015/03 B64D045/02 C08K003/08 | 6 | 7 | - | C09D0005/24 | C09D0005/24 C09D0161/16 C23C0004/02 C23C0004/04 F16B0001/00 B60K0015/03 B60K2015/03401 B64D0045/02 C08K0003/08 C08K2003/0881 F16B2001/0064 | B05B0007/205 C09D0005/24 B64D0037/32 B64F0005/10 C09D0005/03 C09D0007/61 C09D0161/16 C23C0004/02 C23C0004/04 F16B0001/00 F16B0033/06 F16B0037/14 B05B0013/0431 B60K0015/03 B60K2015/03401 B64D0045/02 C08K0003/04 C08K0003/041 C08K0003/042 C08K0003/08 C08K2003/085 C08K2003/0862 C08K2003/0881 C08K2201/001 F16B2200/93 Y02T0050/40 | - | - | - | - | - | - | - | Weidong Song | 1 | US | WA Mukilteo | COATS & BENNETT, PLLC | - | - | Nathan L Van Sell | Nathan L Van Sell | US3755713 US5302414 US8293378 US8658256 US11390773 US20020168466 US20050196543 US20060183841 US20070044406 US20080011444 US20100063072 US20100224724 US20120138609 US20140055906 US20150210039 US20150271960 US20160096302 US20160107739 US20170152601 US20170217560 US20170275476 US20180298154 | 22 | CN1410475 CN101115791 CN101309758 CN103194142 CN107674559 EP0988898 EP2733231 EP2585372 EP3150502 WO2006076341 WO2008048705 WO2015023353 WOWO-2015119123 WOWO-2016078664 WO2018110488 | 15 | Polymer Database, “Polyphenylene Sulfide (PPS)”, retrieved from the internet: https://polymerdatabase.com/Commercial Polymers/PPS.html [retrieved on Mar. 23, 2023], pp. 1-2.;Polymer Database, “Nylon 12—Poly(ω-dodecanamide)”, retrieved from the internet: https://blog.polymerdatabase.com/polymers/nylon12.html [retrieved on Mar. 23, 2023], pp. 1-2.;Polymer Database, “Nylon 11—Poly(ω-undecanamide)”, retrieved from the internet: https://blog.polymerdatabse.com/polymers/nylon11.html [retrieved on Mar. 23, 2023], pp. 1-2.;Polymer Database, “Unfilled Polyetheretherketone (PEEK)”, retrieved from the internet: https://polymerdatabase.com/Commercial Polymers/PEEK.html [retrieved on Mar. 23, 2023], pp. 1-2.;Polymer Database, “Nylon 6-6—Poly(hexamethylene adipamide)”, retrieved from the internet: https://blog.polymerdatabase.com/polymers/nylon66.html [retrieved on Mar. 23, 2023], pp. 1-2.;Polymer Database, “Nylon 6—Poly(caprolactam)”, retrieved from the internet: https://blog.polymerdatabase.com/polymers/nylon6.html [retrieved on Mar. 23, 2023], pp. 1-2. | 7 | 4 | EP3604456B1 US11767436 CN116239925A CN110804363A BR102019015535A8 BR102019015535A2 | 6 | 4 | - | US20200040201 | 2020-02-06 | 13 | THE BOEING COMPANY | Valid | ||||
51 | US08209865 | B2 | 2012-07-03 | Method of manufacturing aircraft using temporary fasteners | invention | 12/478596 | 2009-06-04 | A temporary fastener and a method of attaching an aircraft skin to a frame using the temporary fastener during a step of the skin to frame assembly process. The fastener secures the skin to the structure while holes for permanent fasteners are drilled through the skin and frame; the fastener is flush mounted so that an automatic drill can drill the holes without interference. The temporary fastener can be removed after the permanent fastener holes are drilled, and before or after permanent fasteners are inserted within their respective holes. | 1. A method of aircraft assembly comprising: positioning an aircraft skin onto an aircraft frame;boring a first hole through the skin and frame;coupling the skin and frame by inserting a temporary fastener within the first hole radially expanding a portion of the temporary fastener to apply a radial force to grip the portion of the first hole within the frame;boring additional holes through the skin and frame; andremoving the temporary fasteners and inserting permanent fasteners through the additional holes and the hole previously occupied by the temporary fastener to permanently attach the skin to the frame. | 1. A method of aircraft assembly comprising: positioning an aircraft skin onto an aircraft frame;boring a first hole through the skin and frame;coupling the skin and frame by inserting a temporary fastener within the first hole radially expanding a portion of the temporary fastener to apply a radial force to grip the portion of the first hole within the frame;boring additional holes through the skin and frame; andremoving the temporary fasteners and inserting permanent fasteners through the additional holes and the hole previously occupied by the temporary fastener to permanently attach the skin to the frame. 2. The method of claim 1, wherein inserting permanent fasteners comprises bonding nuts to the frame opposite the holes. 3. The method of claim 1, further comprising applying a pliable shim material between the skin and frame before installing the temporary fastener. 4. The method of claim 3, further comprising compressing the skin and frame with a clamp to force excess shim material from between the skin and frame before installing the temporary fastener. 5. The method of claim 4, further comprising applying a mask film to the skin on its side facing the structure before applying the shim material and removing the mask film after removing the temporary fastener and prior to affixing the skin and frame with a permanent fastener. 6. The method of claim 4, further comprising removing the clamp before boring the additional holes. 7. The method of claim 1, wherein the temporary fastener includes a segmented annular body having an axial bore, threads within the bore, a shaft insertable within the bore, and threads on the shaft engageable with the threads within the bore. 8. The method of claim 1, wherein the temporary fastener has a head that is substantially flush with the skin when installed. 9. A method of attaching an aircraft skin to a frame comprising: a. aligning the skin with the structure;b. forming an attachment hole through the skin and structure by boring a transfer hole in the structure that aligns with a pilot hole in the skin;c. applying a liquid shim material to the structure;d. clamping together the skin and structure;e. providing an elongated temporary fastener having a radially expandable body and a head with a diameter that is greater than the diameter of the pilot hole;f. inserting the temporary fastener into the attachment hole and expanding the body to engage the structure;g. forming additional attachment holes in the structure;h. removing the temporary fastener; andi. bolting a permanent fastener into the attachment hole. 10. The method of claim 9, further comprising adding a mask film to the skin bottom surface prior to step (d) and removing the mask film prior to step (i). 11. The method of claim 9, wherein the temporary fastener head has a frusto-conical cross section, the method further comprising tapering the skin pilot hole to match the fastener head frusto-conical shape so that the temporary fastener is flu... | James A. Kelley Rick A. Luepke Lisa M. Vestal Elizabeth J. Kush Michael Loren Hestness Eric C. Patty Jeff Langevin | US | Lockheed Martin Corporation | US | MD Bethesda | LOCKHEED MARTIN CORPORATION | US | 6801 ROCKLEDGE DRIVE | B21D039/00 | B21D039/00 B23P011/00 F16B013/06 | 3 | 3 | B23P0019/04 F16B0019/109 B23P2700/01 B64F0005/10 Y10T0029/49622 Y10T0029/49812 Y10T0029/49947 Y10T0029/49948 Y10T0029/49963 | 029/897.200 | 029/897.200 029/424.000 029/525.010 029/525.020 029/525.110 411/057.100 | - | - | James A. Kelley Rick A. Luepke Lisa M. Vestal Elizabeth J. Kush Michael Loren Hestness Eric C. Patty Jeff Langevin | 7 | US | TX Benbrook TX Fort Worth TX Fort Worth TX Fort Worth TX Fort Worth OH Wauseon TX Fort Worth | Bracewell & Giuliani LLP | - | - | Jermie Cozart | Jermie Cozart | US3426399 US4370081 US4548533 US4610587 US4783228 US4878791 US4934885 US4979281 US5030051 US5927919 US6088897 US6134940 US6158666 US6172374 US6210084 US6302630 US2005/0025602 US2006/0170142 US2008/0216292 | 19 | 0 | 16 | 13 | US08209865 | 1 | 1 | - | US20100308171 | 2010-12-09 | 4 | LOCKHEED MARTIN CORPORATION | Valid | ||||||||||||
52 | EP0405033 | A1 | 1991-01-02 | Engine clip bolt | invention | 89311415.7 | 1989-11-03 | Engine clip bolts fasten parts of aircraft engines together. The clip bolt (10) comprises a bolt (12) and a clip (14). The bolt (12) has a boss (24) which is orbitally swaged by an orbital swaging tool (46) into recesses (44) in the clip (14) while simultaneously swaging bolt material over the clip (14) to develop a torsional interference lock and an axial interference lock, respectively between the clip (14) and the bolt (12). Ihe recesses (44) are arc shaped, have a centre of curvature on a circle having a smaller diameter than a circle that defines lands between the recesses (44), and a number between six and eight. | 1. A method for producing an engine clip bolt comprising the steps of: (a) producing a bolt having a male threaded end at one end, a head larger in diameter than the male threaded end proximate the other end, and a circular in radial cross-section boss extending from the head opposite from the male threaded end and having a diameter smaller than the head; (b) producing a clip having means for engaging structure with which the clip bolt is used to provide a mechanical torsional lock between the structure and the clip bolt, an ear with a thickness less than the length of the boss, and a hole having a perimeter that includes first and second alternating sections, each of the first sections falling on the circumference of a circle that has a radius slightly larger than the radius of the boss, each of the second sections opening onto this circumference, the torsional strength of the clip between the second sections being less than that of the bolt but at least as great as the torque applied to the bolt at a predetermined preload on the structure applied by the bolt and a cooperating nut; (c) placing the boss into the hole of the clip with the ear bearing on the head of the bolt and the boss extending through the clip with a portion of the boss extending beyond the clip; and (d) swaging the boss so that it expands in radius to fill the hole and torsionally locks the clip to the bolt and also expands in radius over the clip to a radius larger than the radius of the circle to axially lock the clip to the bolt; whereby, the clip and the bolt unite into a clip bolt with the clip rotationally and axially coupled to the bolt. | 1. A method for producing an engine clip bolt comprising the steps of: (a) producing a bolt having a male threaded end at one end, a head larger in diameter than the male threaded end proximate the other end, and a circular in radial cross-section boss extending from the head opposite from the male threaded end and having a diameter smaller than the head; (b) producing a clip having means for engaging structure with which the clip bolt is used to provide a mechanical torsional lock between the structure and the clip bolt, an ear with a thickness less than the length of the boss, and a hole having a perimeter that includes first and second alternating sections, each of the first sections falling on the circumference of a circle that has a radius slightly larger than the radius of the boss, each of the second sections opening onto this circumference, the torsional strength of the clip between the second sections being less than that of the bolt but at least as great as the torque applied to the bolt at a predetermined preload on the structure applied by the bolt and a cooperating nut; (c) placing the boss into the hole of the clip with the ear bearing on the head of the bolt and the boss extending through the clip with a portion of the boss extending beyond the clip; and (d) swaging the boss so that it expands in radius to fill the hole and torsionally locks the clip to the bolt and also expands in radius over the clip to a radius larger than the radius of the circle to axially lock the clip to the bolt; whereby, the clip and the bolt unite into a clip bolt with the clip rotationally and axially coupled to the bolt. 2. The method claimed in claim 1 wherein the perimeter of each of the second sections is the arc of a circle having a center on a circle ccncentric with the first mentioned circle and slightly smaller in diameter. 3. The method claimed in claim 1 wherein the swaging step is by orbital swaging. 4. The method claimed in claim 3 wherein each of the second sections has a mouth falling on the circumference of the circle, the aggregate length of the mouths being about equal to the aggregate length of the first sections. 5. The method claimed in claim 4 wherein each of the second sections has a circular perimeter with a radius that falls on a second circle within the first mentioned circle and ccncentric with it. 6. The method claimed in claim 5 wherein there are between six and eight of the second sections. 7. The method claimed in claim 3 wherein the orbital swaging step deforms the boss where it extends away from the clip to a radius at least sufficient to overlie the second sections. 8. A method for manufacturing an engine clip bolt comprising the steps of: (a) heading a bolt to form a head proximate a first end of the bolt and a circular in radial cross- section boss extending axially from the head to the first end, the boss having a diameter smaller than the head;(b) forming a thread on the bolt beginning at the second end of the... | VSI CORPORATION | US | 8463 Higuera Street | VSI CORPORATION | US | - | - | - | B21K025/00 | B21K025/00 F16B035/00 F16B041/00 | 2 | 3 | - | - | - | US 374479 | 1989-06-30 | US | Compton, Clair E. Nicolle, Jean-Paul Andre | 2 | US | Simi Valley California 93065 Canoga Park California 91306 | Enskat, Michael Antony Frank | - | - | 0 | 0 | 36 | 0 | EP0405033A1 | 1 | 1 | - | EP0405033 | 1991-01-02 | 0 | VSI CORPORATION | |||||||||||||||
