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YF-120t
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Designer: China Academy of Aerospace Liquid Propulsion Technology. Developed in: 1999-2006. Propellants: Lox/Kerosene. Thrust(vac): 1,340.200 kN (301,289 lbf). Thrust(sl): 1,200.000 kN (269,700 lbf). Throttled thrust(vac): 871.000 kN (195,808 lbf). Isp: 336 sec. Isp (sea level): 301 sec. Chambers: 1. Oxidizer to Fuel Ratio: 2.70. Country: China. Status: In development. New Lox/Kerosene engine for the next generation Chinese launch vehicles. Said to have been developed with Russian assistance and has turbomachinery design features in common with the Glushko RD-170/-180/-190 series. However the Russians have no thrust chamber in this thrust category and therefore the engine represents an entirely new design using all-indigenous components. Turbopump-fed, built in one- and two-axis gimballed versions. Oxygen bled from engine is used to pressurize oxygen tank; helium to pressurize kerosene tank. The engine can be throttled to 65% of rated thrust. Firing tests began in 2003 and were to be completed by early 2006. Instead there were delays and the first 300-second full-duration firing test did not occur until 8 November 2005. First launch, originally expected in 2008, was delayed to 2010 or later.
YF-120t used on Rocket Stages
Bibliography and Further Reading - Video presentation, IAF Bremen, September 2003.
- Tangming Cheng, Xiaojun Wang, Dong Li, "The New Generation Launch Vehicles of Long March Family", IAF 2003.
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