RS-27A
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(Redirected from RS-27A (rocket engine))
The RS-27A is a liquid-fuel rocket engine developed by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides 1.05 meganewtons of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27;[1] its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude.
The RS-27A main engine is neither restartable nor throttleable. In addition to its main engine, the RS-27A includes two vernier engines to provide vehicle roll control during flight. The RS-27A has a run duration of 265 seconds.
[edit] Specifications
- Source: Astronautix[2]
- Thrust (vac): 237,000 lbf (1.05 MN)
- Specific impulse, Isp (vac): 302 s
- Isp (sea level): 255 s
- Mass: 2,528 lb (1,147 kg)
- Diameter: 67 in (1.70 m)
- Length: 12 ft 5 in (3.78 m)
- Chambers: 1
- Chamber pressure: 700 psia (4.8 MPa)
- Area ratio: 12:1
- Oxidizer to fuel ratio: 2.245:1
- Thrust to Weight ratio: 102
[edit] References
[edit] External links
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