RS-27
From Infogalactic: the planetary knowledge core
Country of origin | USA |
---|---|
Date | 1974 |
Designer | Rocketdyne |
Manufacturer | Rocketdyne |
Application | Booster |
Predecessor | H-1 |
Successor | RS-27A, RS-56 |
Status | Retired |
Liquid-fuel engine | |
Propellant | LOX / RP-1 |
Cycle | Gas Generator |
Configuration | |
Chamber | 1 |
Performance | |
Thrust (vac.) | 1,023 kN (230,000 lbf) |
Thrust (SL) | 971 kN (218,000 lbf) |
Chamber pressure | 4.9 MPa (49 bar) |
Isp (vac.) | 295 seconds (2.89 km/s) |
Isp (SL) | 264 seconds (2.59 km/s) |
Burn time | 274 Sec |
Dimensions | |
Length | 3.63 m (11.9 ft) |
Diameter | 1.07 m (3.51 ft) |
Dry weight | 1,027 kg (2,264 lb) |
Used in | |
Delta 2000, 3000, 5000, 6000, first stage[1] |
The RS-27 is a liquid-propellant rocket engine developed[when?] by Rocketdyne. 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 from surplus engines 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.[2][3] In addition to its main engine, the RS-27 included two vernier engines to provide vehicle roll control during flight.[citation needed]. RS-27 was later developed into the RS-27A, and RS-56.[4][5]
References
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