Encyclopedia Astronautica

A-6 differed from A-7 in having two fuel downcomers, one is hidden on the other side of the engine. The A-7 had one fuel downcomer to the aft manifold for engine cooling.
Credit: Boeing / Rocketdyne
Redstone engine
Credit: NASA
Rocketdyne Lox/Hydyne rocket engine. 416.2 kN. Out of Production. Version of Redstone engine for Jupiter-C test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 1956-1959. Gas generator, pump-fed. Thrust 370 kN at sea level. Isp=265s.

Thrust (sl): 369.100 kN (82,977 lbf). Thrust (sl): 37,635 kgf. Engine: 658 kg (1,450 lb). Propellant Formulation: Lox/Alcohol or Hydyne. Thrust to Weight Ratio: 64.2112462006079.

Status: Out of Production.
Unfuelled mass: 658 kg (1,450 lb).
Diameter: 1.77 m (5.80 ft).
Thrust: 416.20 kN (93,565 lbf).
Specific impulse: 265 s.
Specific impulse sea level: 235 s.
Burn time: 155 s.
First Launch: 1951.
Number: 9 .

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Associated Countries
See also
Associated Launch Vehicles
  • Jupiter C American orbital launch vehicle. Re-entry vehicle test booster and satellite launcher derived from Redstone missile. The Jupiter A version of the Redstone missile was modified with upper stages to test Jupiter re-entry vehicle configurations. Von Braun's team was ordered to ballast the upper stage with sand to prevent any 'inadvertent' artificial satellites from stealing thunder from the official Vanguard program. Korolev's R-7 orbited the first earth satellite instead. The Jupiter C was retroactively named the 'Juno I' by Von Braun's team. More...

Associated Manufacturers and Agencies
Associated Propellants
  • Lox/Hydyne Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Hydyne was a propellant blend pushed rather vigorously by the Redstone arsenal in the late 1950's, but it found little application. Hydyne, which is also known as MAF-4, is a 60 per cent, by weight, mixture of UDMH and 40 weight percent diethyltrianine (DETA). More...

Associated Stages
  • Jupiter C Lox/Hydyne propellant rocket stage. Loaded/empty mass 28,430/3,890 kg. Thrust 416.18 kN. Vacuum specific impulse 265 seconds. Redstone missile, stretched, modified with different propellants to serve as first stage of IRBM nose cone/orbital test vehicle. More...
  • Redstone Mercury Lox/Alcohol propellant rocket stage. Loaded/empty mass 28,440/3,125 kg. Thrust 414.34 kN. Vacuum specific impulse 265 seconds. Used for Jupiter-C satellite missions, and greatly modified, for Mercury manned positions. For Jupiter-C missions, used Hydyne fuel, which was toxic but increased specific impulse. More...

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