YF-40
| Country of origin | China |
|---|---|
| First flight | 1995-06-01 |
| Designer | Academy of Aerospace Liquid Propulsion Technology |
| Associated L/V | Long March 1D, Long March 4 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 2.14 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 2 |
| Nozzle ratio | 55 |
| Performance | |
| Thrust (vac.) | 103 kN (23,000 lbf) |
| Chamber pressure | 4.6 MPa (670 psi) |
| Isp (vac.) | 303 seconds (2.97 km/s) |
| Burn time | 412s |
| Gimbal range | ±4.5° |
| Dimensions | |
| Length | 120 centimetres (47 in) |
| Diameter | 63 centimetres (25 in) |
| Dry weight | 83 kg (183 lb) |
| Used in | |
| Long March 1D second stage and Long March 4 third stage. | |
| References | |
| References | [1][2][3][4][5][6] |
The YF-40 is a Chinese liquid rocket engine burning N2O4 and UDMH in an gas generator cycle. It has dual gimbaling combustion chambers.
Originally it was developed for the Long March 1D second stage.[6] It is used on the third stage of the Long March 4 family of launch vehicles.[1][3][7]
References
- 1 2 "Long March". Rocket and Space Technology. Retrieved 2015-07-08.
- ↑ "YF-40". Encyclopedia Astronautica. Retrieved 2015-07-15.
- 1 2 Gunter Dirk Krebs. "CZ-4 (Chang Zheng-4)". Gunter's Space Page. Retrieved 2015-07-15.
- ↑ Sutton, George Paul (November 2005). "Liquid Rocket Propellant Engines in the People's Republic of China". History of Liquid Propellant Rocket Engines. AIAA. p. 873. ISBN 978-1563476495. Retrieved 2015-07-15.
- ↑ Mowthorpe, Matthew (2004). "Chinas Military Space Program". The Militarization and Weaponization of Space. Lexington Books. p. 90. ISBN 978-0739107133. Retrieved 2015-07-15.
- 1 2 "Chang Zheng-1 (Long March-1)". SinoDefence. Retrieved 2015-07-15.
- ↑ Harvey, Brian (2004). "Launch Centers Rockets and Engines". China's Space Program — From Conception to Manned Spaceflight. Springer Science & Business Media. p. 231. ISBN 978-1852335663. Retrieved 2015-07-15.
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