基于羽流效应分析的航天器发动机布局设计研究

The layout design of spacecraft thrusters based on the vacuum plume effect analysis

为解决由航天器姿控发动机等带来的羽流热效应问题,文章通过仿真得到了在不同的发动机布局下航天器表面的羽流热流密度分布情况,通过增大发动机的推力线角度和安装点高度,可以使得发动机羽流核心区远离航天器表面,从而降低喷流对航天器表面的加热效应。综合考虑控制力矩及推力损失、布局包络和发动机支架设计等因素,对某航天器发动机布局进行了优化设计及羽流热防护设计。

To solve the problem of the vacuum plume effect caused by the spacecraft thrusters, the optimal layout design of the thrusters is made based on the vacuum plume effect analysis. The heat fluxes on the surfaces of the spacecraft are obtained for different layouts of the thrusters. By increasing the thrust line angle and the altitude of the fix point of the thruster, the core region of the plume will disappear from the surface of the spacecraft, and the heat flux on the surface of the spacecraft will be decreased. This method could help the layout design of the thrusters, with consideration of the thrust loss, the layout envelope and the bracket design of the thrusters, and two schemes of thermal protection of plume are put forward, for the layout design of spacecraft thrusters.