Analysis of Static Parameters for Heavy Lift Launch Vehicle Engine System

摘要：

The models for engine cycle power balance calculation, stage combustion cycles maximum chamber pressure calculation, and static characteristic analysis were established for heavy lift launch vehicle engine system, based on the object-oriented sequential analysis method. The balanced system parameters of gas generator cycle and stage combustion cycle, as well as the stage combustion cycles maximum chamber pressures, were delivered at 4000 kN with liquid oxygen and methane/propane/kerosene as propellant. The effects of propellant choice, chamber pressure, mixture ratio and nozzle expansion ratio on engine performance were well analyzed also. The results were helpful for the development of the new generation heavy lift launch vehicle engine.

关键词： Heavy lift Launch Vehicle Liquid Propellant Rocket Engine Static Characteristic Steady-state Parameter

作者: Li Xiangning Liu Yu

作者单位: School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100083,China

会议类型: 国际会议

会议名称: The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)

会议地点: 北京

会议语种:英文

页码: 554-562

在线出版日期: 2007-05-16（万方平台首次上网日期，不代表论文的发表时间）