Our website is made possible by displaying online advertisements to our visitors.
Please consider supporting us by disabling your ad blocker.
AJ10
 AJ10-118K | |
| Country of origin |  United States |
|---|---|
| Date | 1957–present |
| Manufacturer | Aerojet, Aerojet Rocketdyne |
| Application | Upper stage |
| Status | In use |
| Liquid-fuel engine | |
| Propellant | N2O4 / Aerozine 50 |
| Cycle | Pressure-fed |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 43.7 kN (9,800 lbf) |
| Chamber pressure | 7–9 bars (700–900 kPa)[1] |
| Specific impulse, vacuum | 270–319 seconds (2.65–3.13 km/s) |
| Dimensions | |
| Diameter | 0.84 m (2 ft 9 in) |
| Dry mass | 90–100 kg (200–220 lb) |
| Used in | |
| |
The AJ10 is a hypergolic rocket engine manufactured by Aerojet Rocketdyne (previously Aerojet). It has been used to propel the upper stages of several launch vehicles, including the Delta II and Titan III. Variants were and are used as the service propulsion engine for the Apollo command and service module, in the Space Shuttle Orbital Maneuvering System, and on the European Service Module – part of NASA's Orion spacecraft.
- ^ "AJ10-118". Encyclopedia Astronautica. Archived from the original on 2008-07-06. Retrieved 2008-06-22.
Previous Page Next Page
