摘要
针对“嫦娥”月球探测器着陆器太阳电池阵转动轴组件在轨热–力多物理场复合环境载荷模拟,文章提出一种适用于热真空环境,可同步叠加恒定扭矩、正弦交变扭矩与静态弯矩的扭转–弯曲复合力矩加载方法,并设计了相应的加载装置与摩擦降阻装置。为验证该方法的可行性,在高低温交变热真空条件下开展了地面模拟试验。结果表明,扭矩加载误差最大仅为1.8%,弯矩加载误差约为0.3%,均满足优于2%的设计指标。该方法能有效模拟空间转动机构在轨受力工况,具备较高的工程适用性,可为空间转动部件的寿命预测、容差设计与失效机制研究提供技术支撑。
A torsion-bending composite moment loading method was developed for use in a thermal vacuum environment to simulate the thermo-mechanical and multiphysics-coupled environmental loads experienced by the rotary shaft assembly of the Chang’e lunar lander’s solar panel during in-orbit operations.The method enables the synchronous superposition of constant torque,sinusoidal alternating torque,and static bending moments.A dedicated loading device and a friction-reduction mechanism were designed to ensure loading accuracy and environmental compatibility.Ground-based thermal-vacuum tests under high/low-temperature cycling conditions demonstrated the feasibility and repeatability of the method,with the maximum torque loading error only 1.8%,and the bending moment loading error approximately 0.3%,both meeting the design criteria of less than 2%error.The results indicate that the proposed approach effectively simulates in-orbit mechanical conditions and provides a method with high engineering applicability,offering technical support for lifetime prediction,tolerance design,and failure-mechanism analysis of space rotary components.
作者
周原
马晓荔
马龙
董上
闫琦
居楠
徐宏贵
丁磊
ZHOU Yuan;MA Xiaoli;MA Long;DONG Shang;YAN Qi;JU Nan;XU Honggui;DING Lei(Science and Technology on Realiability and Environmental Engineering Laboratory;Beijing Institute of Spacecraft Environment Engineering;Beijing Spacecraft Manufacturing Co.,Ltd.,Beijing 100094,China)
出处
《航天器环境工程》
2025年第6期644-649,共6页
Spacecraft Environment Engineering
基金
重点实验室稳定支持科研项目(编号:WDZC614200420230401)。
关键词
空间转动机构
扭转–弯曲复合力矩
热真空环境
地面模拟试验
space rotary mechanisms
torsion-bending composite moment
thermal vacuum environment
ground-based simulation testing
