Credit: © Mark Wade
Credit: © Mark Wade
American orbital launch vehicle. The very first design that would lead to Saturn. A 1.5 million pound thrust booster using four E-1 engines - initial consideration of using a single USAF F-1 engine abandoned because of development time. Existing missile tankage was clustered above the engines.
The design effort began in April 1957, with variants studied with a single F-1 engine, four E-1 engines, or 8-9 H-1 engines. In at least one variant the second stage was powered by a single E-1 engine, and the third stage by an S-4, a variant of the Rocketdyne LR105. The propellant tankage seems to have consisted of a cluster of Redstone tanks, given the total diameter indicated. The empty masses of the stages seem remarkably optimistic. In the event, ARPA indicated that they did not want the two year delay waiting for E-1 development would entail, and Von Braun's team turned to a cluster of 8 H-1 engines in the first stage and two in the second. This was designated Juno-V and led to the Saturn series. Super-Jupiter withered away by September 1959.
LEO Payload: 11,000 kg (24,000 lb) to a 185 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 14.000 million.
Stage Data - Super-Jupiter
- Stage 1. 1 x Super-Jupiter. Gross Mass: 317,600 kg (700,100 lb). Empty Mass: 19,600 kg (43,200 lb). Thrust (vac): 7,538.300 kN (1,694,677 lbf). Isp: 290 sec. Burn time: 110 sec. Isp(sl): 260 sec. Diameter: 5.23 m (17.15 ft). Span: 5.23 m (17.15 ft). Length: 22.00 m (72.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: E-1. Status: Development 1958. Comments: Earliest member of what would become the Saturn family. Masses estimated.
- Stage 2. 1 x Titan 1-1. Gross Mass: 76,203 kg (167,998 lb). Empty Mass: 4,000 kg (8,800 lb). Thrust (vac): 1,467.908 kN (329,999 lbf). Isp: 290 sec. Burn time: 138 sec. Isp(sl): 256 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 16.00 m (52.00 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: LR-87-3. Status: Out of Production.
- Stage 3. 1 x Titan 1-2. Gross Mass: 28,939 kg (63,799 lb). Empty Mass: 1,725 kg (3,802 lb). Thrust (vac): 355.863 kN (80,001 lbf). Isp: 308 sec. Burn time: 225 sec. Isp(sl): 210 sec. Diameter: 2.26 m (7.41 ft). Span: 2.26 m (7.41 ft). Length: 9.80 m (32.10 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: LR-91-3. Status: Out of Production.
Status: Study 1957.
More... - Chronology...
Gross mass: 572,840 kg (1,262,890 lb).
Payload: 11,000 kg (24,000 lb).
Height: 60.00 m (196.00 ft).
Diameter: 9.15 m (30.01 ft).
Thrust: 6,758.50 kN (1,519,371 lbf).
Apogee: 185 km (114 mi).
E-1 Rocketdyne Lox/Kerosene rocket engine. 1885 kN. Study 1957. Developed by USAF in late 1950's. Cancelled and decision to go direct to 1,500,000 lbf F-1 as next step. Booster applications. Gas generator, pump-fed. Isp=290s. More...
LR87-3 Aerojet Lox/Kerosene rocket engine. 733.9 kN. Study 1957. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. Isp=290s. First flight 1959. More...
LR91-3 Aerojet Lox/Kerosene rocket engine. 355.9 kN. Development begun 1957. Titan 1 Stage 2 major production version. Isp=308s. Proposed for second stage of Juno V-A, Super-Jupiter in 1959. Flown 1959-1965. More...
S-4 Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only. Used on Super Jupiter launch vehicle. 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...
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...
Super-Jupiter Lox/Kerosene propellant rocket stage. Loaded/empty mass 317,600/19,600 kg. Thrust 7,538.30 kN. Vacuum specific impulse 290 seconds. Earliest member of what would become the Saturn family. Masses estimated. More...
Titan 1-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 76,203/4,000 kg. Thrust 1,467.91 kN. Vacuum specific impulse 290 seconds. More...
Titan 1-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 28,939/1,725 kg. Thrust 355.86 kN. Vacuum specific impulse 308 seconds. More...
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