空间光学载荷在飞行任务期间受复杂热环境的影响,部分关键部件如光学镜体及其内部支撑结构由于温度变化带来的热变形会对载荷整体性能产生重要影响。精确模拟空间外热流作用下的载荷飞行和关键部件在给定温度场下的结构变形,可为其热设计、结构设计提供科学依据和有效支撑。以某空间光学载荷为例,基于Sinda/Fluint和Patran仿真分析软件,通过仿真流程开发,提出了基于同一有限元网格的机热联合仿真方法。经过与现有方法的比较,前者能够实现温度场参数在软件间的无误差传递,能较为准确地得出预示温度下全场热变形结果,保证了空间光学载荷的热变形仿真精度,提高了计算效率。

Space optical payload is affected by the complex environment during the flight. The thermal deformation caused by temperature variation for some critical components,such as optical frames and interior structural supports,will influence performance on payload obviously. Accurate simulation of payload’s temperature in space heat flux and structural deformation of key components is significant to thermal design and structural design. A space optical payload is used to propose the thermal-mechanical analysis based on Patran and Sinda/Fluint integrated simulation with the same finite element mesh information. The comparison of the proposed method and traditional method is described. Simulation results show that this method can transmit temperature field parameters between software without error,and evaluate the full space optical payload thermal deformation more accurately. The method can achieve more accurate simulation result of thermal deformation for space optical payloadandfaster calculation speed.