重庆大学学报2025，Vol.48Issue(5)：41-50,10.DOI:10.11835/j.issn.1000-582X.2025.05.004
航天器控制力矩陀螺温度场计算与分析
Calculation and analysis of temperature field in a control moment gyroscope for spacecraft
摘要
Abstract
The control moment gyroscope(CMG)is a critical actuator in spacecraft attitude control systems.In the vacuum of space,heat generated by the CMG is primarily dissipated through thermal conduction and radiation,resulting in substantial temperature rises that may compromise system stability and reliability.Consequently,analyzing the CMG's temperature field and maintaining its operating temperature within acceptable limits is essential.This study focuses on a 70 Nms single-frame CMG,for which a thermal simulation model is developed to investigate temperature distribution and assess the effects of rotational speed,applied torque,and bearing preload on thermal behavior.The model,validated against experimental data,achieves an average temperature prediction accuracy of 93.87%.Results reveal that temperature at various measurement points is highly sensitive to changes in rotational speed.The lower end of the rotor shaft exhibits a pronounced responsiveness to torque,while both ends of the rotor shaft are significantly influenced by bearing preload.The maximum observed temperature increase is 5.2℃at the lower end of the rotor shaft,whereas the frame experiences the smallest increase at 1.72℃.The presented temperature field modeling approach offers valuable insights for optimizing the design of control moment gyroscopes and facilitating operational diagnostics of spacecraft systems.关键词
控制力矩陀螺/热分析/温度场/预紧力/温度预测Key words
control moment gyroscope/thermal analysis/temperature field/preload force/temperature prediction分类
机械工程引用本文复制引用
梅澳,周广武..航天器控制力矩陀螺温度场计算与分析[J].重庆大学学报,2025,48(5):41-50,10.基金项目
装备预研教育部联合基金项目(8091B032209) （8091B032209）
四川省重点研发项目(2023YFG0258).Supported by Joint Fund of Equipment Pre-research and Ministry of Education(8091B032209),Sichuan Science and Technology Program(2023YFG0258). （2023YFG0258）
