RS-27A

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 Retired
Liquid-fuel engine
Propellant LOX / RP-1
Cycle Gas Generator
Configuration
Chamber 1
Performance
Thrust (vac.) 1,054.2 kN
Thrust (SL) 890.1 kN (200,102 lbf)
Thrust-to-weight ratio 102.47
Chamber pressure 4.8MPa (700 psia)
Isp (vac.) 302 seconds (2.96 km/s)
Isp (SL) 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 in 1980s 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.[4]. The RS-27A, used as the main booster propulsion system for the Delta II family of launch vehicles, has an operational duration of 265 seconds. The RS-27A engine was retired at conclusion of the ICESat-2 launch on 15 September, 2018.

References

  1. ↑ Astronautix: RS-27A Engine
  2. ↑ Astronautix: RS-27 Engine
  3. ↑ Astronautix: RS-27 Derivation on Delta
  4. ↑ "RS-27A Engine". Aerojet Rocketdyne. Retrieved May 15, 2018.
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