Encyclopedia Astronautica
Saturn V-3B


American orbital launch vehicle. Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine.

LEO Payload: 166,600 kg (367,200 lb) to a 185 km orbit at 28.00 degrees. Payload: 72,800 kg (160,400 lb) to a translunar trajectory.

Stage Data - Saturn V-3B

  • Stage 1. 1 x Saturn MS-IC-3B. Gross Mass: 2,718,800 kg (5,993,900 lb). Empty Mass: 178,700 kg (393,900 lb). Thrust (vac): 45,925.500 kN (10,324,463 lbf). Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study Boeing 1967. Comments: S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission).
  • Stage 2. 1 x Saturn MS-II-3B. Gross Mass: 643,200 kg (1,418,000 lb). Empty Mass: 53,500 kg (117,900 lb). Thrust (vac): 12,455.400 kN (2,800,085 lbf). Isp: 447 sec. Burn time: 204 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.56 m (96.98 ft). Propellants: Lox/LH2. No Engines: 5. Engine: Toroidal 400k. Status: Study Boeing 1967. Comments: S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines.
  • Stage 3. 1 x Saturn MS-IVB-3B. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,778.900 kN (399,913 lbf). Isp: 447 sec. Burn time: 385 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: Toroidal 400k. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 400,000 pound thrust toroidal engine.

Status: Study 1967.
Gross mass: 3,741,120 kg (8,247,750 lb).
Payload: 166,600 kg (367,200 lb).
Height: 121.00 m (396.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 40,033.80 kN (8,999,956 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s. More...
  • Toroidal 400k Notional lox/lh2 rocket engine. 1778 kN. Study 1967. Isp=447s. Used on Saturn V-3B launch vehicle. More...

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 MS-IC-3B Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,718,800/178,700 kg. Thrust 45,925.50 kN. Vacuum specific impulse 304 seconds. S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission). More...
  • Saturn MS-IVB-3B Lox/LH2 propellant rocket stage. Loaded/empty mass 179,200/20,400 kg. Thrust 1,778.90 kN. Vacuum specific impulse 447 seconds. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 400,000 pound thrust toroidal engine. More...
  • Saturn MS-II-3B Lox/LH2 propellant rocket stage. Loaded/empty mass 643,200/53,500 kg. Thrust 12,455.40 kN. Vacuum specific impulse 447 seconds. S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines. More...

Home - Browse - Contact
© / Conditions for Use