RS-27

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RS-27
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

  1. "Delta". Astronautix. Retrieved March 2015. Check date values in: |accessdate= (help)<templatestyles src="Module:Citation/CS1/styles.css"></templatestyles>
  2. "RS-27". Astronautix. Retrieved March 2015. Check date values in: |accessdate= (help)<templatestyles src="Module:Citation/CS1/styles.css"></templatestyles>
  3. "Extended Long Tank Delta". SpaceLaunchReport.com. Retrieved March 2015. Check date values in: |accessdate= (help)<templatestyles src="Module:Citation/CS1/styles.css"></templatestyles>
  4. "Atlas IIA(S) Data Sheet". Space Launch Report. Retrieved 9 January 2016.<templatestyles src="Module:Citation/CS1/styles.css"></templatestyles>
  5. "RS-27A". Astronautix. Retrieved 10 January 2016.<templatestyles src="Module:Citation/CS1/styles.css"></templatestyles>