基于RVE模型的空间天线结构热稳定性优化设计与热变形分析

空间环境温度变化会使空间天线支撑结构产生热变形,影响其使用性能,因此进行天线热稳定性设计及热变形分析具有重要的意义.基于代表性体积单元(Representative Volume Element,RVE)方法对空间天线结构进行热稳定性设计与热变形分析.通过建立纤维随机分布并含有材料孔隙的RVE,得到纤维热膨胀系数.对M40/TDE85单向复合材料的热膨胀性能进行实验测试,计算结果与测试结果吻合良好,验证了RVE模型的正确性与准确性.建立了复合材料圆管参数化模型,根据计算得到的热膨胀系数及优化算法,对天线支撑结构进行热稳定性优化设计,并对优化后的天线结构进行热致变形分析,结果表明优化后的结构具有很高的热稳定性.

Thermal Stability Optimization Design and Thermal Deformation Analysis of Space Antenna Structure Based on Representative Volume Element Method

High temperature gradient and severe temperature variation in spacecraft will induce spacecraft thermal expansion and deformation.Thermally induced deflections of reflector have much effect on the electric performance of antenna on satellite that has a great limit in surface precision. Obviously,the research of in-orbit temperature and thermal distortion for antennas on satellites is very important.In this paper,the thermal stability of space antenna structure is designed and analyzed by RVE (Representative Volume Element) method.The Coefficient of Thermal Expansion (CTE) is predicted by RVE mode and experiment is also carried out.Comparison between the predicted results and experimental data verifies the rightness of this model.Optimization models for space antenna structure are created,and both the longitudinal and transverse CTE are considered. Analyzed results show that this optimized support structure and the whole antenna have an excellent thermal dimensional stability.