YF-40
Chinese liquid rocket engine
From Wikipedia, the free encyclopedia
The YF-40 is a Chinese liquid rocket engine burning N2O4 and UDMH in a gas generator cycle. It has dual gimbaling combustion chambers.
| Country of origin | China |
|---|---|
| First flight | 1995-06-01 |
| Designer | Academy of Aerospace Liquid Propulsion Technology |
| Associated LV | 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, vacuum | 103 kN (23,000 lbf) |
| Chamber pressure | 4.6 MPa (670 psi) |
| Specific impulse, vacuum | 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 mass | 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] |
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]