53 | US07596846 | B2 | 2009-10-06 | Clamping fastener grip length indicator | invention | 11/383172 | 2006-05-12 | A temporary fastener includes a grip length indicator. By machining a flattened area into a body of the temporary fastener, by engraving an scale into the flattened area, and by attaching an indicator dot visible in the groove to a moving part of an internal assembly of the temporary fastener, the grip length of the installed temporary fastener may be read directly on the scale while the temporary fastener applies a clamp-up force to a structure. By using the temporary fastener of the present invention, it is possible to determine a fastener hole length while a temporary fastener is installed. Using the method for determining a fastener grip length of the present invention enables the effective determination of the correct fastener grip length for each particular fastener hole of a large structure, such as an aircraft airframe. | 1. A method for determining a fastener hole length, comprising: forming a temporary fastener that includes a cylindrical-shaped body having a longitudinal axis, and a moveable member that is moveable along said longitudinal axis relative to said cylindrical-shaped body, wherein said moveable member is mounted on a shaft that extends from a rotatable member, and wherein forming said temporary fastener comprises: providing a scale on said cylindrical-shaped body:providing a groove in said cylindrical-shaped body adjacent said scale: andproviding an indicator on said moveable member:inserting said temporary fastener into a fastener hole of a structure having a thickness;applying a clamp-up force to said structure with said temporary fastener, wherein applying said clamp-up force comprises rotating said rotatable member to move said shaft and said moveable member mounted thereon along said longitudinal axis to move said indicator relative to said scale;observing said indicator through said groove; andreading said scale at the position of said indicator to determine a length of said fastener hole. | 1. A method for determining a fastener hole length, comprising: forming a temporary fastener that includes a cylindrical-shaped body having a longitudinal axis, and a moveable member that is moveable along said longitudinal axis relative to said cylindrical-shaped body, wherein said moveable member is mounted on a shaft that extends from a rotatable member, and wherein forming said temporary fastener comprises: providing a scale on said cylindrical-shaped body:providing a groove in said cylindrical-shaped body adjacent said scale: andproviding an indicator on said moveable member:inserting said temporary fastener into a fastener hole of a structure having a thickness;applying a clamp-up force to said structure with said temporary fastener, wherein applying said clamp-up force comprises rotating said rotatable member to move said shaft and said moveable member mounted thereon along said longitudinal axis to move said indicator relative to said scale;observing said indicator through said groove; andreading said scale at the position of said indicator to determine a length of said fastener hole. 2. The method of claim 1, wherein providing a scale on said cylindrical-shaped body comprises: forming said scale on a flattened area of said cylindrical-shaped body; and wherein providing a groove in said cylindrical-shaped body adjacent said scale comprises providing said groove in said flattened area. 3. The method of claim 2, wherein forming said scale on a flattened area comprises: engraving graduation marks into said flattened area. 4. The method of claim 1, further comprising selecting a permanent fastener to be installed permanently according to the determined length of said fastener hole. 5. The method of claim 4, further comprising: removing said temporary fastener from said fastener hole; andinstalling said selected permanent fastener into said fastener hole. 6. The method of claim 1. wherein said shaft comprises a threaded shaft, and wherein said moveable member comprises a threaded moveable member mounted on said threaded shaft. 7. A method for determining a fastener grip length of a fastener used in an aircraft airframe assembly, comprising: providing a scale on a cylindrical-shaped body of a temporary fastener;providing a groove in said body adjacent said scale;providing an indicator on a moving part of an internal assembly of said temporary fastener, wherein said moving part comprises a moveable member that is mounted on a shaft that extends from a rotatable member;inserting bearing wires of said temporary fastener into a fastener hole of said aircraft airframe assembly having an inner mold line and an outer mold line;positioning said cylindrical-shaped body on said outer mold line;retracting said bearing wires by rotating said rotatable member to move said shaft and said moveable member mounted thereon along a longitudinal axis of said cylindrical-shaped body to move said indicator relative to said scale until said bearing wires contac... | Leslie A. Hoeckelman | US | The Boeing Company | US | IL Chicago | The Boeing Company | US | - | B23Q017/00 | B23Q017/00 E01B003/00 F16B013/06 F16B031/02 G01B005/20 G01B003/12 G09F009/00 H03J001/00 | 6 | 8 | F16B0019/109 Y10T0029/4978 | 029/407.100 | 029/407.100 033/554.000 033/679.100 033/774.000 033/806.000 116/259.000 116/321.000 269/048.300 269/048.400 411/014.000 411/054.000 | - | - | Leslie A. Hoeckelman | 1 | US | MO O'Fallon | Yee & Associates, P.C. Dennis R. Plank | - | - | David P Bryant | David P Bryant Alexander P Taousakis | US517073 US536676 US1375747 US1383340 US2241609 US2293411 US2294013 US2295783 US2317315 US2354480 US2365787 US2439531 US2446030 US2484458 US2579956 US2755541 US2894331 US3000086 US3016619 US3144804 US3144805 US3225447 US3260151 US3289525 US3426399 US3568562 US3751083 US3869801 US4033043 US4237612 US4399685 US4537542 US4548533 US4763459 US4787274 US4858607 US4876800 US4892449 US4899431 US4934885 US4936726 US4972603 US5048805 US5095638 US5164154 US5228731 US5240361 US5439310 US5469629 US5538381 US5702401 US5927919 US6017136 US6056283 US6196779 US6346114 US6450976 US6508012 US6755407 US6827345 | 60 | 0 | 19 | 6 | US07596846 US07070375 | 2 | 1 | - | US20060193709 | 2006-08-31 | 1 | THE BOEING COMPANY | Overdue | ||||||||||||
54 | US09376217 | B2 | 2016-06-28 | Jig for forming sealant layer for lightning protection fastener, method for forming sealant layer for lightning protection fastener, lightning protection fastener, and wing of aircraft | invention | 14/166278 | 2014-01-28 | To provide a jig for forming a sealant layer for a lightning protection fastener which enables to quickly and accurately obtain a sealant layer having a required thickness. A guide jig 30 is used to form a sealant layer 29 around a fastener member 24 that passes through and fastens a plurality of members constituting an airframe of an aircraft, the jig including: a cup 31 including a cavity 33 to be filled with an uncured sealant 28; and a guide that is provided within the cavity 33 and engaged with the fastener member 24 so as to match a center axis of the cavity 33 with a center axis of the fastener member 24. | 1. A method for producing a lightning protection fastener with an insulating sealant layer, the lightning protection fastener comprising:a fastener member that passes through and fastens a plurality of members constituting an airframe of an aircraft; andan insulating sealant layer that is formed around the fastener member,with a jig comprising:a cup including a cavity to be filled with an uncured sealant; anda guide that is provided within the cavity and engaged with the fastener member of the lightning protection fastener so as to match a center axis of the cavity with a center axis of the fastener member,performing the method comprising:a step A of filling the cavity of the cup with the sealant; anda step B of mounting the cup filled with the sealant to the fastener member while the guide is engaged with the fastener member so as to match the center axis of the cavity with the center axis of the fastener member. | 1. A method for producing a lightning protection fastener with an insulating sealant layer, the lightning protection fastener comprising:a fastener member that passes through and fastens a plurality of members constituting an airframe of an aircraft; andan insulating sealant layer that is formed around the fastener member,with a jig comprising:a cup including a cavity to be filled with an uncured sealant; anda guide that is provided within the cavity and engaged with the fastener member of the lightning protection fastener so as to match a center axis of the cavity with a center axis of the fastener member,performing the method comprising:a step A of filling the cavity of the cup with the sealant; anda step B of mounting the cup filled with the sealant to the fastener member while the guide is engaged with the fastener member so as to match the center axis of the cavity with the center axis of the fastener member. 2. The method according to claim 1, further comprising a step C of filling an airspace formed by the cup and the guide with an uncured sealant after the step B. 3. The method according to claim 1, wherein before the step B, a region around a portion of the fastener member to be insulated is coated with another sealant having lower viscosity than the sealant to be fed in the cup. | MITSUBISHI AIRCRAFT CORPORATION | JP | MITSUBISHI AIRCRAFT CORPORATION | JP | Aichi | MITSUBISHI AIRCRAFT CORPORATION | JAPAN | 2-15, OYE-CHO, MINATO-KU, NAGOYA-SHI | B64D045/02 | B64D045/02 F16B037/14 F16B033/00 B23P011/00 | 3 | 4 | B64D0045/02 | B64D0045/02 B23P0011/00 F16B0033/004 F16B0037/14 | B64D0045/02 B23P0011/00 F16B0033/004 F16B0037/14 | - | - | 2013-14092 | 2013-01-29 | JP | Hideo Yamakoshi Yuji Asahara Wataru Nishimura Takeyasu Tarumi Noritomo Takata Jun Kawaguchi Hiroshi Rikukawa Tomonori Okumura Kengo Nomiya | 9 | JP | Aichi Aichi Tokyo Tokyo Tokyo Tokyo Tokyo Aichi Tokyo | Pearne & Gordon LLP | - | - | Alexander P Taousakis | Alexander P Taousakis | US5749670 US2009/0147429 US2012/0074257 US2012/0155987 US2013/0153136 US2013/0186552 US2014/0091175 US2014/0209736 US2014/0234050 US2015/0184688 US2015/0271960 | 11 | JP2010-254287 | 1 | 11 | 5 | JP6270317 US09376217 | 2 | 2 | - | US20150298819 | 2015-10-22 | 9 | MITSUBISHI AIRCRAFT CORPORATION | Valid | ||||||||
55 | WO2020046161 | A1 | 2020-03-05 | HIGH STRENGTH FASTENER STOCK OF WROUGHT TITANIUM ALLOY AND METHOD OF MANUFACTURING THE SAME | invention | RU2018000578 | 2018-08-31 | This invention generally relates to the field of nonferrous metallurgy, namely to titanium alloy materials with specified mechanical properties for manufacturing the aircraft fasteners. A stock for high strength fastener is manufactured from wrought titanium alloy containing, in weight percentages, 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 tol.5 Cr, 0.05 to 0.5 Zr, 0.15 to 0.3 O, 0.05 max. N, 0.08 max. C, 0.25 max. Si, balance titanium and inevitable impurities, having the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.5, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq =[Al]+[O]x l0+ [Zr]/6; [Mo]eq =[Mo]+[V]/1.5+[Cr]xl.25+[Fe]x2.5. A manufacturing method for a stock for high strength fastener includes melting of titanium alloy ingot, production of forged billed from ingot at beta and/or alpha-beta phase field temperatures, hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a round stock, subsequent annealing of a rolled stock at a temperature of 550°C to 705°C (1022°F to 1300°F) for at least 0.5 hour followed by drawing to produce a wire with diameter up to 10 mm (0.394 inches) and subsequent annealing at a temperature of 550°C to 705°C (1022°F to 1300°F) for at least 0.5 hour. A technical result is production of a titanium alloy stock for high strength fastener having high ultimate tensile strength and double shear strength while maintaining a high level of plastic properties in the annealed condition.12 claims, 5 illustrations. | CLAIMS 1. A high strength fastener stock made of wrought titanium alloy consisting of, in weight percentages: 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 to 1.5 Cr, 0.05 to 0.5 Zr, 0.2 to 0.3 O, 0.05 max. N, 0.08 mqx. C, 0.25 max. Si, and balance titanium and inevitable impurities, characterized by the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.5, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq = [Al]+[0]x 10+ [Zr]/6; [Mo]eq = [Mo]+[V]/1.5+[Cr]xl.25+[Fe]x2.5. 2. A fastener stock made in the form of a round rolled bar with diameter of 8 mm to 31.75 mm (0.315 inches to 1.25 inches). 3. A fastener stock made in the form of a round rolled bar with diameter over 31.75 mm to 101.6 mm (1.25 inches to 4.0 inches). 4. A fastener stock under claim 1 made in the form of a round wire with diameter up to 10 mm (0.394 inches) by drawing. 5. A fastener stock under claims 1, 2, having ultimate tensile strength in the annealed condition of 165 ksi (1138 MPa) minimum. 6. A fastener stock under claims 1, 2, having double shear strength in the annealed condition of 100 ksi (689 MPa) minimum. 7. A fastener stock under claims 1, 3, having ultimate tensile strength in the annealed condition of 160 ksi (1103 MPa) minimum. 8. A fastener stock under claims 1, 3, having double shear strength in the annealed condition of 95 ksi (655 MPa) minimum. 9. A fastener stock under claims 1, 4, having ultimate tensile strength in the annealed condition of 168 ksi (1158 MPa) minimum. 10. A fastener stock under claims 1, 4, having double shear strength in the annealed condition of 103 ksi (710 MPa) minimum. 11. A manufacturing method for a fastener stock under claims 1, 2, 3, 5, 6, 7, 8, which includes melting of titanium alloy ingot consisting of, in weight percentages: 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe,· 0.3 to 1.5 Cr, 0.05 to 0.5 Zr, 0.2 to 0.3 O, 0.05 max. N, 0.08 max. C, 0.25 max. Si, and balance titanium and inevitable impurities, characterized by the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.0, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq = [Al]+[O]xl0+ [Zr]/6; [Mo]eq = [Mo]+[V]/1.5+[Cr]xl.25+[Fe]x2.5, conversion of the ingot to a forged billet at beta and/or alpha-beta phase field temperatures, machining of forged billets, hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a rolled stock, subsequent annealing of a rolled stock at a temperature of 550°C to 705°C (1022°F to 1300°F) for at least 0.5 hour. 12. A manufacturing method for a fastener stock under claims 1, 4, 9, 10, which includes melting of titanium alloy ingot consisting of, in weight percentages: 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 to 1.5... | -->CLAIMS 1. A high strength fastener stock made of wrought titanium alloy consisting of, in weight percentages: 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 to 1.5 Cr, 0.05 to 0.5 Zr, 0.2 to 0.3 O, 0.05 max. N, 0.08 mqx. C, 0.25 max. Si, and balance titanium and inevitable impurities, characterized by the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.5, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq = [Al]+[0]x 10+ [Zr]/6; [Mo]eq = [Mo]+[V]/1.5+[Cr]xl.25+[Fe]x2.5. 2. A fastener stock made in the form of a round rolled bar with diameter of 8 mm to 31.75 mm (0.315 inches to 1.25 inches). 3. A fastener stock made in the form of a round rolled bar with diameter over 31.75 mm to 101.6 mm (1.25 inches to 4.0 inches). 4. A fastener stock under claim 1 made in the form of a round wire with diameter up to 10 mm (0.394 inches) by drawing. 5. A fastener stock under claims 1, 2, having ultimate tensile strength in the annealed condition of 165 ksi (1138 MPa) minimum. 6. A fastener stock under claims 1, 2, having double shear strength in the annealed condition of 100 ksi (689 MPa) minimum. 7. A fastener stock under claims 1, 3, having ultimate tensile strength in the annealed condition of 160 ksi (1103 MPa) minimum. 8. A fastener stock under claims 1, 3, having double shear strength in the annealed condition of 95 ksi (655 MPa) minimum. 9. A fastener stock under claims 1, 4, having ultimate tensile strength in the annealed condition of 168 ksi (1158 MPa) minimum. -->10. A fastener stock under claims 1, 4, having double shear strength in the annealed condition of 103 ksi (710 MPa) minimum. 