Encyclopedia Astronautica
Saturn A-2

Saturn A-2
Credit: © Mark Wade
Saturn A-1 to C-5
Credit: © Mark Wade
American orbital launch vehicle. More powerful version of Saturn I with low energy second stage consisting of cluster of four IRBM motors and tankage, Centaur third stage. Masses, payload estimated.

LEO Payload: 10,000 kg (22,000 lb) to a 185 km orbit at 38.00 degrees. Payload: 2,000 kg (4,400 lb) to a translunar trajectory in 1985 dollars. Flyaway Unit Cost $: 63.800 million.

Stage Data - Saturn A-2

  • Stage 1. 1 x Saturn IB. Gross Mass: 448,648 kg (989,099 lb). Empty Mass: 41,594 kg (91,699 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 155 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-1b. Status: Out of Production.
  • Stage 2. 1 x Jupiter Cluster. Gross Mass: 226,716 kg (499,823 lb). Empty Mass: 27,205 kg (59,976 lb). Thrust (vac): 3,034.285 kN (682,134 lbf). Isp: 282 sec. Burn time: 172 sec. Isp(sl): 248 sec. Diameter: 5.34 m (17.51 ft). Span: 5.34 m (17.51 ft). Length: 18.28 m (59.97 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: S-3. Status: Study 1959. Comments: Masses estimated (cluster of four Jupiter IRBM stages).
  • Stage 3. 1 x Centaur C. Gross Mass: 15,600 kg (34,300 lb). Empty Mass: 1,996 kg (4,400 lb). Thrust (vac): 133.448 kN (30,000 lbf). Isp: 425 sec. Burn time: 430 sec. Isp(sl): 0.0000 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.14 m (29.98 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-1. Status: Out of Production.

Status: Study 1959.
Gross mass: 702,960 kg (1,549,760 lb).
Payload: 10,000 kg (22,000 lb).
Height: 62.00 m (203.00 ft).
Diameter: 6.52 m (21.39 ft).
Thrust: 7,295.10 kN (1,640,004 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...

Associated Countries
Associated Engines
  • H-1b Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966. More...
  • RL-10A-1 Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=425s. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961. More...
  • S-3 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Juno II, Saturn A-2 studies of 1959. Isp=282s. First flight 1958. 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 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...

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

Associated Stages
  • Centaur C Lox/LH2 propellant rocket stage. Loaded/empty mass 15,600/1,996 kg. Thrust 133.45 kN. Vacuum specific impulse 425 seconds. The first high-energy liquid oxygen/liquid hydrogen propellant stage in history. Despite initial development problems, the Centaur is entering its sixth decade of development and production. More...
  • Jupiter Cluster Lox/Kerosene propellant rocket stage. Loaded/empty mass 226,716/27,205 kg. Thrust 3,034.29 kN. Vacuum specific impulse 282 seconds. Masses estimated (cluster of four Jupiter IRBM stages) More...
  • Saturn IB Lox/Kerosene propellant rocket stage. Loaded/empty mass 448,648/41,594 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. Configuration as flown, Saturn IB. More...

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