Saturn INT-20

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Saturn INT-20

Part of Saturn V

S-1C details
Credit: © Mark Wade

American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage.

Status: Study 1967. Payload: 60,000 kg (132,000 lb). Thrust: 33,737.90 kN (7,584,582 lbf). Gross mass: 2,478,120 kg (5,463,310 lb). Height: 72.00 m (236.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

Liftoff Mass - kg	S-IC - No. F-1 Motors	Payload - kg - 4.68 G limit	Payload - kg - 6.0 G limit
1,107,000	2	36,000	27,000
1,655,000	3	78,000	47,000
2,209,000	4	132,000	63,000
2,299,000	5	133,000	72,000

LEO Payload: 60,000 kg (132,000 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 391.500 million.

Stage Data - Saturn INT-20

Stage 1. 1 x Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Out of Production.

Stage 3. 1 x Saturn IVB (S-V). Gross Mass: 119,900 kg (264,300 lb). Empty Mass: 13,300 kg (29,300 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Out of Production. Comments: Saturn V version of S-IVB stage.

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1. Stages: Saturn IC, Saturn IVB (S-V).

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