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RS-27

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RS-27
Country of originUnited States
Date1974
DesignerRocketdyne
ManufacturerRocketdyne
ApplicationBooster
PredecessorH-1
SuccessorRS-27A, RS-56
StatusRetired
Liquid-fuel engine
PropellantLOX / RP-1
CycleGas Generator
Configuration
Chamber1
Performance
Thrust, vacuum1,023 kN (230,000 lbf)
Thrust, sea-level971 kN (218,000 lbf)
Chamber pressure4.9 MPa (49 bar)
Specific impulse, vacuum295 seconds (2.89 km/s)
Specific impulse, sea-level264 seconds (2.59 km/s)
Burn time274 Sec
Dimensions
Length3.63 m (11.9 ft)
Diameter1.07 m (3.51 ft)
Dry mass1,027 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. Archived from the original on May 22, 2013. Retrieved March 5, 2015. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)
  2. ^ "RS-27". Astronautix. Archived from the original on August 13, 2011. Retrieved March 5, 2015. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)
  3. ^ "Extended Long Tank Delta". SpaceLaunchReport.com. Retrieved March 5, 2015.
  4. ^ "Atlas IIA(S) Data Sheet". Space Launch Report. Retrieved 9 January 2016.
  5. ^ "RS-27A". Astronautix. Archived from the original on 5 August 2014. Retrieved 10 January 2016. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)