低压工况下10N姿控推力器燃烧室工作过程仿真

毛晓芳; 唐振宇; 蔡国飙

低压工况下10N姿控推力器燃烧室工作过程仿真

北京航空航天大学宇航学院,北京 100191

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出版历程
- 收稿日期: 2011-11-28
- 刊出日期: 2013-03-28

Simulation on working process of 10N attitude-control thruster combustion chamber at lower-pressure condition

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 描述了发动机燃烧室工作过程仿真模型的主要参数,应用此模型对10N推力器在不同供应管路压强条件下燃烧室的脉冲工作过程进行了仿真.对比分析了长脉冲和短脉冲两种工作模式下管路压强逐渐降低时燃烧室压强、推力等参数的变化规律.通过长脉冲工况的仿真理论推力与实验测量推力反推出管路压强为1.48,1.0,0.6MPa时推力效率分别为94%,91%和90%.短脉冲工况仿真结果表明:管路压强为0.4MPa时推力器已经无法正常点火,应避免推力器工作于此工况.d:\PDF\.pdf
- 低供应管路压强 /
- 推力器 /
- 燃烧室 /
- 工作过程 /
- 数值仿真模型
Abstract: A simulation model for the working process of rocket engine combustion chamber was described. Simulation was implemented by using this model for a 10N thruster working at different lower supply pressures. Comparisons were made to find some characteristics of chamber pressure and thrust of the thruster when it worked in long-pulse and short-pulse modes at regular and lower supply pressures. According to the theoretical thrust obtained by simulation and the experimental thrust in long-pulse mode, it can be concluded that the thrust efficiencies are 94%, 91% and 90%, respectively, while supply pressures equal to 1.48, 1.0, 0.6MPa, separately. Meanwhile, simulation results of short-pulse mode cases show that, when the supply pressure decreases to 0.4MPa, the thruster cannot be ignited in short-pulse mode.
- lower pressure in supply pipe /
- thruster /
- combustion chamber /
- working process /
- numerical simulation model

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参考文献(15)

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