The Juno-5 was designed to be air-transportable and assembled at austere launch pads.
Full recovery and reuse of the Juno-5 was planned. The structural provisions were retained in the earliest Saturn I test vehicles, but never used.
Juno-5 Parallel Stag
A parallel staging scheme was considered for the Juno-5. This would have resulted in a vehicle similar to the Russian R-7 launcher.
Juno-5 on Test Stand
The very first Juno-5 test article firing on the stand at the Redstone Arsenal.
Alternate configurations studied for Juno 5.
The selected sequential staging method selected for the Juno-5.
American orbital launch vehicle. 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.
LEO Payload: 10,000 kg (22,000 lb) to a 185 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 57.500 million.
Status: Study 1958.
More... - Chronology...
Gross mass: 549,820 kg (1,212,140 lb).
Payload: 10,000 kg (22,000 lb).
Height: 60.00 m (196.00 ft).
Diameter: 6.52 m (21.39 ft).
Thrust: 6,690.00 kN (1,503,970 lbf).
Apogee: 185 km (114 mi).
H-1 Rocketdyne Lox/Kerosene rocket engine. 947.7 kN. Saturn l/lB. Designed for booster applications. Gas generator, pump-fed. Isp=289s. First flight 1961. 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...
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...
Saturn I Lox/Kerosene propellant rocket stage. Loaded/empty mass 432,681/45,267 kg. Thrust 7,582.10 kN. Vacuum specific impulse 289 seconds. Configuration as flown, Saturn I. 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...
Juno V-A Chronology
: Saturn I
. Launch Vehicle
: Juno V-A
- Juno V heavy space launch design - .
Nation: USA. Summary: 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..
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