Encyclopedia Astronautica
Saturn IB-A



satiba.gif
Saturn IB-A
Credit: © Mark Wade
American orbital launch vehicle. Douglas Studies, 1965: S-IB with 225 k lbf H-1's; S-IVB stretched with 350,000 lbs propellants; Centaur third stage.

LEO Payload: 18,600 kg (41,000 lb) to a 185 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 20.300 million.

Stage Data - Saturn IB-A

  • Stage 1. 1 x Saturn S-IB-A. Gross Mass: 448,600 kg (988,900 lb). Empty Mass: 41,600 kg (91,700 lb). Thrust (vac): 9,045.600 kN (2,033,532 lbf). Isp: 296 sec. Burn time: 128 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1c. Status: Study 1965. Comments: Douglas Studies, 1965: S-1B with 225 k lbf H-1's.
  • Stage 2. 1 x Saturn IVB-A. Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 956.100 kN (214,940 lbf). Isp: 421 sec. Burn time: 450 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: Study 1965. Comments: Douglas Studies, 1965: S-IVB with 215k lbf J-1 (actual final model had 230k J-1).
  • Stage 3. 1 x Centaur D/E. Gross Mass: 16,258 kg (35,842 lb). Empty Mass: 2,631 kg (5,800 lb). Thrust (vac): 131.222 kN (29,500 lbf). Isp: 444 sec. Burn time: 470 sec. Isp(sl): 0.0000 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.60 m (31.40 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3. Status: Out of Production.

Status: Study 1965.
Gross mass: 605,980 kg (1,335,950 lb).
Payload: 18,600 kg (41,000 lb).
Height: 62.00 m (203.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 8,006.60 kN (1,799,955 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • H-1c Rocketdyne Lox/Kerosene rocket engine. 1130 kN. Study Saturn IB-A, Saturn IB-B, 1965. Isp=296s. More...
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...
  • RL-10A-3 Pratt and Whitney lox/lh2 rocket engine. 65.6 kN. Study 1968. Isp=444s. First flight 1967. More...

See also
  • Saturn I Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it. More...
  • 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...

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

Associated Stages
  • Centaur D/E Lox/LH2 propellant rocket stage. Loaded/empty mass 16,258/2,631 kg. Thrust 131.22 kN. Vacuum specific impulse 444 seconds. More...
  • Saturn IVB-A Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 956.10 kN. Vacuum specific impulse 421 seconds. Douglas Studies, 1965: S-IVB with 215k lbf J-1 (actual final model had 230k J-1) More...
  • Saturn S-IB-A Lox/Kerosene propellant rocket stage. Loaded/empty mass 448,600/41,600 kg. Thrust 9,045.60 kN. Vacuum specific impulse 296 seconds. Douglas Studies, 1965: S-1B with 225 k lbf H-1's More...

Home - Browse - Contact
© / Conditions for Use