Rocketdyne H-1
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.
An H-1 engine at the Udvar-Hazy Center | |
| Country of origin | United States |
|---|---|
| Date | 1963-1975 |
| Manufacturer | Rocketdyne |
| Application | Booster |
| Successor | RS-27 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Gas generator |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, sea-level | 205,000 lbf (900 kN) |
| Thrust-to-weight ratio | 102.47 |
| Chamber pressure | 700 psia (4.8 MPa) |
| Specific impulse, vacuum | 289 seconds (2.83 km/s) |
| Specific impulse, sea-level | 255 seconds (2.50 km/s) |
| Burn time | 155 s |
| Dimensions | |
| Length | 8.8 feet |
| Diameter | 4.9 feet |
| Dry weight | 2,200 lb (1,000 kg) |
| Used in | |
| Saturn I, Saturn 1B | |
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.