11. A manufacturing method for a fastener stock under claims 1, 2, 3, 5, 6, 7, 8, which includes melting of titanium alloy ingot consisting of, in weight percentages: 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe,· 0.3 to 1.5 Cr, 0.05 to 0.5 Zr, 0.2 to 0.3 O, 0.05 max. N, 0.08 max. C, 0.25 max. Si, and balance titanium and inevitable impurities, characterized by the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.0, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq = [Al]+[O]xl0+ [Zr]/6; [Mo]eq = [Mo]+[V]/1.5+[Cr]xl.25+[Fe]x2.5, conversion of the ingot to a forged billet at beta and/or alpha-beta phase field temperatures, machining of forged billets, hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a rolled stock, subsequent annealing of a rolled stock at a temperature of 550°C to 705°C (1022°F to 1300°F) for at least 0.5 hour. 12. A manufacturing method for a fastener stock under claims 1, 4, 9, 10, which includes melting of titanium alloy ingot consisting of, in weight percentages: 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 ... | THE BOEING COMPANY PUBLIC STOCK COMPANY VSMPO-AVISMA CORPORATION | US RU | 100 North Riverside Plaza,IL, Chicago, 60606,60606,US Parkovaya St., 1,Verkhnaya Salda,Sverdlovsk Region, 624760,624760,RU | THE BOEING COMPANY PUBLIC STOCK COMPANY VSMPO-AVISMA CORPORATION | US RU | - | - | - | - | C22F001/18 | C22F001/18 C22C014/00 F16B033/00 | 3 | 3 | - | - | - | - | - | - | - | - | - | - | - | MITROPOLSKAYA, Natalia Georgievna LEDER, Michael Ottovich PUZAKOV, Igor Yurievich ZAITSEV, Alexey Sergeevich TARENKOVA, Natalia Yuryevna BRIGGS, Robert David | 6 | RU US | Gazetny pereulok, 17,Moscow, 125009,125009,RU Voronova street, 9,Verkhnyaya Salda, 624760,624760,RU Engels street, 76,Verkhnyaya Salda, 624760,624760,RU Lenina street, 5,Verkhnaya Salda,Sverdlovsk Region, 624760,624760,RU Engels street, 99/3,Verkhnyaya Salda, 624760,624760,RU 5524 S. 299 CT,Auburn, WA 98001,98001,US | NILOVA, Maria Innokentievna | Patentica Box 1125,St.Petersburg, 190000,190000,RU | - | - | - | - | - | 0 | - | 0 | - | 7 | 0 | US11920218 JP7223121 EP3844316A1 CN112823218A WO2020046161 BR112021003069A2 CA3110188C CA3110188A1 BR112021003069B1 | 9 | 7 | - | WO2020046161 | 2020-03-05 | 13 | THE BOEING COMPANY,PUBLIC STOCK COMPANY VSMPO-AVISMA CORPORATION | |||
56 | US09759251 | B2 | 2017-09-12 | Barrel nut with stress reduction features | invention | 14/469640 | 2014-08-27 | A barrel nut with features for reducing tensile stresses under heavy load within the barrel nut has a partial-cylindrical body having a first planar end surface and a second planar end surface. A threaded bore extends through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface. At least one groove is formed in each of the first planar end surface and the second planar end surface, the groove having a rounded surface extending at least a part of a distance between a curved upper surface of the partial-cylindrical body to a bottom surface thereof in a direction substantially parallel to the central axis of the threaded bore. | 1. A barrel nut comprising a one-piece partial-cylindrical body having a first planar end surface and a second planar end surface, a threaded bore extending through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface, and at least one groove partially recessed into each of the first planar end surface and the second planar end surface extending at least a part of a length of the partial-cylindrical body in a direction substantially parallel to the central axis of the threaded bore. | 1. A barrel nut comprising a one-piece partial-cylindrical body having a first planar end surface and a second planar end surface, a threaded bore extending through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface, and at least one groove partially recessed into each of the first planar end surface and the second planar end surface extending at least a part of a length of the partial-cylindrical body in a direction substantially parallel to the central axis of the threaded bore. 2. The barrel nut of claim 1, wherein a surface of the at least one groove is rounded. 3. The barrel nut of claim 2, wherein a bottom surface of the partial-cylindrical body comprises a flange surrounding the threaded bore, the flange being raised above the bottom surface and extending from a circumferential edge of the threaded bore to a side edge of the bottom surface. 4. The barrel nut of claim 3, wherein the at least one groove in each of the first planar end surface and the second planar end surface is aligned with the central axis of the threaded bore such that the at least one groove is positioned on a center line of each of the first planar end surface and the second planar end surface. 5. The barrel nut of claim 3, wherein each of the first planar end surface and the second planar end surface comprises two grooves extending in a direction substantially parallel to the central axis from a curved upper surface to a non-curved bottom surface. 6. The barrel nut of claim 3, wherein the flange at the side edge extends a curved upper surface of the partial-cylindrical body below the bottom surface in a central area, the central area having a length substantially equal to a diameter of the threaded bore. 7. The barrel nut of claim 1, wherein the at least one groove in each of the first planar end surface and the second planar end surface is aligned with the central axis of the threaded bore such that the at least one groove is positioned on a center line of each of the first planar end surface and the second planar end surface. 8. The barrel nut of claim 1, wherein the threaded bore comprises a plurality of threads extending from a bottom surface to a point below a curved upper surface of the partial-cylindrical body, a distance between the point and the curved upper surface being about 2% to about 10% of a total length of the threads. 9. The barrel nut of claim 1, wherein the at least one groove has a rounded surface recessed into the first planar end and the second planar end of the one-piece partial-cylindrical body. 10. The barrel nut of claim 9, wherein the rounded surface has a radius in the range of about 0.015 to 0.15 times a diameter of the barrel nut. 11. A barrel nut comprising a partial-cylindrical body having a first planar end surface and a second planar end surface, a threaded bore extending through the partial-cylindrical body with a central axis substantial... | The Boeing Company | US | The Boeing Company | US | IL Chicago | THE BOEING COMPANY | US | - | F16B037/08 | F16B037/08 F16B031/06 B23G009/00 F16B037/04 | 2 | 3 | - | F16B0031/06 | F16B0031/06 B23G0009/006 F16B0037/047 | F16B0031/06 B23G0009/006 F16B0037/047 | - | - | - | - | - | - | - | Adrian Stanescu Constantine Kostakis Michael Ronald Butcher | 3 | US | WA Maple Valley WA Kirkland WA Issaquah | Ostrager Chong Flaherty & Broitman PC | - | - | Gary Estremsky | Gary Estremsky | US2688355 US3021162 US3205927 US3208496 US3322177 US4119130 US4861207 US4886407 US5779412 US8142123 US2010/0244342 | 11 | - | 0 | Printouts from http://www.shur-lok.com/ and http://www.shur-lok.com/solutions/barrel/ . . . showing barrel nuts, printed Jun. 26, 2014.;Printouts from http://www.theharwarehut.com/catalog-product-specs.php?p;ref=302759, showing Selby ¾″ Steel Barrel Nut, printed Jun. 26, 2014.;Search Report dated Jun. 2, 2016 in related Canadian Patent Application No. 2,892,723. | 11 | 3 | US10520002 US09759251 AU2015202597B2 RU2015117927A3 RU2678886C2 AU2015202597A1 CA2892723A1 RU2015117927A BR102015018911B1 BR102015018911A2 CA2892723C | 11 | 5 | - | US20160061250 | 2016-03-03 | 9 | THE BOEING COMPANY | Valid | ||||
57 | CN103016494 | A | 2013-04-03 | 鉚接螺母與板件的連接結構及其連接方法 | invention | CN201210594385.X | 2012-12-31 | 本發明屬於機械連接件技術領域，涉及鉚接螺母與板件的連接結構及其連接方法，所述的連接結構是：設有內螺紋的鉚接螺母包括一體式結構的螺母帽頭以及鉚接部，所述鉚接部由螺母帽頭的根部向外依次設置有縮頸形成的第一臺階和第二臺階，靠近螺母帽頭一側的第一臺階的外圓柱面上設置有花鍵，第二臺階內側的外圓柱面上設置有環形的嵌入槽，鉚接部卡接在板件的通孔或盲孔內形成過盈配合，所述的連接方法是：用衝床將鉚接螺母的鉚接部壓入板件的通孔或盲孔內形成過盈配合，優點是：使用本發明與板件連接的同心度好，連接過程的各種機械及化學性能不變，而且連接牢固，應用於航空、鐵路、車輛等各類重載荷的連接。 | 1.鉚接螺母與板件的連接結構，包括鉚接螺母及板件，其特徵在於：設有內螺紋的鉚接螺母包括一體式結構的螺母帽頭以及鉚接部，所述鉚接部由螺母帽頭的根部向外依次設置有縮頸形成的第一臺階和第二臺階，靠近螺母帽頭一側的第一臺階的外圓柱面上設置有花鍵，第二臺階內側的外圓柱面上設置有環形的嵌入槽，所述的鉚接部卡接在板件上設置的通孔或盲孔內，板件與鉚接螺母的第一臺階、花鍵及嵌入槽過盈配合。 | 1.鉚接螺母與板件的連接結構，包括鉚接螺母及板件，其特徵在於：設有內螺紋的鉚接螺母包括一體式結構的螺母帽頭以及鉚接部，所述鉚接部由螺母帽頭的根部向外依次設置有縮頸形成的第一臺階和第二臺階，靠近螺母帽頭一側的第一臺階的外圓柱面上設置有花鍵，第二臺階內側的外圓柱面上設置有環形的嵌入槽，所述的鉚接部卡接在板件上設置的通孔或盲孔內，板件與鉚接螺母的第一臺階、花鍵及嵌入槽過盈配合。 2.所述螺母帽頭的外徑大於花鍵的外徑，花鍵的外徑大於第二臺階的外徑，花鍵的內徑大於或等於第一臺階的外徑，花鍵的外徑大於板件的通孔或盲孔的內徑。 3.所述花鍵的齒形為三角形或梯形。 4.所述嵌入槽為三角形槽或矩形槽。 5.所述三角形槽的外側直徑大、內側直徑小。 6.所述鉚接螺母是用金屬材料製成的。 7.如權利要求1所述的鉚接螺母與板件的連接結構的連接方法，其特徵在於：包括如下步驟： (1)製作所述的鉚接螺母及板件上的通孔或盲孔，使通孔或盲孔的內徑與鉚接螺母的第二臺階間隙配合； (2)將板件放在衝床的專用工作臺上，將鉚接螺母的第二臺階穿入板件的通孔或盲孔內，並使鉚接螺母的螺母帽頭朝上； (3)用紅外線定心裝置定心：啟動紅外線定心裝置，調整鉚接螺母的螺母帽頭的中點對正紅外線定心裝置發出的紅外線的中心點，紅外線的中心點與衝床的沖頭的軸線重合； (4)啟動衝床，衝床帶動沖頭將鉚接螺母的第一臺階、花鍵壓入強行壓入板件的通孔或盲孔內，同時板件的通孔或盲孔多出鉚接螺母的第一臺階及花鍵的部分變形材料流入到嵌入槽內，使板件與螺母的第一臺階、花鍵及嵌入槽形成過盈配合。 8.所述的步驟（2)也可以是這樣的：先將鉚接螺母的第二臺階插入板件的通孔或盲孔內，再將插入鉚接螺母的板件放在衝床的專用工作臺上，並使鉚接螺母的螺母帽頭朝上。 9.所述衝床的具體結構是：在機架上懸空設置由氣缸，氣缸的活塞杆向下伸出並在其端部安裝有所述的沖頭，沖頭的下側設置有工作臺，所述的氣缸由氣源供氣、由電磁閥控制其工作，所述衝床的壓力即小於鉚接螺母的變形壓力，又可將鉚接螺母的第一臺階及花鍵部分壓入板件的通孔或盲孔內。 10.所述的工作臺上設置有板件夾具。 | 浙江天成自控股份有限公司 | CN | 317200 浙江省台州市天臺縣西工業區 | 浙江天成自控股份有限公司 | CN | 浙江 | - | - | - | F16B037/06 | F16B037/06 B21D039/00 | 2 | 2 | - | - | - | 陳邦銳 | 1 | CN | 苑新民 台州藍天智慧財產權代理有限公司 33229 | - | - | 0 | 0 | 13 | 3 | CN103016494A | 1 | 1 | - | CN103016494 | 2013-04-03 | 7 | 浙江天成自控股份有限公司 | Overdue | |||||||||||||||||
58 | WO2021222862 | A1 | 2021-11-04 | MULTI-PIECE FASTENER INCLUDING A LOCKBOLT COLLAR ASSEMBLY AND METHOD OF FASTENING | invention | US2021030344 | 2021-04-30 | Non-limiting embodiments of a multi-piece fastener and a fastening method are disclosed. The multi-piece fastener comprises a fastening collar and a pin. The fastening collar comprises a first collar end, a second collar end, and an inner collar surface extending from the first collar end to the second collar end. The inner collar surface comprises a first lock region and defines a collar cavity. The pin is configured to be at least partially received by the collar cavity. The pin comprises a first pin end, a second pin end, and a shank extending intermediate the first pin end and the second pin end. The shank comprises a second lock region configured to engage the first lock region to form an interference fit between the fastening collar and the pin when the pin is received in the collar cavity. The fastening collar is configured to be deformed onto the shank. | CLAIMS What is claimed is: 1. A multi-piece fastener comprising: a fastening collar comprising a first collar end, a second collar end, and an inner collar surface extending from the first collar end to the second collar end and comprising a first lock region, wherein the inner collar surface defines a collar cavity; and a pin configured to be at least partially received by the collar cavity, the pin comprising a first pin end, a second pin end, and a shank extending intermediate the first pin end and the second pin end, wherein the shank comprises a second lock region configured to engage the first lock region to form an interference fit between the fastening collar and the pin when the pin is received in the collar cavity, and wherein the fastening collar is configured to be deformed onto the shank. 2. The multi -piece fastener of claim 1, wherein at least one of the first lock region and the second lock region defines a taper in a range of 0.5 degrees to 15 degrees relative to a longitudinal axis of the fastening collar. 3. The multi -piece fastener of claim 1, wherein at least one of the first lock region and the second lock region comprises a frustoconical shape. 4. The multi -piece fastener of claim 1, wherein at least one of the first lock region and the second lock region defines a curve relative to a longitudinal axis of the fastening collar. 5. The multi -piece fastener of claim 1, wherein a dimension of the collar cavity decreases along the first lock region in an axial direction towards the second collar end. 6. The multi -piece fastener of claim 1, wherein a diameter of the collar cavity in the first lock region is less than a diameter of the collar cavity adjacent to the first lock region. 7. The multi -piece fastener of claim 1, wherein a diameter of the shank decreases in an axial direction towards the first pin end. 8. The multi-piece fastener of claim 1, wherein the second lock region is substantially cylindrical. 9. The multi -piece fastener of claim 1, wherein the first pin end comprises a pull-region. 10. The multi -piece fastener of claim 1, wherein the shank comprises at least one of a generally smooth region, an annular shoulder, a groove, and a threaded region. 11. The multi -piece fastener of claim 1, wherein the multi -piece fastener is configured to be installed in a bore in a structure and wherein the structure is configured as at least one of an aerospace part or component, an automotive part or component, a transportation part or component, and a building and construction part or component. 12. The multi-piece fastener of claim 1, wherein a diameter of the shank is in a range of 0.06 inches to 4 inches. 13. A lockbolt comprising the multi -piece fastener of claim 1. 14. A method for fastening, the method comprising: inserting a first pin end of a multi-piece fastener into a bore in a structure, the multi piece fastener comprising a fastening collar comprising a first collar end, a second collar end, and an inner co... | -->CLAIMS What is claimed is: 1. A multi-piece fastener comprising: a fastening collar comprising a first collar end, a second collar end, and an inner collar surface extending from the first collar end to the second collar end and comprising a first lock region, wherein the inner collar surface defines a collar cavity; and a pin configured to be at least partially received by the collar cavity, the pin comprising a first pin end, a second pin end, and a shank extending intermediate the first pin end and the second pin end, wherein the shank comprises a second lock region configured to engage the first lock region to form an interference fit between the fastening collar and the pin when the pin is received in the collar cavity, and wherein the fastening collar is configured to be deformed onto the shank. 2. The multi -piece fastener of claim 1, wherein at least one of the first lock region and the second lock region defines a taper in a range of 0.5 degrees to 15 degrees relative to a longitudinal axis of the fastening collar. 3. The multi -piece fastener of claim 1, wherein at least one of the first lock region and the second lock region comprises a frustoconical shape. 4. The multi -piece fastener of claim 1, wherein at least one of the first lock region and the second lock region defines a curve relative to a longitudinal axis of the fastening collar. 