Encyclopedia Astronautica
Saturn V-C


American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.

LEO Payload: 81,600 kg (179,800 lb) to a 185 km orbit at 28.00 degrees. Payload: 20,400 kg (44,900 lb) to a translunar trajectory.

Stage Data - Saturn V-C

  • Stage 0. 1 x Saturn S-ID Booster. Gross Mass: 67,100 kg (147,900 lb). Empty Mass: 67,100 kg (147,900 lb). Thrust (vac): 30,962.500 kN (6,960,647 lbf). Isp: 304 sec. Burn time: 154 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: F-1. Status: Study 1967. Comments: Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example).
  • Stage 1. 1 x Saturn S-ID Sustainer. Gross Mass: 2,219,100 kg (4,892,200 lb). Empty Mass: 68,100 kg (150,100 lb). Thrust (vac): 7,740.300 kN (1,740,089 lbf). Isp: 304 sec. Burn time: 315 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: F-1. Status: Study 1967. Comments: Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration.
  • 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.

Status: Study 1968.
Gross mass: 2,504,020 kg (5,520,410 lb).
Payload: 81,600 kg (179,800 lb).
Height: 72.00 m (236.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 33,737.70 kN (7,584,537 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
See also
  • Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...
  • Saturn V America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration. More...

Associated Manufacturers and Agencies
  • Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...

Associated Stages
  • Saturn IVB (S-V) Lox/LH2 propellant rocket stage. Loaded/empty mass 119,900/13,300 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn V version of S-IVB stage for use with upper stage. More...
  • Saturn S-ID Booster Lox/Kerosene propellant rocket stage. Loaded/empty mass 67,100/67,100 kg. Thrust 30,962.50 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example). More...
  • Saturn S-ID Sustainer Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,219,100/68,100 kg. Thrust 7,740.30 kN. Vacuum specific impulse 304 seconds. Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration. More...

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