Saturn C-8

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Saturn C-8

Part of Nova

Saturn C-8
Model of Saturn C-8 configuration
Credit: Mike Robel

American orbital launch vehicle. The largest member of the Saturn family ever contemplated. Designed for direct landing of Apollo command module on moon. Configuration used eight F-1 engines in the first stage, eight J-2 engines in the second stage, and one J-2 engine in the third stage. Distinguishable from Nova 8L in use of J-2 engines instead of M-1 engines in second stage.

Status: Study 1960. Payload: 210,000 kg (460,000 lb). Thrust: 53,981.00 kN (12,135,411 lbf). Gross mass: 4,770,260 kg (10,516,620 lb). Height: 131.00 m (429.00 ft). Diameter: 12.19 m (39.99 ft). Apogee: 185 km (114 mi).

LEO Payload: 210,000 kg (460,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 74,000 kg (163,000 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 58.290 million.

Stage Data - Saturn C-8

Stage 1. 1 x Saturn S-IC-8. Gross Mass: 3,627,500 kg (7,997,200 lb). Empty Mass: 181,400 kg (399,900 lb). Thrust (vac): 61,925.000 kN (13,921,293 lbf). Isp: 304 sec. Burn time: 157 sec. Isp(sl): 265 sec. Diameter: 12.19 m (39.99 ft). Span: 22.87 m (75.03 ft). Length: 48.79 m (160.07 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: F-1. Status: Study 1960.

Stage 2. 1 x Saturn S-II-8. Gross Mass: 770,835 kg (1,699,400 lb). Empty Mass: 63,480 kg (139,940 lb). Thrust (vac): 8,265.260 kN (1,858,104 lbf). Isp: 425 sec. Burn time: 338 sec. Isp(sl): 306 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 42.68 m (140.02 ft). Propellants: Lox/LH2. No Engines: 8. Engine: J-2. Status: Study NASA Feb 62.

Stage 3. 1 x Saturn IVB. Gross Mass: 119,920 kg (264,370 lb). Empty Mass: 13,311 kg (29,345 lb). Thrust (vac): 1,031.983 kN (231,999 lbf). Isp: 425 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.

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1, J-2. Spacecraft: Apollo Lunar Landing. Stages: Saturn IVB, Saturn S-IC-8, Saturn S-II-8. Bibliography: 222, 228, 8591.

Photo Gallery

1962 May 25 - . LV Family: Nova. Launch Vehicle: Saturn C-8.

Apollo lunar landing mode component schedules and cost breakdowns prepared - . Nation: USA. Related Persons: Holmes, Brainard. Program: Apollo. Spacecraft: Apollo Lunar Landing.
D. Brainerd Holmes, NASA's Director of Manned Space Flight, requested the Directors of Launch Operations Center, Manned Spacecraft Center, and Marshall Space Flight Center (MSFC) to prepare supporting component schedules and cost breakdowns through Fiscal Year 1967 for each of the proposed lunar landing modes: earth orbit rendezvous, lunar orbit rendezvous, and direct ascent. For direct ascent, a Saturn C-8 launch vehicle was planned, using a configuration of eight F-1 engines, eight J-2 engines, and one J-2 engine. MSFC was also requested to submit a proposed schedule and summary of costs for the Nova launch vehicle, using the configuration of eight F-1 engines, two M-1 engines, and one J-2 engine. Each Center was asked to make an evaluation of the schedules as to possibilities of achievement, major problem areas, and recommendations for deviations.

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