Super-Jupiter Credit - © Mark Wade

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.

Manufacturer: Von Braun. LEO Payload: 11,000 kg (24,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 6,758.500 kN (1,519,371 lbf). Total Mass: 572,840 kg (1,262,890 lb). Core Diameter: 9.15 m (30.01 ft). Total Length: 60.00 m (196.00 ft). Flyaway Unit Cost $: 14.000 million. in: 1985 unit dollars.

By 1958 the Super-Jupiter was called Juno V and the 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage. The A version had a Titan I ICBM as the upper stages. Masses, payload estimated.

Manufacturer: Von Braun. LEO Payload: 10,000 kg (22,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 6,690.000 kN (1,503,970 lbf). Total Mass: 549,820 kg (1,212,140 lb). Core Diameter: 6.52 m (21.39 ft). Total Length: 60.00 m (196.00 ft). Flyaway Unit Cost $: 57.500 million. in: 1985 unit dollars.

A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated.

Manufacturer: Von Braun. LEO Payload: 12,500 kg (27,500 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 3,500 kg (7,700 lb). to a: Translunar trajectory. Liftoff Thrust: 6,690.000 kN (1,503,970 lbf). Total Mass: 539,480 kg (1,189,340 lb). Core Diameter: 6.52 m (21.39 ft). Total Length: 60.00 m (196.00 ft). Flyaway Unit Cost $: 73.800 million. in: 1985 unit dollars.

• Stage Number: 1. 1 x Stage: 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: Study 1957. Earliest member of what would become the Saturn family. Masses estimated.

• Stage Number: 2. 1 x Stage: 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: Study 1957.

• Stage Number: 3. 1 x Stage: 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: Study 1957.

1958 - Launch Vehicle: Super-Jupiter. Model: Juno V-A.

• Juno V heavy space launch design Nation: USA. The Von Braun team's Super-Jupiter evolved into the Juno V. The 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage.

• Bilstein, Roger E, Stages to Saturn, US Government Printing Office, 1980. ISBN: 0160489091. Excellent account of the evolution, design, and development of the Saturn launch vehicles. More at amazon.com...

• Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.