RS-27

First stage of a Delta II rocket, including an RS-27
Country of origin	United States
Date	1974
Designer	Rocketdyne
Manufacturer	Rocketdyne
Application	Booster
Predecessor	H-1
Successor	RS-56
Status	Retired
Liquid-fuel engine
Propellant	LOX /RP-1
Cycle	Gas-generator
Configuration
Chamber	1
Performance
Thrust, vacuum	RS-27: 1,023 kN (230,000 lbf) RS-27A: 1,054.2 kN (237,000 lbf)
Thrust, sea-level	RS-27: 971 kN (218,000 lbf) RS-27A: 890.1 kN (200,100 lbf)
Chamberpressure	RS-27: 4.9 MPa (49 bar; 710 psi) RS-27A: 4.8 MPa (48 bar; 700 psi)
Specific impulse, vacuum	RS-27: 295 s (2.89 km/s) RS-27A: 302 s (2.96 km/s)
Specific impulse, sea-level	RS-27: 264 s (2.59 km/s) RS-27A: 255 s (2.50 km/s)
Burn time	RS-27: 274 s RS-27A: 265 s
Dimensions
Length	RS-27: 3.63 m (11.9 ft) RS-27A: 3.78 m (12.4 ft)
Diameter	RS-27: 1.07 m (3 ft 6 in) RS-27A: 1.70 m (5 ft 7 in)
Dry mass	RS-27: 1,027 kg (2,264 lb) RS-27A: 1,147 kg (2,529 lb)
Used in
Delta 2000, 3000, 5000, 6000 first stage[1](RS-27) Delta 7000, 8000 first stage(RS-27A)

TheRS-27 (Rocket System-27) was aliquid-propellant rocket engine developed in 1974 byRocketdyne to replace the agingMB-3 in the Delta. Incorporating components of the venerable MB-3 and theH-1 designs, the RS-27 was a modernized version of the basic design used for two decades. It was used to power thefirst stage of theDelta 2000,3000,5000, and the first model of theDelta II, the Delta 6000.

The RS-27 was a modifiedRocketdyne H-1 built to power the first stage of theSaturn I andSaturn IB and replaced the MB-3 engine that had been used on previous versions of the Delta launcher. NASA had a large supply of surplus H-1 engines in the early 1970s, as the Apollo program was ending.^[2][3] In addition to its main engine, the RS-27 included twovernier engines to provide vehicle roll control during flight.^[4] RS-27 was later developed into theRS-27A andRS-56.^[5][6]

TheRS-27A is aliquid-fuel rocket engine developed in 1980s byRocketdyne for use on thefirst stage of theDelta II andDelta III launch vehicles. It provides 1.05 meganewtons (240,000 lbf) of thrust burningRP-1 andLOX in agas-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 northrottleable. In addition to its main engine, it includes twovernier engines to provide vehicle roll control during flight.^[7] 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 theICESat-2 launch on 15 September 2018.

• Aerojet Rocketdyne RS-27A Product PageArchived 2019-03-07 at theWayback Machine
• Pratt and Whitney RS-27A BrochureArchived 2022-05-31 at theWayback Machine

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