Build a Better Saturn

	B	C	E	F	G	H	I	J	K	L	M
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2	Global		TOTAL dV past TLI: -498 m/s								Excess past TLI....
3	Payload (kg)	130000	OK: Rocket taller than Saturn V				OK: Second-stage engines well-spaced				To Mercury Injection - 2290m/s
4	Max vehicle dia. (m)	10	2	4.00	5.00	6.00	OK: Good second-stage T/W				To Venus Injection - 140m/s
5	Payload height (m)	25	OK: Fineness ratio is good				OK: Second stage suborbital				To Mars Injection - 340m/s
6	Optional: LES (kg)	0	OK: Stage length good				OK: Good third stage structure				To Jupiter Injection - 3040m/s
7	Payload fairing (y/n)	y	OK: Good first stage structure				OK: Third-stage engines well-spaced				To Saturn Injection - 4030m/s
8			OK: First-stage engines well-spaced				OK: Good third-stage T/W				To Uranus Injection - 4720m/s
9	v_cap = 1/6pi()h(3r^2+h^2)		WARNING: First stage cannot get off the ground				WARNING: not enough dV for TLI				To Neptune Injection - 4990m/s
10	A = pi()*(r^2 + h^2)		OK: High-altitude first stage burnout				OK: Good payload to TLI				To Solar Escape - 5490m/s
11			OK: Good second stage structure				GLOW greater than Saturn V
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13	Stage 1		interstage mass	960.66	total dV	3,920.77	net dV	2230.26	used dia.	80%
14	Stage height (m)	40	engine mass	42,000.00	burnout	1,445,592.55	total dV	2230.26	req dias	2.70
15	Struct. density (kg/m^2)	45	tank mass	95,328.68	startup	5,382,888.05	burn time	302.24	cuml bal	80%
16	Engine	F-1	tank vol	3,881.97	TWR_start	0.64	cosdrag	1365.35	dia ratio	3.38
17	No. of engines	5	prop mass	3,937,295.50	TWR_end	2.74	aerodrag	151.21
18	Stage diameter	12.5	total dry	144,328.42	mass flow	13,027.12	stage balance	80%	mass v S-V	181.53%
19	Bulkheads	4
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21	Stage 2		interstage mass	768.53	total dV	2,973.61	net dV	2606.79	used dia.	82%
22	Stage height (m)	30	engine mass	22,155.65	burnout	665,454.76	total dV	4837.04	req dias	4.52
23	Struct. density (kg/m^2)	20.00	tank mass	21,586.51	startup	1,301,264.13	burn time	264.72	cuml bal	69%
24	Engine	BE-3U	tank vol	1,849.21	TWR_start	0.83	cosdrag	366.83	dia ratio	5.49
25	No. of engines	15	prop mass	635,809.37	TWR_end	1.63	aerodrag	0.00
26	Stage diameter	10	total dry	44,510.69	mass flow	2,401.83	stage balance	62%	R_fine	12.34
27	Bulkheads	4
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29	Stage 3				total dV	6,125.80	net dV	5497.63	used dia.	55%
30	Stage height (m)	22	engine mass	10,339.30	burnout	155,979.78	total dV	10334.67	req dias	3.00
31	Struct. density (kg/m^2)	18.00	tank mass	14,288.15	startup	620,944.07	burn time	414.83	cuml bal	95%
32	Engine	BE-3U	tank vol	1,352.32	TWR_start	0.82	cosdrag	628.17	dia ratio	5.49
33	No. of engines	7	prop mass	464,964.30	TWR_end	3.25	aerodrag	0.00
34	Stage diameter	10	total dry	25,979.78	mass flow	1,120.85	stage balance	143%	PBF mass	6039.08
35	Bulkheads	3
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