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 A computer rendering of a J-2X. | |
| Country of origin | United States |
|---|---|
| Manufacturer | Aerojet Rocketdyne |
| Application | Upper stage engine |
| Associated LV | Block II Space Launch System (EDS) |
| Predecessor | J-2 |
| Status | Unknown |
| Liquid-fuel engine | |
| Propellant | Liquid oxygen / liquid hydrogen |
| Mixture ratio | 5.5–4.5 |
| Cycle | Gas generator |
| Configuration | |
| Nozzle ratio | 92:1 |
| Performance | |
| Thrust, vacuum | 1,307 kN (294,000 lbf) |
| Thrust-to-weight ratio | 55.04 |
| Specific impulse, vacuum | 448 seconds (4.39 km/s) |
| Dimensions | |
| Length | 4.7 metres (15 ft) |
| Diameter | 3 metres (9.8 ft) |
| Dry weight | 5,450 pounds (2,470 kg) |
| References | |
| References | [1][2] |
The J-2X is a liquid-fueled cryogenic rocket engine that was planned for use on the Ares rockets of NASA's Constellation program, and later the Space Launch System. Built in the United States by Aerojet Rocketdyne (formerly, Pratt & Whitney Rocketdyne), the J-2X burns cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing 1,307 kN (294,000 lbf) of thrust in vacuum at a specific impulse (Isp) of 448 seconds (4.39 km/s).[2] The engine's mass is approximately 2,470 kg (5,450 Lb), significantly heavier than its predecessors.[2]
The J-2X was intended to be based on the J-2 used on the S-II and S-IVB stages of the Saturn rockets used during the Apollo program, but as required thrust for the Ares I increased due to weight problems it became a clean-sheet design. It entered development in 2007 as part of the now-cancelled Constellation program.[2] Originally planned for use on the upper stages of the Ares I and Ares V rockets, the J-2X was later intended for use in the Earth Departure Stage of the Block 2 Space Launch System, the successor to the Constellation program. The engine is intended to be more efficient and simpler to build than its J-2 ancestor, and cost less than the RS-25 engine.[1] Differences in the new engine include the removal of beryllium, a centrifugal turbo pump versus the axial turbo pump of the J-2, different chamber and nozzle expansion ratios, a channel-walled combustion chamber versus the tube-welded chamber of the J-2, a redesign of all the electronics, a gas generator and supersonic main injector based on the RS-68,[3] and the use of 21st-century joining techniques.[2][4]
- ^ a b "J-2X Engine". Aerojet Rocketdyne. Archived from the original on 12 January 2014. Retrieved 9 January 2014.
- ^ a b c d e Mark Wade (17 November 2011). "J-2X". Encyclopedia Astronautica. Archived from the original on 12 December 2011.
- ^ "The J-2X Upper Stage Engine: From Design to Hardware. Thomas Byrd, Deputy Manager, J-2X Upper Stage Engine Element Ares Projects Office Marshall Space Flight Center Huntsville, AL 35812" (PDF).
- ^ William D Greene (4 June 2012). "J-2X Extra: What's in a Name?". NASA. Archived from the original on 9 November 2010. Retrieved 11 June 2012.