| Country of origin | China |
|---|---|
| First flight | 1994-02-08 |
| Designer | Beijing Aerospace Propulsion Institute |
| Manufacturer | China Academy of Launch Vehicle Technology (CALT) |
| Associated LV | Long March 3A, Long March 3B and Long March 3C |
| Predecessor | YF-73 |
| Successor | YF-75D |
| Status | In service |
| Liquid-fuel engine | |
| Propellant | Liquid oxygen / Liquid hydrogen |
| Mixture ratio | 5.1 (adjustable) |
| Cycle | Gas-generator |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 80 |
| Performance | |
| Thrust, vacuum | 78.45 kilonewtons (17,640 lbf) |
| Chamber pressure | 3.76 MPa (37.6 bar) |
| Specific impulse, vacuum | 438 seconds (4.30 km/s) |
| Burn time | 470 seconds (7.8 min) |
| Dimensions | |
| Length | 2.8 metres (9 ft 2 in) |
| Diameter | 1.5 metres (4 ft 11 in) |
| Dry mass | 550 kilograms (1,210 lb) |
| Used in | |
| Long March 3A, Long March 3B and Long March 3C H-18 third stage. | |
| References | |
| References | [1][2][3][4] |
The YF-75 is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in a gas generator cycle. It is China's second generation of cryogenic propellant engine, after the YF-73, which it replaced. It is used in a dual engine mount in the H-18 third stage of the Long March 3A, Long March 3B and Long March 3C launch vehicles. Within the mount, each engine can gimbal individually to enable thrust vectoring control. The engine also heats hydrogen and helium to pressurize the stage tanks and can control the mixture ratio to optimize propellant consumption.[4]
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