Saturn C-8 Credit - Mike Robel

Orbital launch vehicle. Family:

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.

Manufacturer: Von Braun. LEO Payload: 210,000 kg (460,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 74,000 kg (163,000 lb). to a: Translunar trajectory. Liftoff Thrust: 53,981.000 kN (12,135,411 lbf). Total Mass: 4,770,260 kg (10,516,620 lb). Core Diameter: 12.19 m (39.99 ft). Total Length: 131.00 m (429.00 ft). Flyaway Unit Cost $: 58.290 million. in: 1985 unit dollars.

• Stage1: 1 x Saturn S-IC-8. Gross Mass: 3,627,500 kg (7,997,200 lb). Empty Mass: 181,400 kg (399,900 lb). Motor: 8 x F-1. Thrust (vac): 61,925.000 kN (13,921,293 lbf). Isp: 304 sec. Burn time: 157 sec. Length: 48.79 m (160.07 ft). Diameter: 12.19 m (39.99 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Saturn S-II-8. Gross Mass: 770,835 kg (1,699,400 lb). Empty Mass: 63,480 kg (139,940 lb). Motor: 8 x J-2. Thrust (vac): 8,265.260 kN (1,858,104 lbf). Isp: 425 sec. Burn time: 338 sec. Length: 42.68 m (140.02 ft). Diameter: 10.06 m (33.00 ft). Propellants: Lox/LH2.

• Stage3: 1 x Saturn IVB. Gross Mass: 119,920 kg (264,370 lb). Empty Mass: 13,311 kg (29,345 lb). Motor: 1 x J-2. Thrust (vac): 1,031.983 kN (231,999 lbf). Isp: 425 sec. Burn time: 475 sec. Length: 17.80 m (58.30 ft). Diameter: 6.61 m (21.68 ft). Propellants: Lox/LH2.

1962 May 25 - Apollo lunar landing mode component schedules and cost breakdowns prepared 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.