5. The multi -piece fastener of claim 1, wherein a dimension of the collar cavity decreases along the first lock region in an axial direction towards the second collar end. 6. The multi -piece fastener of claim 1, wherein a diameter of the collar cavity in the first lock region is less than a diameter of the collar cavity adjacent to the first lock region. -->7. The multi -piece fastener of claim 1, wherein a diameter of the shank decreases in an axial direction towards the first pin end. 8. The multi-piece fastener of claim 1, wherein the second lock region is substantially cylindrical. 9. The multi -piece fastener of claim 1, wherein the first pin end comprises a pull-region. 10. The multi -piece fastener of claim 1, wherein the shank comprises at least one of a generally smooth region, an annular shoulder, a groove, and a threaded region. 11. The multi -piece fastener of claim 1, wherein the multi -piece fastener is configured to be installed in a bore in a structure and wherein the structure is configured as at least one of an aerospace part or component, an automotive part or component, a transportation part or component, and a building and construction part or component. 12. The multi-piece fastener of claim 1, wherein a diameter of the shank is in a range of 0.06 inches to 4 inches. 13. A lockbolt comprising the multi -piece fastener of claim 1. 14. A method for fastening, the method comprising: inserting a first pin end of a multi-piece fastener into a bore in a structure, the multi piece fastener comprising a fastening collar comprising a first collar end, a second collar end, and an in... | HOWMET AEROSPACE INC. | US | 201 Isabella Street,Pittsburgh, Pennsylvania 15212-5858,15212-5858,US | HOWMET AEROSPACE INC. | US | - | - | - | - | F16B019/05 | F16B019/05 B21J015/02 | 2 | 2 | - | - | - | - | - | - | - | - | 63/018,687 | 2020-05-01 | US | WILCOX, Robert B. | 1 | US | 354 Elm Grove Circle,McGregor, Texas 76657,76657,US | SOVESKY, Robert J. et al. | K&L Gates LLP,210 Sixth Avenue,K&L Gates Center,Pittsburgh, Pennsylvania 15222-2613,15222-2613,US | - | - | - | - | - | 0 | - | 0 | - | 4 | 0 | US20230114567 EP4143447A1 WO2021222862 AU2021264070A1 AU2021264070B2 | 5 | 4 | - | WO2021222862 | 2021-11-04 | 16 | HOWMET AEROSPACE INC. | |||
59 | US20100221064 | A1 | 2010-09-02 | FASTENER JOINT WITH SEALING GASKET | invention | 12/680911 | 2008-10-20 | A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall.;The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar. | 1. A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall | 1. A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall 2. The joint of claim 1 wherein the gasket further comprises a reinforcing element. 3. The joint of claim 2 wherein the reinforcing element comprises a fabric. 4. The joint of claim 1 wherein the bore comprises a tapered opening and the head of the fastener comprises a tapered head which is received in the tapered opening. 5. The joint of claim 1 wherein the polysulphide material forming the gasket is loaded with conductive particles. 6. A gasket for sealing a fastener joint, the gasket comprising a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant with a region of increased thickness positioned towards the inner periphery of the ring. 7. The gasket of claim 6 wherein the sealing material further comprises a reinforcing element. 8. The gasket of claim 7 wherein the ring comprises a matrix-rich region which contains a lower than average density of reinforcement. 9. The gasket of claim 8 wherein the matrix-rich region includes an outer surface of the ring. 10. The gasket of claim 7 wherein the reinforcing element comprises a fabric. 11. The gasket of claim 10 wherein the region of increased thickness extends around the entire circumference of the ring. 12. The gasket of claim 6 wherein the region of increase thickness includes a matrix-rich protrusion which contains a lower than average density of reinforcement. 13. The gasket of claim 6 wherein the polysulphide sealing material is loaded with conductive particles. 14. A method of manufacturing a joint, the method comprising: mounting a gasket on a fastener; the fastener comprising a head and a shaft protruding from the head, and the gasket comprising an at least partially cured polysulphide sealing material;inserting the shaft of the fastener through a first component and at least partially through a second component until the gasket engages the first component; andcompressing the gasket between the head of the fastener and the first component whereby the sealing material flows along the shaft of the fastener and forms a collar between the shaft of the fastener and the first component. 15. The method of claim 14 wherein the gasket comprises a region of increased thickness positioned towards the inner periphery of the gasket which flows along the shaft of the fastener. 16. The method of claim 15 wherein the region of increased thickness extends around the entire circumference of the gasket. 17. The method of claim 14 wherein the gasket further compri... | Colin John West David Alistair Sutton | GB | AIRBUS UK LIMITED | GB | Bristol | AIRBUS UK LIMITED | UNITED KINGDOM | NEW FILTON HOUSE, FILTON | F16J015/06 | F16J015/06 B23P011/00 F16B005/00 | 3 | 3 | F16B0019/008 F16B0033/004 F16B0043/001 F16J0015/14 F16B2200/60 Y10T0029/49947 | 403/288.000 | 403/288.000 029/525.010 277/650.000 277/651.000 | - | - | 0720705.3 | 2007-10-23 | GB | Colin John West David Alistair Sutton | 2 | GB | Bristol Bristol | - | - | - | 0 | 0 | 17 | 10 | US09568035 EP2201272B1 US20130125374 US20100221064 WO2009053734 ATE524679T1 GB0720705D0 | 7 | 5 | - | US20100221064 | 2010-09-02 | 3 | AIRBUS UK LIMITED | Overdue | ||||||||||||
60 | US09649682 | B2 | 2017-05-16 | Method of assembling a structure using highly-deformable titanium and titanium-alloy one-piece fasteners | invention | 14/569031 | 2014-12-12 | A method of forming a fastener may include inserting a blank precursor into a bore of a forming die having an enlarged bore portion. The method may further include applying a first axial compression force to the blank precursor, and forming a cold-worked head section and an enlarged shank portion on the blank precursor corresponding to the enlarged bore portion. The enlarged shank portion may have a nominal shank portion extending therefrom. The method may additionally include inserting the nominal shank portion into a bore of a final reduction die, applying a second axial compression force to the enlarged shank portion, and urging the enlarged shank portion into the bore of the final reduction die. The method may also include reducing a cross-sectional area of the enlarged shank portion by approximately 2 to 5 percent to form a cold-worked shank section. | 1. A method of assembling a structure, comprising the steps of: providing a semi-tubular fastener formed from a semi-tubular blank precursor having a hollow tubular cavity, extending at least partially into the semi-tubular blank precursor and having an ultra-fine grain titanium or titanium-alloy composition having an average grain size of less than approximately 10 microns, the semi-tubular fastener having a head and a shank terminating at a tail end portion, the head comprising a cold-worked head section, the shank including a cold-worked shank section and a ductile shank section extending from the cold-worked shank section to the tail end portion, the cold-worked shank section being formed by reducing a cross-sectional area of an enlarged shank portion by approximately 2 to 5 percent while a shaft of an insert tool is inserted into the hollow tubular cavity, the cold-worked head section and the cold-worked shank section having a higher strength than the ductile shank section;installing the semi-tubular fastener in a hole of the structure; andupsetting the tail end portion of the ductile shank section. | 1. A method of assembling a structure, comprising the steps of: providing a semi-tubular fastener formed from a semi-tubular blank precursor having a hollow tubular cavity, extending at least partially into the semi-tubular blank precursor and having an ultra-fine grain titanium or titanium-alloy composition having an average grain size of less than approximately 10 microns, the semi-tubular fastener having a head and a shank terminating at a tail end portion, the head comprising a cold-worked head section, the shank including a cold-worked shank section and a ductile shank section extending from the cold-worked shank section to the tail end portion, the cold-worked shank section being formed by reducing a cross-sectional area of an enlarged shank portion by approximately 2 to 5 percent while a shaft of an insert tool is inserted into the hollow tubular cavity, the cold-worked head section and the cold-worked shank section having a higher strength than the ductile shank section;installing the semi-tubular fastener in a hole of the structure; andupsetting the tail end portion of the ductile shank section. 2. The method of claim 1 wherein the cold-worked shank section is formed by reducing a cross-sectional area of the enlarged shank portion by approximately 3.5 percent. 3. The method of claim 1 wherein: the structure has a thickness, the cold-worked shank section having a length that is substantially similar to the thickness of the structure. 4. The method of claim 1 wherein the semi-tubular fastener is a protruding head fastener and the step of installing the protruding head fastener comprises: installing the protruding head fastener in a non-countersunk hole of the structure. 5. The method of claim 1 wherein the semi-tubular fastener is a flush head fastener and the step of installing the flush head fastener comprises: installing the flush head fastener in a countersunk hole of the structure. 6. The method of claim 1 wherein: the ductile shank section has a level of ductility that is higher than the level of ductility of the cold-worked head section and the cold-worked shank section. 7. The method of claim 1 further comprising the step of: providing the semi-tubular fastener coated with a corrosion-resistant, curable organic coating material. 8. The method of claim 1 wherein the step of installing the semi-tubular fastener comprises: installing the semi-tubular fastener in an aircraft structure. 9. The method of claim 1 wherein: the ductile shank section of the semi-tubular fastener has a ductility value of at least 10 percent elongation along a longitudinal axis of the semi-tubular fastener prior to fracturing or failure of the ductile shank section. 10. The method of claim 1 wherein: the ductile shank section of the semi-tubular fastener has a ductility level represented by a reduction in cross-sectional area of at least approximately 30 percent prior to fracturing or failure of the ductile shank section. 11. The method of claim 1 wh... | The Boeing Company | US | The Boeing Company | US | IL Chicago | THE BOEING COMPANY | US | 100 N. RIVERSIDE | B21K001/60 | B21K001/60 B21J015/02 B21K001/58 F16B019/06 F16B005/04 | 3 | 4 | - | B21J0015/02 | B21J0015/02 B21K0001/58 B21K0001/60 F16B0019/06 F16B0005/04 Y10T0029/49956 | B21K0001/60 B21J0015/02 B21K0001/58 F16B0005/04 F16B0019/06 Y10T0029/49956 | - | - | - | - | - | - | - | Steven G. Keener | 1 | US | CA Trabuco Canyon | - | - | - | - | Edward Tolan | Edward Tolan | US1329144 US1554336 US2395721 US3072933 US3126561 US3426641 US3526032 US3626531 US3828422 US3848389 US3911783 US3975786 US3995406 US4126076 US4223433 US4861211 US5333980 US6267684 US6274200 US6499926 US6638381 US6726085 US6865919 US6912885 US7077755 US7241328 US7465234 US7513728 US7654909 US7785530 US7922841 US2004/0247835 US2006/0099432 US2006/0177284 US2008/0089802 | 35 | CN101404911 CN201568418 CN201836171 JPS48059242 JPS52009613 JPH04502798 JP2005194550 | 7 | Chinese Office Action for Application No. 2012104678556, dated Jul. 5, 2016.;Japanese Office Action for Application No. 2012-252251, dated Aug. 23, 2016.;Canadian Office Action for Application No. 2,792,752, dated Sep. 18, 2015.;Extended European Search Report for Application No. 12192230.6, dtd Jun. 17, 2015.;Chinese Office Action for Application No. 2012104678556, dated Sep. 6, 2015.;Chinese Office Action for Application No. 2016122802157660 dated Jan. 3, 2017. | 11 | 8 | EP2594349B1 US10589342 JP6258580 CN103122900B US09649682 US20130125376 CA2792752C CA2792752A1 BR102012029191B1 BR102012029191A2 | 10 | 6 | - | US20150096166 | 2015-04-09 | 9 | THE BOEING COMPANY | Valid | |||
61 | US09103047 | B2 | 2015-08-11 | Electrochemical deposition process for composite structures | invention | 13/099807 | 2011-05-03 | A method of improving the material properties of a composite by electrodepositing particular polymers, organic compounds or inorganic compounds onto electrically conductive fibrous substrates, whether individual fibers or as a fabric, to form composites of improved structural properties and having particular physical properties such as being ice phobic, fire resistant, or electrically conductive. | 1. A process for forming a resin-fiber composite, comprising the steps of providing an aqueous solution comprising an ionizable moiety, the ionizable moiety selected from the group consisting of polyamic acid, phenyl phosphinic acid, polyisobutylene-alt-maleic acid, polyphosphazene, polymetallophosphazene, polyborazine, phosphonicacidmethylene iminodiacetic acid, polyferrocene, polymetallocene, polysulfone, polyquinoxaline, polyether ether ketone (PEEK), and any combination thereof;disposing an electrically conductive fibrous substrate within the aqueous solution, wherein the fibrous substrate serves as an anode;contacting a second conductive body with the aqueous solution, wherein the second conductive body serves as a cathode;applying an electric potential between the anode and the cathode;ionizing the ionizable moiety in the aqueous solution;covalently bonding the ionizable moiety to the fibrous substrate to form a composite fiber;maintaining the electrodeposition conditions until at least one additional layer of the ionizable moiety is deposited on top of the resin matrix; andimpregnating the composite fiber with polyamic acid. | 1. A process for forming a resin-fiber composite, comprising the steps of providing an aqueous solution comprising an ionizable moiety, the ionizable moiety selected from the group consisting of polyamic acid, phenyl phosphinic acid, polyisobutylene-alt-maleic acid, polyphosphazene, polymetallophosphazene, polyborazine, phosphonicacidmethylene iminodiacetic acid, polyferrocene, polymetallocene, polysulfone, polyquinoxaline, polyether ether ketone (PEEK), and any combination thereof;disposing an electrically conductive fibrous substrate within the aqueous solution, wherein the fibrous substrate serves as an anode;contacting a second conductive body with the aqueous solution, wherein the second conductive body serves as a cathode;applying an electric potential between the anode and the cathode;ionizing the ionizable moiety in the aqueous solution;covalently bonding the ionizable moiety to the fibrous substrate to form a composite fiber;maintaining the electrodeposition conditions until at least one additional layer of the ionizable moiety is deposited on top of the resin matrix; andimpregnating the composite fiber with polyamic acid. 2. The process of claim 1, wherein the electrically conductive fibrous substrate is carbon fiber. 