SS_SH_2021.xlsx

	A	B	C	D	E	F	G	H	I	J	K	L	M	N	O	P	Q	R	S	T
1	2024 Reverse Engineering of Spacex Starship / Superheavy to LEO (circular)												75570	13200						@dropdown
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3	Superheavy booster stage				Starship upper stage/spacecraft					SL Raptor engines @ 100%			Vac Raptor engines @ 100%				final weight statements
4	inert mtn	prop mtn	eng type	no. eng.	inert mtn	prop mtn	payld mtn	eng type	no.eng	where	F, MN	Isp, s	where	F, KN	Isp, s		SS inert	120
5	250	3600	SL	33	120	2000	150	SL	3	SL	2.29	334.4	vac	2.232	381.3		SS payload	150
6								vac	3	50 kft	2.092	357.4	100 kft	2.224	379.9		SSdrytanks	270
7	Vstg km/s	rvloss km/s	X, km/s	stg1 loss	surf Vcirc	stg2 loss				vac	2.11	360.4					max prop	2000
8	2.23	0.1	0.7	0.632	7.886	0.1567				avg asc	2.034	347.4					SS max ign	2270	m.tons
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10	booster flyback determines ascent performance (MR-eff dV's)									Starship		Superheavy at stg		Superheavy at launch			SH inert	200
11	burn	dV, km/s	Isp, s	Vex, km/s	req mass ratio	Mass Final mtn	Mass init mtn	dM mtn	prop rem t	inert	120	inert	250	inert	250		SH payload	2270
12	landing	0.45	334.4	3.28	1.15	250.00	286.77	36.77	36.77	payload	150	payload	2270	payload	2270		SHdrytanks	2470
13	entry	1.172	357.4	3.50	1.00	286.77	286.77	0.00	36.77	propellant	2000	prop rem	441.82	prop rem	3600		max prop	3600
14	reversal	3.112457469	360.4	3.53	2.41	286.77	691.82	405.05	441.82	ign	2270	ign	2961.816347	ign	6120		SH max ign	6070	m.tons
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16	Starship descent (MR-eff dV's)									need >0		Superheavy ascent					Vstg, km/s	2.23
17	burn	dV, km/s	Isp, s	Vex, km/s	req MR	Mfin mtn	Min mtn	dM mtn	prop rem t	err km/s	fact dV k/s	MR	Isp, s	Vex km/s	dV km/s		max payld	150	m.tons
18	landing	0.15	334.4	3.279350448	1.046803008	270	282.6368123	12.63681226	12.63681226	-0.3894559572	2.862	2.066299623	347.4	3.406837158	2.472544043
19	deorbit	0.1	381.3	3.739283271	1.027103899	282.6368123	290.2973718	7.660559503	20.29737177	sets vstg for a given ultimate payload							to circular LEO eastward
20									propellant req'd for landing with full payload^								able to abort with payload
21											meeting mission thrust reqmnts & limits						300x300 km
22	Starship on-orbit		Starship at staging		Starship ascent from staging					need > 0	condition	mass mtn	W, MN	no. eng.	T/W
23	inert	120	inert	120	MR	Isp, s	Vex, km/s	dV, km/s	reqdV k/s	err km/s	launch	6120	60.0168204	33	1.259147011	1.5 des'd, > 1.1 req'd
24	payload	150	payload	150	7.819567867	381.3	3.739283271	7.69031951	5.8127	1.87761951	stg1 bo	2961.816347	29.04555552	33	2.397268662	<6 req'd per user manual
25	prop rem	20.29737177	prop rem	2000						sets max payload^	stg2 bo	290.2973718	2.846850527	3	2.352072909	<6 req'd per user manual
26	ign	290.2973718	ign	2270							SS deorbit	290.2973718	2.846850527	1	0.7812141801	>0.5 req'd to be "impulsive"
27											SS landing	270	2.6478009	3	2.594605961	>1.5 req'd for net kinematic 0.5 gee vertical
28		Notes:									SH reversal	691.816347	6.784414616	3	0.9330208071	>0.8 req'd for net kinematic 0.1 gee vertical
29		1.spreadsheet set up for appropriate input engine choices and performances							redQs		SH entry	286.77	2.812266388	3	2.231652032	>1.5 req'd for net kinematic 0.5 gee vertical
30		2. user should essentially almost zero the stage velocity margin first							749,250		SH landing	286.77	2.812266388	2	1.628579718	>1.5 req'd for net kinematic 0.5 gee vertical
31		3. user should then maximize payload by nearly zeroing stg 2 dV margin									SSland0pay	120	1.1768004	1	1.777701639	>1.5 req'd for net kinematic 0.5 gee vertical
32		4. do not let payload drive stage velocity margin negative
33		5. adjust number of operating engines to meet thrust reqmnts & limits
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