This page no longer updated from 31 October 2001. Latest version can be found at A-7

A-6 - 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. 6,451 bytes. 128 x 235 pixels.

Manufacturer Name: A-7. Designer: Rocketdyne. Developed in: 1951. Application: . Used on stages: Jupiter C. Used on launch vehicles: Jupiter C. Propellants: Lox/Hydyne Thrust(vac): 42,439 kgf. Thrust(vac): 416.20 kN. Isp: 265 sec. Isp (sea level): 235 sec. Burn time: 155 sec. Mass Engine: 658 kg. Diameter: 1.8 m. Chambers: 1. Thrust to Weight Ratio: 64.21. Country: USA. Status: Out of Production. First Flight: 1956. Last Flight: 1958. Flown: 9. Comments: Redstone Booster. Gas generator, pump-fed. Thrust 83,000 sl with Hydyne.

Redstone engineRedstone engine

Credit: NASA. 33,508 bytes. 386 x 305 pixels.

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Last update 12 March 2001.
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