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][failed verification]. 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.
^"RS-27A Engine". Aerojet Rocketdyne. Retrieved May 15, 2018.
External links
Aerojet Rocketdyne RS-27A Product Page
Pratt and Whitney RS-27A Brochure
January 27, 2023
liquid, fuel, rocket, engine, developed, 1980s, rocketdyne, first, stage, delta, delta, launch, vehicles, provides, meganewtons, thrust, burning, generator, cycle, engine, modified, version, predecessor, thrust, nozzle, been, extended, increase, area, ratio, f. 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 RS 27ARS 27A Engine on Delta IICountry of originUnited StatesDate1989DesignerRocketdyneManufacturerRocketdyne Pratt amp Whitney RocketdyneApplicationBoosterPredecessorRS 27StatusRetiredLiquid fuel enginePropellantLOX RP 1CycleGas GeneratorConfigurationChamber1PerformanceThrust vacuum1 054 2 kNThrust sea level890 1 kN 200 102 lbf Thrust to weight ratio102 47Chamber pressure4 8MPa 700 psia Specific impulse vacuum302 seconds 2 96 km s Specific impulse sea level255 seconds 2 50 km s Burn time265 SecDimensionsLength3 78 m 12 40 ft Diameter1 70 m 5 58 ft Dry weight1 147 kg 2 528 lb Used inDelta 7000 first stage 1 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 failed verification 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 Edit Astronautix RS 27A Engine Astronautix RS 27 Engine RS 27A Engine Aerojet Rocketdyne Retrieved May 15 2018 External links EditAerojet Rocketdyne RS 27A Product Page Pratt and Whitney RS 27A Brochure Retrieved from https en wikipedia org w index php title RS 27A amp oldid 1084022713, wikipedia, wiki, book, books, library,
