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 | |
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. It is used on the third stage of the Long March 4 family of launch vehicles.
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Wikipedia