3. The process of claim 1, further comprising the step of curing the deposited resin matrix. 4. The process of claim 1, wherein the aqueous solution contains an organic solvent. 5. A composite structure formed according to the process of claim 1, wherein the composite substrate comprises a fibrous substrate having polyphosphinohydrazide covalently bonded to a surface thereof. 6. The composite structure of claim 5, wherein the structure takes the form of a composite fastener. 7. The composite structure of claim 6, wherein the composite fastener is a bolt or composite rivet. 8. The composite structure of claim 5, wherein the composite is a structural component of an aircraft. 9. The process of claim 1, wherein the ionizable moiety is polyphosphinohydrazide, and wherein the resulting resin-fiber composite has fire retardant properties. 10. A process for forming a resin-fiber composite, comprising the steps of providing an aqueous solution comprising an ionizable moiety, the ionizable moiety selected from the group consisting of polyamic acid, polypyrrole, polyaniline, phenyl phosphinic acid, polyisobutylene-alt-maleic acid, polysiloxane, polyphosphazene, polymetallophosphazene, polyborazine, phosphonicacidmethylene iminodiacetic acid, polyphosphinohydrazide, polyferrocene, polymetallocene, polysulfone, polyquinoxaline, polyether ether ketone (PEEK), and any combination thereof;disposing an electrically conductive fibrous substrate within the aqueous solution, wherein the fibrous substrate serves as an anode;contacting a second conductive body with the aqueous solution, wherein the second conductive body serves as a cathode; and,applying an electric potential between the anode and the cathode, thereby causing the ioni... | Norman R. Byrd Steven G. Keener Stephen C. Amundson Arthur Rojo | US | The Boeing Company | US | IL Chicago | THE BOEING COMPANY | US | 100 N. RIVERSIDE PLAZA | C25D009/00 | C25D009/00 C25D009/02 C25D019/00 C25D013/02 C25D009/06 C25D013/04 | 1 | 3 | C25D0013/02 | C25D0013/02 C25D0009/02 C25D0009/06 C25D0013/04 | C25D0013/02 C25D0009/02 C25D0009/06 C25D0013/04 | - | - | Norman R. Byrd Steven G. Keener Stephen C. Amundson Arthur Rojo | 4 | US | CA Villa Park CA Trabuco Canyon CA Huntington Beach CA Cypress | Alston & Bird LLP | - | - | Zulmariam Mendez | Zulmariam Mendez | US3926761 US4180442 US4272346 US4341889 US4405427 US4480088 US4582932 US4588838 US4614696 US4659444 US4664768 US4724062 US4738757 US4739115 US4749451 US5126017 US5238542 US5358747 US5844053 US6033545 US6537654 US6558782 US6565971 US6569523 US6575726 US6576341 US6609452 US6627312 US6630221 US6630416 US6638615 US6649265 US6660383 US6686048 US6689439 US6699582 US6699589 US6797795 US6809169 US7854788 US2003/0235696 US2004/0037951 US2004/0091711 US2005/0161337 | 44 | CN1 306 104 DE37 00 811 EP0 374 680 GB1 205 852 GB1 404 290 JPH02307967 WOWO 2005/033373 | 7 | Database WPI Section Ch, Week 200612 Derwent Publications Ltd., London, GB; AN 2002-011675 XP002390849 & CN 1 160 488C; Changchun Applied Chem Inst Chinese Acad; Aug. 4, 2004.;PCT Search Report and Written Opinion for PCT/US2006/001610 dated Aug. 8, 2006.;Tsubokawa, N., et al.; “Surface Grafting of Polymers onto Carbon Thin Film”, Journal of Applied Polymer Science; vol. 58; Issue 8; Nov. 21, 1995; pp. 1221-1227.;Delamar, M., et al.; “Modification of Carbon Fiber Surfaces by Electrochemical Reduction of Aryl Diazonium Salts: Application to f Carbon Epoxy Composites”; Carbon Journal; vol. 35; Issue 6; 1997; pp. 801-807.;Reichenbacher, P. H., et al.; “Intermediates in Anodic Oxidation of Carboxylates. Chronopotentiometry”; Journal of the American Chemical Society;vol. 90; No. 13, Jun. 1968; pp. 3432-3436.;Andrieux et al.; “Derivatization of Carbon Surfaces by Anodic Oxidation of Arylacetates. Electrochemical Manipulation of the Grafted Films”, Journal of the American Chemical Society; vol. 119; No. 18; May 7 1997; pp. 4292-4300.;Buttry, D. A., et al.; “Immobilization of amines at carbon fiber surfaces”; Carbon; vol. 37; Issue 12; 1999; pp. 1929-1940.;Miller, L. L., et al.; “Electrode Surface Modification via Polymer Adsorption”; Journal of the American Chemical Society, vol. 100; No. 2; Jan. 1978; pp. 639-640.;Downard, A. J.; “Electrochemically Assisted Covalent Modification of Carbon Electrodes”; Electroanalysis; vol. 12; No. 14; Oct. 2000; pp. 1085-1096.;Pierson, H. O.; “Applications of Carbon Fibers”, Chapter 9 from Handbook of Carbon, Graphite, Diamond and Fullerenes—Properties, Processing and Applications; © 1993 by Noyes Publications; Park Ridge, New Jersey; US; pp. 198-225. | 14 | 2 | US09103047 US07959783 EP1838904A2 WO2006081101 | 4 | 3 | - | US20110266153 | 2011-11-03 | 6 | THE BOEING COMPANY | Overdue | ||||||||||
62 | US11052454 | B2 | 2021-07-06 | Dynamic collar swage conformance checking based on swage tool parameters | invention | 16/519714 | 2019-07-23 | Systems and methods are provided for inspecting fastener installation. One embodiment is a method for inspecting installation of a fastener. The method includes determining an initial distance between a nose of a swage tool and an Inner Mold Line (IML) of a part, operating the swage tool to swage a collar onto a fastener that protrudes through the IML of the part, determining a terminal distance of the nose to the IML during swaging, prior to a pintail of the fastener breaking, and arriving at a conclusion indicating a state of a fastener installation, based on the terminal distance. | 1. A method for inspecting installation of a fastener, the method comprising: determining an initial distance between a nose of a swage tool and an Inner Mold Line (IML) of a part;operating the swage tool to swage a collar onto a fastener that protrudes through the IML of the part;determining a terminal distance of the nose to the IML during swaging, prior to a pintail of the fastener breaking; andarriving at a conclusion indicating a state of a fastener installation, based on the terminal distance. | 1. A method for inspecting installation of a fastener, the method comprising: determining an initial distance between a nose of a swage tool and an Inner Mold Line (IML) of a part;operating the swage tool to swage a collar onto a fastener that protrudes through the IML of the part;determining a terminal distance of the nose to the IML during swaging, prior to a pintail of the fastener breaking; andarriving at a conclusion indicating a state of a fastener installation, based on the terminal distance. 2. The method of claim 1 wherein: determining the initial distance comprises: placing a tip of a pressure foot of the swage tool in contact with the IML;determining a separation between the tip of the pressure foot and a tip of the nose; anddetermining the initial distance based on the separation between the tip of the pressure foot and a tip of the nose. 3. The method of claim 1 wherein: determining the terminal distance comprises: analyzing hydraulic pressure readings to identify a point in time that the pintail of the fastener broke; anddetermining a distance between the nose and the IML at the point in time. 4. The method of claim 1 wherein: determining the terminal distance comprises: analyzing hydraulic pressure readings to identify a first point in time that the pintail of the fastener broke;identifying a second point in time prior to the first point in time when hydraulic pressure reached a threshold value; anddetermining a distance between the nose and the IML at the second point in time. 5. The method of claim 1 further comprising: determining the terminal distance and arriving at the conclusion is performed in real-time prior to installing a next fastener. 6. The method of claim 1 wherein: arriving at the conclusion indicating the state of the fastener installation comprises: if the terminal distance is less than a threshold amount, concluding that the fastener installation has completed successfully; andif the terminal distance is not less than a threshold amount, concluding that the fastener installation has not completed successfully. 7. The method of claim 1 wherein: reporting the state of the fastener installation comprises: including the state of the fastener installation within a report detailing states of fastener installation for multiple fasteners within a region of the part; andproviding the report via a display for review by a technician. 8. The method of claim 1 further comprising: reporting the state of the fastener installation for review. 9. A portion of an aircraft assembled according to the method of claim 1. 10. A non-transitory computer readable medium embodying programmed instructions which, when executed by a processor, are operable for performing a method for inspecting installation of a fastener, the method comprising: determining an initial distance between a nose of a swage tool and an Inner Mold Line (IML) of a part;operating the swage tool to swage a collar onto a fastener that protrudes through the IML ... | The Boeing Company | US | The Boeing Company | US | IL Chicago | The Boeing Company | US | - | B21J015/28 | B21J015/28 B21J015/02 F16B019/05 B21J015/14 | 2 | 2 | - | B21J0015/28 | B21J0015/28 B21J0015/022 F16B0019/05 | B21J0015/28 B21J0015/022 B21J0015/142 B21J0015/285 F16B0019/05 | - | - | - | - | - | - | - | Kwok Tung Chan Farahnaz Sisco Skye Jenkins Jeffrey Devlin Nathan Christopher McRae | 5 | US | WA Seattle WA Mukilteo WA Snohomish WA Seattle WA Seattle | Duft & Bornsen, PC | - | - | Bayan Salone | Bayan Salone | US1901431 US3036576 US3089062 US3603126 US3661887 US4901431 US5036576 US5315755 US5502884 US5661887 US6089062 US6256854 US6347449 US7055393 US7137182 US7503196 US7527759 US7655168 US7802352 US7879177 US7922856 US8012291 US8206540 US8336596 US8465613 US8640757 US8758538 US8808490 US9399338 US10483901 US10821496 US2004/0060363 US2004/0063362 US2006/0230571 US2008/0168816 US2018/0148196 US2019/0283113 US2019/0283114 | 38 | CN101053889 CN108296406 DE102004020409 DE102013112363 EP0995518 EP1302258 EP1712311 EP3330173 EP3560624 WO2015083756 | 10 | European Search Report; Application No. EP20183457; dated Dec. 21, 2020.;U.S. Appl. No. 15/923,297.;U.S. Appl. No. 15/923,378.;U.S. Appl. No. 15/963,148.;European Search Report; Application EP19190789; dated Feb. 19, 2020. | 6 | 0 | US11052454 KR1020210012928 CN112307592A EP3769860A1 | 4 | 4 | - | US20210023607 | 2021-01-28 | 14 | THE BOEING COMPANY | Valid | ||||
63 | US08303227 | B2 | 2012-11-06 | Lining fasteners and methods and apparatus therefor | invention | 12/246490 | 2008-10-06 | Fastener assemblies, elements for fastener assemblies and methods of making and assembling elements for fastener assemblies, for example for insulation blanket fasteners such as those used on aircraft, may include a formed monolithic metal configuration having first and second side portions with a plurality of panel retaining elements arranged linearly along the side portions. A planar retaining element, for example a disc, may be assembled with the metal portion to form a fastener assembly, such as may be used to retain and insulation blanket. The planar retaining element may include a rolled edge, and if a coated part, may include surface projections to keep adjacent parts from sticking together during the coating process. | 1. A fastener stud for a blanket insulation fastener assembly, the fastener stud comprising a monolithic metal fastener stud having a post element, the post element having two side portions spaced apart from each other and each side portion being supported at a support portion by a bridge portion, wherein each side portion extends in a respective side direction away from the bridge portion and includes a plurality of retaining surfaces at edge surfaces of the respective side portion, wherein each retaining surface extends outward of the respective side portion in the respective side direction and wherein each retaining surface of the plurality of retaining surfaces on one side portion has a corresponding retaining surface on the other side portion and wherein the corresponding retaining surface has corresponding surfaces substantially equidistant from a plane perpendicular to an axis of the stud facing the retaining surface and wherein each retaining surface on a side portion is spaced apart from an adjacent retaining surface by a substantially straight surface substantially perpendicular to a portion of the perpendicular plane. | 1. A fastener stud for a blanket insulation fastener assembly, the fastener stud comprising a monolithic metal fastener stud having a post element, the post element having two side portions spaced apart from each other and each side portion being supported at a support portion by a bridge portion, wherein each side portion extends in a respective side direction away from the bridge portion and includes a plurality of retaining surfaces at edge surfaces of the respective side portion, wherein each retaining surface extends outward of the respective side portion in the respective side direction and wherein each retaining surface of the plurality of retaining surfaces on one side portion has a corresponding retaining surface on the other side portion and wherein the corresponding retaining surface has corresponding surfaces substantially equidistant from a plane perpendicular to an axis of the stud facing the retaining surface and wherein each retaining surface on a side portion is spaced apart from an adjacent retaining surface by a substantially straight surface substantially perpendicular to a portion of the perpendicular plane. 2. The stud of the claim 1 wherein each side portion has the same number of teeth as the other side portion. 3. The stud of claim 1 wherein each retaining surface has a substantially flat surface substantially parallel to a portion of the perpendicular plane. 4. The stud of claim 3 wherein each retaining surface has a ramp surface extending from the substantially flat surface away from the perpendicular plane to the support portion of the side portion. 5. The stud of claim 1 wherein each retaining surface on a side portion is spaced apart from an adjacent retaining surface. 6. The stud of claim 1 wherein the post is a substantially U-shaped post element having a U-shaped post profile and wherein the retaining surfaces are at ends of the U-shaped post profile. 7. The stud of claim 1 wherein the post includes a curved bridge portion. 8. The stud of claim 7 wherein the curved bridge portion is substantially semi-circular. 9. The fastener stud of claim 1 further including a sleeve wherein the sleeve is a resiliently flexible sleeve over part of the fastener stud having a peripheral groove formed in an outside surface of the sleeve between first and second sleeve ends and a plurality of flexible protrusions in the groove extending within the groove. 10. The fastener stud of claim 9 wherein a first sleeve end includes a ramped surface. 11. The fastener stud of claim 9 wherein at least one of the flexible protrusions extends about the grooves in a circumferential direction. 12. The fastener stud of claim 9 wherein at least one of the flexible protrusions includes at least one surface extending in a substantially radial direction. 13. The fastener stud of claim 9 wherein at least one of the flexible protrusions includes at least one surface extending in a direction at an angle to a central axis of the sleeve. 14. The... | Igor Komsitsky Javier Torres | US | The Monadnock Company | US | CA City of Industry | THE MONADNOCK COMPANY | US | 18301 EAST ARENTH AVENUE | F16B015/00 | F16B015/00 | 1 | 1 | F16B0019/00 F16B0043/00 F16B0005/0692 Y10T0024/3683 Y10T0024/3685 Y10T0029/49837 | 411/477.000 | 411/477.000 411/450.000 | - | - | Igor Komsitsky Javier Torres | 2 | US | CA Los Angeles CA Hacienda Heights | Henricks, Slavin & Holmes LLP | - | - | Gary Estremsky | Gary Estremsky | US1087580 US2197220 US2202896 US2553917 US2560961 US2797605 US2876971 US3738217 US3983779 US4075924 US4203193 US4289058 US4370840 US4597702 US4739955 US4805366 US5518215 US6022351 US6276644 US6659700 US7658583 | 21 | GB635670 | 1 | Jeong, Kyong Hun; PCT International Search Report; WIPO Korea ISA; May 20, 2010; PCT/US2009/059750 & WO2010042558A2. | 17 | 5 | EP2334936B1 CN102326005B JP5635002 US08303227 WO2010042558 CA2739446C MX343427B BRPI0920418A2 CA2739446A1 BRPI0920418B1 RU2499165C2 RU2011117309A IL212137A ES2606238T3 IL212137A0 MX2011003652A | 16 | 11 | - | US20100083471 | 2010-04-08 | 3 | THE MONADNOCK COMPANY | Valid | ||||||||||
