RS-27

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)
Chamber pressure	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)

The RS-27 (Rocket System-27) was a liquid-propellant rocket engine developed in 1974 by Rocketdyne to replace the aging MB-3 in the Delta. Incorporating components of the venerable MB-3 and the H-1 designs, the RS-27 was a modernized version of the basic design used for two decades. It was used to power the first stage of the Delta 2000, 3000, 5000, and the first model of the Delta II, the Delta 6000.

The RS-27 was a modified Rocketdyne H-1 built to power the first stage of the Saturn I and Saturn 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 two vernier engines to provide vehicle roll control during flight.^[4] RS-27 was later developed into the RS-27A and RS-56.^[5][6]