A-7
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
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
Rocketdyne LOx/Hydyne rocket engine. 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.
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.
Related
- Country
- USA
- Launch Vehicles
- Jupiter C
- Propellants
- Lox/Hydyne
- Stages
- Jupiter C stage, Redstone Mercury
- Agency
- Rocketdyne
Photo Gallery
Redstone engine
Credit: NASA