64 | CN108412883 | A | 2018-08-17 | 一種高溫合金齒形自鎖螺套及其製作方法 | invention | CN201810556845.7 | 2018-05-31 | 本發明涉及一種航空用緊固件，具體為一種高溫合金齒形自鎖螺套及其製作方法，包括如下步驟，1.備料：螺套採用YZGH2132合金材質；2.下料：按鐓制螺套的需求用料；3.表面處理：鍍銅潤滑，防止表面在鐓制過程中拉傷；4.熱鐓：高頻加熱鐓制六方體，防止零件過燒；5.退鍍：退去表面鍍銅層；6.固溶：固溶處理中加熱溫度為990‑1010℃。本發明提供一種能製作螺套的方法，使製作的螺套經過上千次鎖緊不衰減還能在高溫650℃條件下安全使用。; | 1.一種高溫合金齒形自鎖螺套的製作方法，其特徵在於：包括如下步驟，1)備料：螺套採用YZGH2132合金材質；2)下料：按鐓制螺套的需求用料；3)表面處理：鍍銅潤滑，防止表面在鐓制過程中拉傷；4)熱鐓：高頻加熱鐓制六方體，防止零件過燒；5)退鍍：退去表面鍍銅層；6)固溶：固溶處理中加熱溫度為990-1010℃；7)數控車：按照螺套的設定尺寸車外螺紋的螺紋坯徑、滾套鎖緊齒、切割套鎖緊齒下方的環形槽；8)去毛刺：去掉螺套車後的毛刺；9)滾螺紋：滾壓螺套的外螺紋；10)數控車：鑽鏜螺套的安裝通孔，並為孔口倒角；11)擠壓內螺紋；擠壓安裝通孔內壁的內螺紋；12)線切割：切割安裝端的六道槽口，槽口要求對稱、均布；13)收口：擠壓螺套的安裝端，將六道槽口收攏，槽口寬0.05～0.1mm，使內外螺紋割槽段部分變形，收口段形成彈簧片，產生自鎖性能；14)時效：收口後螺套進行時效處理，使螺套強度大於等於1100MPa；15)噴砂：噴砂去掉螺套表面氧化物；16)探傷：螺套經過熱處理後需對其探傷檢測。 | 1.一種高溫合金齒形自鎖螺套的製作方法，其特徵在於：包括如下步驟，1)備料：螺套採用YZGH2132合金材質；2)下料：按鐓制螺套的需求用料；3)表面處理：鍍銅潤滑，防止表面在鐓制過程中拉傷；4)熱鐓：高頻加熱鐓制六方體，防止零件過燒；5)退鍍：退去表面鍍銅層；6)固溶：固溶處理中加熱溫度為990-1010℃；7)數控車：按照螺套的設定尺寸車外螺紋的螺紋坯徑、滾套鎖緊齒、切割套鎖緊齒下方的環形槽；8)去毛刺：去掉螺套車後的毛刺；9)滾螺紋：滾壓螺套的外螺紋；10)數控車：鑽鏜螺套的安裝通孔，並為孔口倒角；11)擠壓內螺紋；擠壓安裝通孔內壁的內螺紋；12)線切割：切割安裝端的六道槽口，槽口要求對稱、均布；13)收口：擠壓螺套的安裝端，將六道槽口收攏，槽口寬0.05～0.1mm，使內外螺紋割槽段部分變形，收口段形成彈簧片，產生自鎖性能；14)時效：收口後螺套進行時效處理，使螺套強度大於等於1100MPa；15)噴砂：噴砂去掉螺套表面氧化物；16)探傷：螺套經過熱處理後需對其探傷檢測。 2.還包步驟17.表面處理：表面鍍銀。 3.包括螺套、與螺套配合的栓柱以及止動圈，所述螺套的一端為鎖緊端，另一端為安裝端，所述鎖緊端的外壁設有套鎖緊齒，所述安裝端設有與基體上的槽螺紋連接的外螺紋，安裝端周向均勻開設有六道槽口，所述槽口寬0.05-0.1mm，所述安裝端設有槽口的位置為收口段，所述螺套開設有供栓柱插入的安裝通孔，所述安裝通孔內壁設有與栓柱螺紋連接的內螺紋，所述安裝通孔對應收口段的一段呈縮口狀；栓柱，栓柱包括安裝段、鎖緊段以及連接段，所述安裝段的外壁設有與安裝通孔螺紋連接的安裝螺紋，所述鎖緊段設有柱鎖緊齒，連接段的外壁設有與外部部件連接的連接螺紋；所述止動圈的外壁設有與安裝槽相互卡緊的定位齒，所述止動圈的內壁設有圈鎖緊齒，所述圈鎖緊齒的上半部分與柱鎖緊齒嚙合，所述圈鎖緊齒的下半部分與套鎖緊齒嚙合。 4.還包括與栓柱連接端螺紋連接的檢測鐳射頭、焊接於基體的對比鐳射頭、固定於螺套上方的投光板、振動件以及投光板的檢測攝像頭，對比鐳射頭與所述檢測鐳射頭的距離小於10cm，所述振動件固定連接基體，所述振動件與螺套的距離小於10cm，所述投光板平行於所述基體的表面並用於顯示檢測鐳射頭與對比鐳射頭投射的光斑，所述檢測攝像頭用於拍攝振動件振動時投光板上的光斑。 5.所述檢測鐳射頭投射到投光板的光斑為“十”字形。 6.振動件通過電磁鐵固定在基體上。 | 貴州精立航太科技有限公司 | CN | 563000 貴州省遵義市紅花崗區南部新區盈田工穀產業園33號樓 | 貴州精立航太科技有限公司 | CN | 中國貴州 | - | - | - | F16B037/00 | F16B037/00 B23P015/00 | 2 | 2 | - | - | - | - | - | - | - | - | - | - | - | 林燚 萬隆 孫文東 陳春旭 旦其江 葉江華 張廣 劉清樹 付開榮 吳軍 盧世寧 | 11 | CN | | 蒙捷 | 20180817 | - | - | - | - | 0 | - | 0 | - | 7 | 2 | CN108412883A | 1 | 1 | - | CN108412883 | 2018-08-17 | 13 | 貴州精立航太科技有限公司 | Overdue | |||
65 | US09038951 | B2 | 2015-05-26 | Coupling assembly | invention | 13/138678 | 2010-03-31 | A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies. | 1. An aircraft assembly comprised of an aircraft skin cover, an aircraft edge panel adjacent said cover and a coupling assembly for joining said cover to said panel, the coupling assembly comprising: a shaft for connecting to said edge panel;a bracket including a mounting plate for connecting to said skin cover, a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm, the shaft being received in the through-bore; anda setting device configured to act between the head and the shaft and to adjust and set the position of the edge panel with respect to the skin cover in the axial direction of the shaft, wherein the coupling assembly includes at least one spherical bearing surface configured to permit self-alignment of the setting device and to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. | 1. An aircraft assembly comprised of an aircraft skin cover, an aircraft edge panel adjacent said cover and a coupling assembly for joining said cover to said panel, the coupling assembly comprising: a shaft for connecting to said edge panel;a bracket including a mounting plate for connecting to said skin cover, a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm, the shaft being received in the through-bore; anda setting device configured to act between the head and the shaft and to adjust and set the position of the edge panel with respect to the skin cover in the axial direction of the shaft, wherein the coupling assembly includes at least one spherical bearing surface configured to permit self-alignment of the setting device and to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. 2. An aircraft assembly according to claim 1, wherein a spherical recess is formed in the head around the periphery of the bore on one or each end of the bore, the recess having the spherical bearing surface. 3. An aircraft assembly according to claim 1, wherein a spherical washer is received on the head around the periphery of the bore on one or each end of the bore, the spherical washer having the spherical bearing surface. 4. An aircraft assembly according to claim 2, wherein the head has the recess formed around one end of the bore, and the head receives the spherical washer around the other end of the bore. 5. An aircraft assembly according to claim 1, wherein a spherical bearing is received in the bore and held in place by a bearing clip, the spherical bearing having the spherical bearing surface and an inner through-bore which receives the shaft. 6. An aircraft assembly according to claim 1, wherein the setting device is one or more nuts threadably received on the shaft. 7. An aircraft assembly according to claim 1, wherein the mounting plate has one or more fixing holes for receiving respective fasteners for connecting said mounting plate to the skin cover. 8. An aircraft assembly according to claim 1, wherein the mounting plate is planar or L-shaped. 9. An aircraft assembly according to claim 1, wherein the shaft is of a bolt having a head connected to the edge panel. 10. An aircraft assembly according to claim 1, wherein the shaft is integrally formed with a second mounting plate connected to the edge panel. 11. An aircraft assembly according to claim 1, wherein the setting device is configured to set the position of the edge panel with respect to the skin cover in a fixed spatial arrangement. 12. An aircraft lifting surface comprising a first component joined to a second component by at least one coupling assembly, said at least one coupling assembly comprising: a shaft for connecting to said first component;a bracket including a mounting plate for connecting to said second component, a bracket arm extending from the mounting plate, and ... | Steven Coulter Paul Hadley Geraint Hopkins | GB | Airbus Operations Limited | GB | Bristol | AIRBUS OPERATIONS LIMITED | UNITED KINGDOM | NEW FILTON HOUSE, FILTON | B64C003/28 | B64C003/28 F16B005/02 | 2 | 2 | B64C0003/28 | B64C0003/28 Y10T0403/19 Y10T0029/49947 F16B0005/025 | B64C0003/28 F16B0005/025 Y10T0029/49947 | 244/131.000 | 244/131.000 | - | - | 0905818.1 | 2009-04-06 | GB | Steven Coulter Paul Hadley Geraint Hopkins | 3 | GB | Bristol Bristol Bristol | Nixon & Vanderhye P.C. | - | - | Philip J Bonzell | Philip J Bonzell Nicholas McFall | US4213587 US2008/0258008 US2010/0096505 | 3 | CN101230874 EP1 503 096 FR2 731 198 GB743267 GB804392 RU2 192 990 WOWO 98/06917 | 7 | Chinese First Office Action issued Aug. 26, 2013 in CN 201080015978.5 and English Translation.;International Search Report for PCT/GB2010/050552, mailed Dec. 1, 2010.;Written Opinion for PCT/GB2010/050552, mailed Dec. 1, 2010.;Search Report for GB 0905818.1, dated Jul. 29, 2009.;Chinese Search Report dated Aug. 15, 2013 in CN 2010800159785. | 15 | 11 | US09038951 CN102369138B JP5643291 EP2417020B1 WO2010116168 GB0905818D0 CA2755879A1 | 7 | 7 | - | US20120006942 | 2012-01-12 | 5 | AIRBUS OPERATIONS LIMITED | Overdue | |||||
66 | US20130125376 | A1 | 2013-05-23 | METHOD FOR PREPARING HIGHLY-DEFORMABLE TITANIUM AND TITANIUM-ALLOY ONE-PIECE FASTENERS AND FASTENERS PREPARED THEREBY | invention | 13/299228 | 2011-11-17 | A fastener has a cold-worked head section, a cold-worked shank section, and a ductile shank section extending from the cold-worked shank section to a tail end portion of the fastener. | 1. A fastener, comprising: a cold-worked head section;a cold-worked shank section; anda ductile shank section extending from the cold-worked shank section to a tail end portion of the fastener, the ductile shank section being non-cold-worked. | 1. A fastener, comprising: a cold-worked head section;a cold-worked shank section; anda ductile shank section extending from the cold-worked shank section to a tail end portion of the fastener, the ductile shank section being non-cold-worked. 2. The fastener of claim 1 wherein: the cold-worked head section and the cold-worked shank section have a higher strength than the ductile shank section. 3. The fastener of claim 1 wherein: the ductile shank section has a higher level of ductility than the cold-worked head section and the cold-worked shank section. 4. The fastener of claim 1 wherein: the fastener has at least one of the following material compositions: aluminum, aluminum-alloy. 5. The fastener of claim 1 wherein: the fastener has at least one of the following material compositions: steel, steel-alloy. 6. The fastener of claim 1 wherein: the fastener has at least one of the following material compositions: titanium, and titanium-alloy. 7. The fastener of claim 1 wherein: the fastener has an ultra-fine grain material composition. 8. The fastener of claim 1 wherein: the cold-worked head section and the cold-worked shank section are formed by a cold-working process. 9. The fastener of claim 1 wherein: the fastener is coated with a corrosion-resistant, curable organic coating material. 10. The fastener of claim 1 having at least one of the following configurations: a flush head configuration; anda protruding head configuration. 11. A method of forming a fastener, comprising the steps of: inserting a blank precursor into a bore of a forming die having an enlarged bore portion;applying an axial compression force to the blank precursor;forming a cold-worked head section and an enlarged shank portion on the blank precursor corresponding to the enlarged bore portion, the enlarged shank portion having a nominal shank portion extending therefrom;inserting the nominal shank portion into a bore of a final reduction die;applying an axial compression force to the enlarged shank portion;urging the enlarged shank portion into the bore of the final reduction die; andforming a cold-worked shank section by reducing a cross-sectional area of the enlarged shank portion. 12. The method of claim 11 wherein the step of reducing the cross-sectional area of the enlarged shank portion comprises: reducing the cross-sectional area of the enlarged shank portion by approximately 2 to 5 percent. 13. The method of claim 11 wherein the step of providing the blank precursor comprises: providing a blank precursor in at least one of the following material compositions:titanium, titanium-alloy. 14. The method of claim 11 wherein: providing a blank precursor having an ultra-fine grain material composition. 15. The method of claim 11 further comprising at least one of the following steps: annealing the blank precursor prior to forming the cold-worked shank section and cold-worked head section; andannealing the fastener after forming the cold-worked head section and the... | Steven G. Keener | US | THE BOEING COMPANY | US | CA Seal Beach | THE BOEING COMPANY | US | 100 N. RIVERSIDE PLAZA | B21J015/02 | B21J015/02 B21K001/58 F16B019/06 | 3 | 3 | B21K0001/60 B21J0015/02 B21K0001/58 F16B0005/04 F16B0019/06 Y10T0029/49956 | 029/525.060 | 029/525.060 411/506.000 470/028.000 | - | - | Steven G. Keener | 1 | US | CA Trabuco Canyon | - | - | - | 0 | 0 | 14 | 1 | EP2594349B1 US10589342 JP6258580 CN103122900B US09649682 US20130125376 CA2792752C CA2792752A1 BR102012029191B1 BR102012029191A2 | 10 | 6 | - | US20130125376 | 2013-05-23 | 6 | THE BOEING COMPANY | Overdue | |||||||||||||||
