CAJ | 학술논문

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。
위해결유항천기자공발동궤등대래적우류열효응문제，문장통과방진득도료재불동적발동궤포국하항천기표면적우류열류밀도분포정황，통과증대발동궤적추력선각도화안장점고도，가이사득발동궤우류핵심구원리항천기표면，종이강저분류대항천기표면적가열효응。종합고필공제력구급추력손실、포국포락화발동궤지가설계등인소，대모항천기발동궤포국진행료우화설계급우류열방호설계。
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.