RS-27A
RS-27A Engine on Delta II
Country of originUnited States
Date1989
DesignerRocketdyne
ManufacturerRocketdyne, Pratt & Whitney Rocketdyne
ApplicationBooster
PredecessorRS-27
StatusRetired
Liquid-fuel engine
PropellantLOX / RP-1
CycleGas Generator
Configuration
Chamber1
Performance
Thrust, vacuum1,054.2 kN
Thrust, sea-level890.1 kN (200,102 lbf)
Thrust-to-weight ratio102.47
Chamber pressure4.8MPa (700 psia)
Specific impulse, vacuum302 seconds (2.96 km/s)
Specific impulse, sea-level255 seconds (2.50 km/s)
Burn time265 Sec
Dimensions
Length3.78 m (12.40 ft)
Diameter1.70 m (5.58 ft)
Dry weight1,147 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 RS-27A main engine is neither restartable nor throttleable. In addition to its main engine, it includes two vernier engines to provide vehicle roll control during flight.[3] When used as the main booster propulsion system for the Delta II family of launch vehicles, has an operational duration of 265 seconds. The last RS-27A engine was used for the ICESat-2 launch on 15 September, 2018.

References

  1. ↑ Astronautix: RS-27A Engine
  2. ↑ Astronautix: RS-27 Engine
  3. ↑ "RS-27A Engine". purdue.edu. Retrieved May 7, 2023.
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