67 | EP3587612 | B1 | 2021-12-08 | METHOD FOR PRODUCING AN ASSEMBLY COMPRISING AN INTERLOCKING CONNECTION AND AN ASSEMBLY WITH AN INTERLOCKING CONNECTION WITH PRECIPITATION-HARDENABLE INTERLOCKING AREA | invention | 19181142.1 | 2019-06-19 | Die vorliegende Erfindung betrifft ein Verfahren zur Herstellung einer Baugruppe mit einer Formschlussverbindung mit einem ausscheidungsgehärteten Formschlussbereich sowie eine entsprechende Baugruppe, wobei mindestens zwei Komponenten einer Baugruppe (1,2,3) bereitgestellt werden, die formschlüssig miteinander verbunden werden, wobei jede der Komponenten einen Formschlussbereich aufweist, der mit mindestens einem anderen Formschlussbereich der anderen zu verbindenden Komponente in Kontakt gelangen kann, um durch die Einschränkung mindestens eines Bewegungsfreiheitsgrades der verbundenen Komponenten zueinander eine formschlüssige Verbindung herzustellen, wobei mindestens eine der Komponenten mindestens einen Verformungsformschlussbereich (6,7) zur Bereitstellung der formschlüssigen Verbindung aufweist, der zur Herstellung der formschlüssigen Verbindung nach einer Anordnung der zu verbindenden Komponenten zueinander umgeformt wird, um die formschlüssige Verbindung herzustellen, wobeider mindestens eine Verformungsformschlussbereich (6,7) aus einem Werkstoff gebildet ist, der durch Ausbildung von Ausscheidungen härtbar ist, wobei der Verformungsformschlussbereich (6,7) im nicht gehärteten Zustand bereitgestellt wird oder durch Lösungsglühen und nachfolgendes Abschrecken in einen nicht gehärteten Zustand gebracht wird, wobei die mindestens eine Komponente mit dem mindestens einen Verformungsformschlussbereich (6,7) im nicht gehärteten Zustand des Verformungsformschlussbereichs relativ zur mindestens einer anderen, zu verbindenden Komponente angeordnet wird und der mindestens ein Verformungsformschlussbereich (6,7) zur Ausbildung eine formschlüssigen Verbindung umgeformt wird, wobei nach der Umformung des Verformungsformschlussbereichs (6,7) der Verformungsformschlussbereich (6,7) einer Auslagerungswärmebehandlung unterzogen wird, bei der der Verformungsformschlussbereich (6,7) durch Bildung von Ausscheidungen gehärtet wird. | Method for producing an assembly comprising a form-fitting connection having a precipitation-hardened form-fitting region, in which at least two components of an assembly (1, 2, 3; 11, 12, 13, 16, 17, 18; 21, 26, 29) are provided that are interconnected in a form-fitting manner, each of the components having a form-fitting region which can come into contact with at least one other form-fitting region of the other componentto be connected in order to produce a form-fitting connection by limiting at least one degree of freedom of movement of the connected components relative to one another, at least one of the components having at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) for providing the form-fitting connection, which region is reshaped to produce the form-fitting connection after the components to be connected are arranged relative to one another, in order to produce the form-fitting connection, the at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) being formed from a material which can be hardened by the formation of precipitates, the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) being provided in a non-hardened state or being brought into a non-hardened state by solution annealing and subsequent quenching, the at least one component having the at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25), in the non-hardened state of the deformation form-fitting region, being arranged relative to at least one other componentto be connected, and the at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) being reshaped to form a form-fitting connection,the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25), after the reshaping of the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25), being subjected to an aging heat treatment in which the deformation form-fitting region (4,5,6,7; 16; 24,25) is hardened by the formation of precipitates, characterized in thatthe deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) or the component having the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) is formed from a precipitation-hardenable nickel-based material or a precipitation-hardenable cobalt-based material. | Method for producing an assembly comprising a form-fitting connection having a precipitation-hardened form-fitting region, in which at least two components of an assembly (1, 2, 3; 11, 12, 13, 16, 17, 18; 21, 26, 29) are provided that are interconnected in a form-fitting manner, each of the components having a form-fitting region which can come into contact with at least one other form-fitting region of the other componentto be connected in order to produce a form-fitting connection by limiting at least one degree of freedom of movement of the connected components relative to one another, at least one of the components having at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) for providing the form-fitting connection, which region is reshaped to produce the form-fitting connection after the components to be connected are arranged relative to one another, in order to produce the form-fitting connection, the at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) being formed from a material which can be hardened by the formation of precipitates, the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) being provided in a non-hardened state or being brought into a non-hardened state by solution annealing and subsequent quenching, the at least one component having the at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25), in the non-hardened state of the deformation form-fitting region, being arranged relative to at least one other componentto be connected, and the at least one deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) being reshaped to form a form-fitting connection,the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25), after the reshaping of the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25), being subjected to an aging heat treatment in which the deformation form-fitting region (4,5,6,7; 16; 24,25) is hardened by the formation of precipitates, characterized in thatthe deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) or the component having the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) is formed from a precipitation-hardenable nickel-based material or a precipitation-hardenable cobalt-based material. Method according to claim 1,characterized in that in order to carry out the aging heat treatment, the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) is locally heated or the component having the deformation form-fitting region (4, 5, 6, 7; 16; 24, 25) or the assembly having the connected components is heated. --> Method according to either claim 1 or claim 2,characterized in that the aging heat treatment takes place in a locally limited manner by means of inductive heating and/or high-energy radiation, in particular laserradiation, electron radiation and/or infrared radiation. Method according to any of the preceding claims,characterized in that the aging heat treatment takes place during operation or use of the assembly. Method ac... | MTU Aero Engines AG | MTU Aero Engines AG | DE | Dachauer Strasse 665 80995 München | - | - | - | C22F001/10 | C22F001/10 F16B019/05 F16B019/06 F01D005/32 | 3 | 3 | - | - | - | - | - | 102018210743 | 2018-06-29 | DE | von Lautz, Julian Weiß, Michael Schlemmer, Markus Matuszewski, Kamil Kirzinger, Anna | 5 | DE | 80634 München 85221 Dachau 84048 Mainburg / Sandelzhausen 85757 Karlsfeld 80686 München | - | - | - | 0 | EP1 306 522 US4 712 958 US2004 247 835 US2014 369 785 US4712958 US20040247835 EP1306522 US20140369785 | 8 | DE RIJCK ET AL: "The driven rivet head dimensions as an indication of the fatigue performance of aircraft lap joints", INTERNATIONAL JOURNAL OF FATIGUE, ELSEVIER, AMSTERDAM, NL, Bd. 29, Nr. 12, 25. Oktober 2007 (2007-10-25), Seiten 2208-2218, XP022314348, ISSN: 0142-1123, DOI: 10.1016/J.IJFATIGUE.2006.12.010;<nplcit id="ref-ncit0001" npl-type="s"><article><author><name>J.J.M. DE RIJCK et al.</name></author><atl>The driven rivet head dimensions as an indication of the fatigue performance of aircraft lap joints</atl><serial><sertitle>International Journal of Fatigue</sertitle><pubdate><sdate>20070000</sdate><edate/></pubdate><vid>29</vid></serial><location><pp><ppf>2208</ppf><ppl>2218</ppl></pp></location></article></nplcit> | 6 | 0 | EP3587612B1 US20200002796 ES2902155T3 DE102018210743A1 | 4 | 4 | - | EP3587612 | 2020-01-01 | 14 | MTU Aero Engines AG | ||||||||||||
68 | US09108363 | B2 | 2015-08-18 | Thin wall bushing for robust electrical bonding to fiber-reinforced structures | invention | 13/267504 | 2011-10-06 | A method for directing electrical current to prevent sparking from the interaction between a composite structure and lightning or static electrical charge, the method including the steps of forming a hole in a composite structure; and positioning a bushing into the hole to create an interference fit between the bushing and the composite structure, wherein the bushing is formed of a material that has a coefficient of thermal expansion close to the coefficient of thermal expansion of the composite structure and the bushing provides an electrical path between a fastener disposed in the bushing and the composite structure. | 1. A method for providing robust electrical bonding to a composite structure, said method comprising the steps of: forming a hole in a composite structure, wherein the hole includes an inner diameter; andpositioning a bushing having an outer diameter into the hole to create an interference fit between the outer diameter of the bushing and the inner diameter of the hole of the composite structure, wherein said bushing is formed of a material that has a coefficient of thermal expansion within about 300% of the coefficient of thermal expansion of the composite structure and said bushing provides an electrical path between a fastener disposed in said bushing and the composite structure. | 1. A method for providing robust electrical bonding to a composite structure, said method comprising the steps of: forming a hole in a composite structure, wherein the hole includes an inner diameter; andpositioning a bushing having an outer diameter into the hole to create an interference fit between the outer diameter of the bushing and the inner diameter of the hole of the composite structure, wherein said bushing is formed of a material that has a coefficient of thermal expansion within about 300% of the coefficient of thermal expansion of the composite structure and said bushing provides an electrical path between a fastener disposed in said bushing and the composite structure. 2. The method of claim 1 wherein said bushing is formed of tungsten, rhenium, nickel, iron or alloys containing these materials. 3. The method of claim 1 wherein said composite structure comprises carbon fibers. 4. The method of claim 3 wherein said composite structure comprises a carbon reinforced polymer material. 5. The method of claim 1 wherein said bushing is cylindrical with a wall thickness of between about 0.010 and 0.020 inches. 6. The method of claim 1 wherein said bushing further comprises an annular flange at one end of the bushing. 7. The method of claim 1 further comprising temporarily expanding the hole prior to positioning the bushing in the hole. 8. The method of claim 7 wherein a tapered lead-in mandrel is used to temporarily expand the hole and position the bushing in the hole. 9. The method of claim 8 wherein the mandrel also provides support to the bushing during positioning of the bushing. 10. The method of claim 1 wherein the composite structure is part of an aircraft. 11. A method of installing a bushing in a hole in a composite structure comprising: providing a mandrel having, in order, a bushing support section, a tapered lead-in section, and a straight positioning section, wherein the tapered lead-in section increases in diameter from the straight positioning section to a maximum diameter immediately adjacent to the bushing support section;installing the bushing on the bushing support section of the mandrel;inserting the straight positioning section of the mandrel into the hole; andmoving the mandrel through the hole thereby temporarily expanding the hole radially to facilitate installation of the bushing in the hole and creation of an interference fit between the bushing and the composite structure, wherein said bushing is formed of a material that has a coefficient of thermal expansion within about 300% of the coefficient of thermal expansion of the composite structure and said bushing provides an electrical path between a fastener disposed in said bushing and the composite structure. 12. The method of claim 11 wherein said bushing is formed of tungsten, rhenium, nickel, iron, or alloys containing these materials. 13. The method of claim 11 wherein said composite structure comprises carbon fibers. 14. The method of claim 13 wh... | Matthew Anthony Dilligan James P. Irwin Christopher Newbolt Peter A. Coronado Benjamin A. Johnson | US | THE BOEING COMPANY | US | IL Chicago | THE BOEING COMPANY | US | 100 NORTH RIVERSIDE PLAZA | H02G003/18 | H02G003/18 B23P011/00 B29C065/00 B29C065/56 B29C065/64 B64D045/02 F16B005/01 B29L031/00 B29L031/30 F16B001/00 | 6 | 7 | B29C0066/742 | B29C0066/742 B29C0065/565 B29C0065/64 B29C0066/131 B29C0066/474 B29C0066/7212 B29C0066/72141 B29C0066/73111 B29C0066/73141 B64D0045/02 F16B0005/01 B29C0066/74283 B29C2793/0045 B29C2793/0081 B29L2031/3076 B29L2031/737 F16B2001/0064 Y10T0029/49826 | B29C0066/742 B29C0065/565 B29C0065/64 B29C0066/131 B29C0066/474 B29C0066/7212 B29C0066/72141 B29C0066/73111 B29C0066/73141 B64D0045/02 F16B0005/01 B29C0066/74283 B29C2793/0045 B29C2793/0081 B29L2031/3076 B29L2031/7172 B29L2031/737 F16B2200/93 Y10T0029/49826 B29K2307/04 | - | - | Matthew Anthony Dilligan James P. Irwin Christopher Newbolt Peter A. Coronado Benjamin A. Johnson | 5 | US | WA Seattle WA Renton WA Seattle WA Renton WA Lynnwood | Robert Parker | - | - | Timothy Thompson | Timothy Thompson Sherman Ng | US3566662 US4702655 US5083363 US5341559 US7277266 US7387277 US2005/0262682 US2007/0110541 US2007/0180885 US2007/0295050 US2008/0078864 US2008/0101887 US2008/0250603 US2008/0297967 US2009/0035084 US2009/0178262 US2009/0304315 US2010/0108804 US2010/0219287 US2010/0260572 US2010/0320315 | 21 | EP0468563 | 1 | PCT, International Search Report and Written Opinion, PCT/US2012/054019 (Dec. 18, 2012).;Ransom, J. et al., “Hole Protection With Expanded Grommets in Carbon Fiber Reinforced Plastic,” Global Material Technology: Soaring to New Horizons: 2009 SAMPE Fall Technical Conference & Exhibition, Oct. 19-22, 2009, Wichita, Kansas; Covina: Society for the Advancement of Material and Process Engineering, Jan. 1, 2009, pp. 1-12. | 14 | 6 | EP2763899B1 US09108363 WO2013052230 | 3 | 3 | - | US20130087380 | 2013-04-11 | 6 | THE BOEING COMPANY | Overdue | ||||||||||
