YF-209
Chinese liquid-fuel rocket engine
Country of origin | China |
---|---|
Designer | Academy of Aerospace Liquid Propulsion Technology |
Status | In development |
Liquid-fuel engine | |
Propellant | LOX / CH4 |
Cycle | Gas-generator cycle |
Configuration | |
Chamber | 1 |
Performance | |
Thrust, vacuum | 825.3 kilonewtons (185,500 lbf) |
Thrust, sea-level | 735 kilonewtons (165,000 lbf) |
Specific impulse, vacuum | 329s |
Specific impulse, sea-level | 293s |
References | |
References | [1] |
The YF-209 is a liquid cryogenic rocket engine burning liquid methane and liquid oxygen in a gas-generator cycle. The engine is designed for reusability and commercial use and is currently under development as of May 2024.
History
The YF-209 is designed for the commercial launch market in China with reusability in mind.[2] It can be reused at least 30 times and can be restarted at least 3 times during the mission with deep throttle capabilities.[3] The engine hot fire test was successfully completed in February 2023.[4] Development has been prioritised in 2024 to meet the growing needs of the commercial launch market.[5]
References
- ^ "China's new rocket engines". www.b14643.de. Retrieved 22 May 2024.
- ^ Curcio, Blaine (10 May 2023). "Commercial Launch at China Space Day: Rocketing Towards Launch Diversity". SpaceRef. Retrieved 22 May 2024.
- ^ "中国航天发布三款商业液体火箭发动机_央广网". news.cnr.cn. Retrieved 22 May 2024.
- ^ Jones, Andrew (27 April 2023). "Chinese state-owned academy makes rocket engines available to commercial space firms". SpaceNews. Retrieved 22 May 2024.
- ^ "China completes largest thrust liquid engine's ignition test". www.ecns.cn. Retrieved 22 May 2024.
- v
- t
- e
Rocket engines and solid motors for orbital launch vehicles
fuel
Cryogenic |
| ||||
---|---|---|---|---|---|
Semi- cryogenic |
| ||||
Storable |
| ||||
Other |
|
![](http://upload.wikimedia.org/wikipedia/commons/thumb/4/4d/RS-68_rocket_engine_test.jpg/120px-RS-68_rocket_engine_test.jpg)
fuel
- China
- Europe
- India
- Iran
- Salman
- Rafe
- Israel
- Japan
- USA
- * Different versions of the engine use different propellant combinations
- Engines in italics are under development