|Saturn A-1 to C-5|
Credit: © Mark Wade. 12,176 bytes. 639 x 461 pixels.
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.
LEO Payload: 210,000 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 74,000 kg. to a: Translunar trajectory. Liftoff Thrust: 5,504,500 kgf. Total Mass: 4,770,260 kg. Core Diameter: 12.2 m. Total Length: 131.0 m. Flyaway Unit Cost $: 58.29 million. in 1985 unit dollars.
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.