69 | US11213897 | B2 | 2022-01-04 | Method of assembling members of an assembly | invention | 16/423610 | 2019-05-28 | A method of assembling an aircraft assembly having a first member and a second member includes drilling at least one first opening through the first member, the at least one opening having a first diameter, and drilling at least one second opening through the second member, the at least one second opening having the first diameter. The method also includes forming a chamfer on the at least one first opening and the at least one second opening, the chamfer having a chamfer diameter, and positioning the first and second members to align the at least one first opening and the at least one second opening. The method further includes drilling the at least one first opening and the at least one second opening to a second diameter, wherein the second diameter is greater than the first diameter. | 1. A method of assembling an aircraft assembly including a first member and a second member, the method comprising: drilling at least one first opening through the first member, the at least one first opening having a first diameter;drilling at least one second opening through the second member, the at least one second opening having the first diameter;forming a chamfer on the at least one first opening and the at least one second opening, the chamfer having a chamfer diameter;positioning the first and second members using a plurality of determinate assembly features integrally formed on the first and second members to align the at least one first opening and the at least one second opening within a predetermined tolerance limit; anddrilling the at least one first opening and the at least one second opening to a second diameter, wherein the second diameter is greater than the first diameter, and wherein the predetermined tolerance limit is less than a difference between the chamfer diameter and the second diameter. | 1. A method of assembling an aircraft assembly including a first member and a second member, the method comprising: drilling at least one first opening through the first member, the at least one first opening having a first diameter;drilling at least one second opening through the second member, the at least one second opening having the first diameter;forming a chamfer on the at least one first opening and the at least one second opening, the chamfer having a chamfer diameter;positioning the first and second members using a plurality of determinate assembly features integrally formed on the first and second members to align the at least one first opening and the at least one second opening within a predetermined tolerance limit; anddrilling the at least one first opening and the at least one second opening to a second diameter, wherein the second diameter is greater than the first diameter, and wherein the predetermined tolerance limit is less than a difference between the chamfer diameter and the second diameter. 2. The method of claim 1, wherein forming the chamfer comprises forming the chamfer on two opposing ends of each of the at least one first opening and the at least one second opening. 3. The method of claim 2, wherein forming the chamfer comprises forming the chamfer at a first end of each of the at least one first opening and the at least one second opening simultaneously when drilling the at least one first opening and the at least one second opening at the first diameter. 4. The method of claim 3, wherein forming the chamfer comprises forming the chamfer at a second end of each of the at least one first opening and the at least one second opening after forming the chamfer at the first end of each of the at least one first opening and the at least one second opening. 5. The method of claim 1, wherein the chamfer diameter is greater than the second diameter. 6. The method of claim 1, further comprising installing a fastener through the at least one first opening and the at least one second opening to secure the first member to the second member. 7. The method of claim 1, wherein drilling the at least one first opening and drilling the at least one second opening at the first diameter is performed before the positioning step, and wherein forming the chamfer on the at least one first opening and the at least one second opening is performed before the positioning step. 8. The method of claim 1, further comprising smoothing an edge defined between the chamfer and the at least one first opening after drilling the at least one opening at the second diameter. 9. The method of claim 1, wherein drilling the at least one first opening comprises drilling the at least one first opening at the first diameter that is within a range of between 50 percent and 90 percent of the second diameter. 10. The method of claim 1, wherein positioning the first and second members using the plurality of determinate assembly features comprises aligning a ... | The Boeing Company | US | THE BOEING COMPANY | US | IL Chicago | THE BOEING COMPANY | US | 100 NORTH RIVERSIDE PLAZA | B23B035/00 | B23B035/00 B64F005/10 F16B005/02 F16B005/04 B23B041/00 | 3 | 4 | - | B23B0041/00 | B23B0041/00 B23B0035/00 B23B2215/04 B23B2220/04 B64F0005/10 F16B0005/02 F16B0005/04 | B23B0041/00 B23B0035/00 B23B2215/04 B23B2220/04 B64F0005/10 F16B0005/02 F16B0005/04 | - | - | - | - | - | - | - | Mark Steven Denman Stephen Richard Dark Gary A. Lipczynski | 3 | US | WA Poulsbo WA Lynnwood CA Garden Grove | Armstrong Teasdale LLP | - | - | Matthew P Travers | Matthew P Travers | US4800686 US4984347 US5265988 US6370752 US7627940 US7794183 US10105765 US2005/0288890 US2020/0191182 US2020/0400171 | 10 | DE102011122539 EP3208017 JP2000288813 JP2010247281 | 4 | Extended European Search Report for Application No. EP20169545.9 dated Oct. 16, 2020, 9 pgs. | 6 | 0 | EP3744642B1 US11213897 AU2020202051A1 | 3 | 3 | - | US20200376613 | 2020-12-03 | 14 | THE BOEING COMPANY | Valid | ||||
70 | EP2594349 | B1 | 2020-04-29 | Method for preparing highly-deformable titanium and titanium-alloy one-piece fasteners | invention | 12192230.6 | 2012-11-12 | A fastener has a cold-worked head section (204), a cold-worked shank section (212), and a ductile shank section (214) extending from the cold-worked shank section (212) to a tail end portion (210) of the fastener. | A method of manufacturing a fastener (200) which comprises a head (203) having a cold-worked head section (204), and a shank (206) having a cold-worked shank section (212) and a ductile shank section (214) extending from the cold-worked shank section (212) to a tail end portion (210) of the fastener (200), the ductile shank section (214) being non-cold-worked; the method comprising: providing a semi-tubular blank precursor (12) having a hollow tubular cavity (22), which extends at least partially into the semi-tubular blank precursor (12), and having an ultra-fine grain titanium or titanium-alloy composition having an average grain size of less than approximately 10 microns;forming the semi-tubular blank precursor (12) into a semi-tubular intermediarily-formed blank precursor (13) comprising installing the semi-tubular blank precursor (12) in a forming die (50), installing an insert tool (24) in the hollow tubular cavity (22) and applying an axial compression force to the semi-tubular blank precursor (12), the semi-tubular intermediarily-formed blank precursor (13) having an enlarged shank portion (32); andreducing a cross-sectional area of the enlarged shank portion by approximately 2 to 5 percent to form the cold-worked shank section (212) while a shaft of the insert tool is inserted into the hollow tubular cavity, the cold-worked head section and the cold-worked shank section having a higher strength than the ductile shank section. | A method of manufacturing a fastener (200) which comprises a head (203) having a cold-worked head section (204), and a shank (206) having a cold-worked shank section (212) and a ductile shank section (214) extending from the cold-worked shank section (212) to a tail end portion (210) of the fastener (200), the ductile shank section (214) being non-cold-worked; the method comprising: providing a semi-tubular blank precursor (12) having a hollow tubular cavity (22), which extends at least partially into the semi-tubular blank precursor (12), and having an ultra-fine grain titanium or titanium-alloy composition having an average grain size of less than approximately 10 microns;forming the semi-tubular blank precursor (12) into a semi-tubular intermediarily-formed blank precursor (13) comprising installing the semi-tubular blank precursor (12) in a forming die (50), installing an insert tool (24) in the hollow tubular cavity (22) and applying an axial compression force to the semi-tubular blank precursor (12), the semi-tubular intermediarily-formed blank precursor (13) having an enlarged shank portion (32); andreducing a cross-sectional area of the enlarged shank portion by approximately 2 to 5 percent to form the cold-worked shank section (212) while a shaft of the insert tool is inserted into the hollow tubular cavity, the cold-worked head section and the cold-worked shank section having a higher strength than the ductile shank section. The method of claim 1 wherein: the ductile shank section (214) has a higher level of ductility than the cold-worked head section (204) and the cold-worked shank section (212). The method of any of the preceding claims wherein: the cold-worked head section (204) and the cold-worked shank section (212) are formed by a cold-working process. --> A method of assembling a structure (250), comprising: providing the fastener (200) manufactured as defined in any one of claims 1 to 3;installing the fastener (200) in a hole (258) of the structure (250); andupsetting the tail end portion (210) of the ductile shank section (214). The method of claim 4 further comprising: providing the fastener (200) coated with a corrosion-resistant, curable organic coating material. The method of any of Claims 4 to 5; wherein installing the fastener (200) in the hole (258) of the structure (250) comprises: installing the fastener (200) in an aircraft structure. | The Boeing Company | The Boeing Company | US | 100 North Riverside Plaza Chicago, IL 60606-1596 | - | - | - | B21J015/02 | B21J015/02 B21K001/58 F16B019/06 | 3 | 3 | - | - | - | - | - | 201113299228 | 2011-11-17 | US | Keener, Steven G. | 1 | US | Trabuco Canyon CA California 92679-1185 | Witte, Weller & Partner Patentanwälte mbB | - | - | - | 0 | US2006 177 284 US20060177284 | 2 | 13 | 0 | EP2594349B1 US10589342 JP6258580 CN103122900B US09649682 US20130125376 CA2792752C CA2792752A1 BR102012029191B1 BR102012029191A2 | 10 | 6 | - | EP2594349 | 2015-07-15 | 7 | THE BOEING COMPANY | ||||||||||||
71 | EP3053679 | B1 | 2019-12-18 | INTERMETALLIC AND COMPOSITE METALLIC GAP FILLER | invention | 16153588.5 | 2016-02-01 | A structural assembly of an aircraft which includes a structural element constructed of a composite material which includes a matrix material and plurality of fibers positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers are accessible from a surface of the structural element. A fastener secures the structural element to a structural component. A metal structure comprising gallium is positioned in contact with a surface of the fastener. The metal structure extends from the surface of the fastener and contacts at least a portion of the at least a portion of the plurality of fibers. Also included is a method for assembling a structure. | A structural assembly (14) of an aircraft (10), comprising: a structural element (20, 26) constructed of a composite material comprising a matrix material (22, 28) and a plurality of fibers (24, 30) positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers are accessible from a surface (48, 50, 52) of the structural element;a fastener (34) secures the structural element to a structural component (32); anda metal structure (56) positioned in contact with a surface (38) of the fastener, wherein the metal structure extends from the surface of the fastener and contacts at least a portion (25) of the at least a portion of the plurality of fibers, wherein the metal structure (56) comprises a gallium alloy,wherein the metal structure (56) is obtainable by: mixing a liquid metal alloy comprising gallium with at least one of a solid metal and solid metal alloy forming a slurry (56); andapplying the slurry onto a surface (38) of a fastener (34) and onto at least a portion (25) of the at least a portion of the plurality of fibers. | A structural assembly (14) of an aircraft (10), comprising: a structural element (20, 26) constructed of a composite material comprising a matrix material (22, 28) and a plurality of fibers (24, 30) positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers are accessible from a surface (48, 50, 52) of the structural element;a fastener (34) secures the structural element to a structural component (32); anda metal structure (56) positioned in contact with a surface (38) of the fastener, wherein the metal structure extends from the surface of the fastener and contacts at least a portion (25) of the at least a portion of the plurality of fibers, wherein the metal structure (56) comprises a gallium alloy,wherein the metal structure (56) is obtainable by: mixing a liquid metal alloy comprising gallium with at least one of a solid metal and solid metal alloy forming a slurry (56); andapplying the slurry onto a surface (38) of a fastener (34) and onto at least a portion (25) of the at least a portion of the plurality of fibers. The structural assembly of claim 1, wherein: the plurality of fibers comprises carbon; the matrix material comprises one of a thermoplastic resin and thermosetting resin; and the fastener is constructed of a metal. The structural assembly of any of claims 1-2, wherein the gallium alloy of the metal structure comprises at least one of indium and tin. The structural assembly of any of claims 1-3, wherein the metal structure further comprises one of a solid metal and a solid metal alloy. The structural assembly of claim 4, wherein: the one of the solid metal and the solid metal alloy comprises one of a powder and a film; and -->a particle size of the powder or a thickness of the film has a dimension in a range between 50 nm and 100 µm. The structural assembly of claim 5, wherein the solid metal comprises one of pure copper, pure silver, and pure nickel. The structural assembly of any of claims 5-6, wherein the solid metal alloy comprises bronze. The structural assembly of any of claims 1-4, wherein the metal structure further comprises a mechanical reinforcing phase comprising one of pure cobalt, pure tungsten, pure molybdenum, and pure titanium or an alloy comprising one of a titanium alloy and a stainless steel. The structural assembly of any of claims 1-4 or 8, wherein: the metal structure extends in a range between 25 µm and 1 mm between the surface of the fastener to at least a portion of the portion of the plurality of fibers; andthe metal structure is in contact with the surface of the structural element. A method for assembling a structure (10), comprising the steps of: providing a structural element (20, 26) constructed of a composite material comprising a matrix material (22, 28) and a plurality of fibers (24, 30) positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers are accessible from a surface (48, 50, 52) of the stru... | The Boeing Company | The Boeing Company | US | 100 North Riverside Plaza Chicago, IL 60606-1596 | - | - | - | B22F007/06 | B22F007/06 B05D007/00 B29C065/00 C23F013/00 B29C065/56 B64D037/32 B29L031/30 B29C070/88 B64D045/02 F16B001/00 | 7 | 9 | - | - | - | - | - | 201514614656 | 2015-02-05 | US | GROSS, Adam Franklin | 1 | US | Chicago, IL 60606-2016 | Boult Wade Tennant LLP | - | - | - | 0 | FR2 765 066 US4 755 904 US2013 099 490 US4755904 FR2765066 US20130099490 | 6 | 9 | 0 | JP6719218 EP3053679B1 CN116331503A CN105857629A US20160229552 CA2913166C BR102015031874B1 CA2913166A1 BR102015031874A2 | 9 | 6 | - | EP3053679 | 2016-08-10 | 11 | THE BOEING COMPANY | ||||||||||||
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