Rocketdyne H-1

H-1
An H-1 engine at the Udvar-Hazy Center
Country of originUnited States
First flight27 October 1961 (1961-10-27)
Last flight15 July 1975 (1975-07-15)
DesignerRocketdyne
ManufacturerRocketdyne
ApplicationFirst stage
SuccessorRS-27
StatusRetired
Liquid-fuel engine
PropellantLOX / RP-1
CycleGas-generator
Configuration
Chamber1
Performance
Thrust, sea-level900 kN (200,000 lbf)
Thrust-to-weight ratio102.47
Chamber pressure700 psi (4,800 kPa)
Specific impulse, vacuum289 s (2.83 km/s)
Specific impulse, sea-level255 s (2.50 km/s)
Burn time155 seconds
Dimensions
Length2.7 m (8.8 ft)
Diameter1.5 m (4.9 ft)
Dry mass1,000 kg (2,200 lb)
Used in
Saturn I, Saturn 1B

The Rocketdyne H-1 was a 205,000 lbf (910 kN) thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines. After the Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne RS-27 engine with first usage on the Delta 2000 series in 1974. RS-27 engines continued to be used up until 1992 when the first version of the Delta II, Delta 6000, was retired. The RS-27A variant, boasting slightly upgraded performance, was also used on the later Delta II and Delta III rockets, with the former flying until 2018.[1][2]

  1. ^ "Delta 2000 series". Encyclopedia Astronautica. Archived from the original on 18 June 2012. Retrieved 8 June 2012.
  2. ^ Kyle, Ed (9 April 2010). "Delta 2000 series – Extended Long Tank Delta". Space Launch Report. Retrieved 7 June 2012.