 An H-1 engine at the Udvar-Hazy Center | |
| Country of origin | United States |
|---|---|
| First flight | 27 October 1961 |
| Last flight | 15 July 1975 |
| Designer | Rocketdyne |
| Manufacturer | Rocketdyne |
| Application | First stage |
| Successor | RS-27 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Gas-generator |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, sea-level | 900 kN (200,000 lbf) |
| Thrust-to-weight ratio | 102.47 |
| Chamber pressure | 700 psi (4,800 kPa) |
| Specific impulse, vacuum | 289 s (2.83 km/s) |
| Specific impulse, sea-level | 255 s (2.50 km/s) |
| Burn time | 155 seconds |
| Dimensions | |
| Length | 2.7 m (8.8 ft) |
| Diameter | 1.5 m (4.9 ft) |
| Dry mass | 1,000 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]
- ^ "Delta 2000 series". Encyclopedia Astronautica. Archived from the original on 18 June 2012. Retrieved 8 June 2012.
- ^ Kyle, Ed (9 April 2010). "Delta 2000 series – Extended Long Tank Delta". Space Launch Report. Retrieved 7 June 2012.