RS-27A
 RS-27A Engine on Delta II | |
| Country of origin | United States |
|---|---|
| Date | 1989 |
| Designer | Rocketdyne |
| Manufacturer | Rocketdyne, Pratt & Whitney Rocketdyne |
| Application | Booster |
| Predecessor | RS-27 |
| Status | In use |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 1,054.2 kN |
| Thrust, sea-level | 890.1 kN (200,102 lbf) |
| Thrust-to-weight ratio | 102.47 |
| Chamber pressure | 4.8MPa (700 psia) |
| Specific impulse, vacuum | 302 seconds (2.96 km/s) |
| Specific impulse, sea-level | 255 seconds (2.50 km/s) |
| Burn time | 265 Sec |
| Dimensions | |
| Length | 3.78 m (12.40 ft) |
| Diameter | 1.70 m (5.58 ft) |
| Dry weight | 1,147 kg (2,528 lb) |
| Used in | |
| Delta 7000, first stage[1] | |
The RS-27A is a liquid-fuel rocket engine developed[when?] by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides 1.05 meganewtons (240,000 lbf) of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27;[2] its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude. The earlier RS-27 was derived from surplus Rocketdyne H-1 engines used in the Saturn 1B launcher.[3]
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.[citation needed] The RS-27A has a run duration of 265 seconds.[clarification needed]
References
External links
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