某航天器发动机机组热分析及在轨应用研究

Thermal Simulation and On-orbit Thermal Study of One Thruster Unit in a Spacecraft

为给某航天器机组热控设计、飞行任务中各种新工况下机组的温度适应性分析和飞控判据提供有效数据支撑,以该航天器某发动机B机组模块作为研究对象,采用IDEAS软件建立了有限元模型,在航天器三轴对地姿态下对该发动机机组温度进行了计算并对热模型进行修正,对飞行数据和热分析结果进行了比对。之后应用该热模型,完成了高温工况1下热控适应性设计工作,开展了组件温度与在轨数据比对工作;并进行了高温工况2中不同太阳入射角下B机组氧阀温度研究。结果表明:B机组热分析得到了在轨飞行的验证,有限元模型有效并且合理;该热模型应用于不同热控状态、位置以及工况下来解决实际热控难题,并可预示不同太阳入射角下的氧阀温度;航天器的运行轨道、飞行姿态以及机组安装位置都是影响机组温度的重要因素,在热控设计中应引起足够重视。

To support the thermal design,the temperature prediction,and the on-orbit judgment of the thruster unit in one spacecraft,thruster unit B of the spacecraft was taken as the research object and the IDEAS software was used to build the finite element model.The temperatures of the thruster unit were calculated under earth-oriented three-axis stabilized attitude and the thermal model was modified.The differences between the thermal analysis and the on-orbit temperature data were compared.Thermal adaptive design was implemented with the thermal model in high temperature case 1 and unit temperatures were compared with the on-orbit data.The temperatures of oxidant valves in thruster unit B were studied under different solar incident angleβin high temperature case 2.The results showed that the thermal analysis of thruster unit B was verified by the on-orbit temperature data and the finite element model was effective and feasible;The thermal model can be applied to solve thermal control problems under various thermal control status,positions,and cases,as well as to predict the temperatures of oxidant valves under different solar incident angleβ;Some temperature influential factors such as the flight orbit,the attitude,and the mounted position of the thruster unit in spacecraft are crucial and should be focused on in the thermal design.