| 飞船推进系统推力室工作过程数值仿真 |
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| 引用本文： | 陈新华,聂万胜,戴德海. 飞船推进系统推力室工作过程数值仿真[J]. 装备指挥技术学院学报, 2001, 12(5): 19-22 |
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| 作者姓名： | 陈新华 聂万胜 戴德海 |
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| 作者单位： | 1. 装备指挥技术学院试验工程系
2. 中国航天科技集团公司801研究所 |
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| 摘 要： | 研究了飞船推进系统推力室工作过程.用一甲基肼作燃料,四氧化二氮为氧化剂.数值仿真模型中考虑了自燃推进剂雾化机理、高压分解燃烧和预混反应流湍流燃烧等.利用压力隐式算子分裂(PISO)计算方法,在任意曲线坐标下采用非交错网格技术,成功地获得了3种推力室工作过程的流场参数,为飞船推进系统工作过程稳定性分析提供了理论依据.
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| 关 键 词： | 飞船 推进系统 推力室 工作过程 数值模拟 |
| 修稿时间： | 2001-07-04 |
Numerical Simulation of Operating Process of Thrust Chamber in Spacecraft Propulsion System |
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| CHEN Xin hua NIE Wan sheng. Numerical Simulation of Operating Process of Thrust Chamber in Spacecraft Propulsion System[J]. Journal of the Academy of Equipment Command & Technology, 2001, 12(5): 19-22 |
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| Authors: | CHEN Xin hua NIE Wan sheng |
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| Abstract: | Operating process of thrust chamber in spacecraft propulsion system is studied. Monemethyl hydrazine (MMH) is used as the fuel, and nitrogen tetroxide(N 2O 4) is used as the oxidizer. The atomization mechanism of hypergolic rocket propellant and decomposition combustion at high pressure and turbulence burning of premixed reactant flow field are considered .The PISO algorithm is introduced to the arbitrary curve line coordinator and non staggered grid is employed in the calculation. The flow field results of the operation process for three thrust chambers are numerically simulated successfully which may be used as one of the theoretical bases of stability analysis for spacecraft propulsion system. |
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| Keywords: | spacecraft propulsion system thrust chamber operating process numerical simulation |
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