控制力矩陀螺是航天器在太空调整姿态的执行部件,其仅依靠热传导和热辐射向真空中传递热量,易出现高温升,影响其稳定性和可靠性。因此研究控制力矩陀螺的温度场,判断其运行温度是否满足要求至关重要。本文以70Nms单框架控制力矩陀螺为对象,建立控制力矩陀螺温度场仿真模型并研究转速、转矩、轴承预紧力对温度场的影响。与实验结果对比,本文仿真模型测点温度平均准确度达93.87%。研究发现,各测点温度变化均对转速比较敏感,转子轴下端测点对转矩最为敏感,上下端两测点对预紧力最为敏感,转子轴下端测点温升最大且为5.2℃,框架测点温升最小且为1.72℃。本文提出的控制力矩陀螺温度场计算方法,可为航天器控制力矩陀螺优化设计和运行诊断提供技术指导。

The control moment gyroscope constitutes a pivotal actuator in spacecraft attitude control systems. It dissipates heat primarily through thermal conduction and radiation into the vacuum of space, which causes substantial temperature increases that potentially compromise its stability and reliability. Consequently, analyzing the temperature field of the control moment gyroscope and ensuring its operating temperature remains within permissible limits are imperative. This research focuses on a 70 Nms single-frame control moment gyroscope. A simulation model is developed to investigate its temperature distribution and explore the influence of rotational speed, torque, and bearing preload on thermal characteristics. Upon validation against experimental data, the simulation model demonstrates an average temperature prediction accuracy of 93.87%. The outcomes reveal that temperature variations across various measurement points are sensitive to rotational speed. Notably, the lower extremity of the rotor shaft exhibits a pronounced responsiveness to torque inputs. Furthermore, both the upper and lower ends of the rotor shaft are significantly influenced by bearing preload. In particular, the maximum temperature increase of 5.2°C is observed at the lower end of the rotor shaft, while the frame experiences the least elevation of 1.72°C. The temperature field modeling approach presented herein offers valuable insights for optimizing the design of control moment gyroscopes and facilitating operational diagnostics of spacecraft systems.

TH133.7

装备预研教育部联合(8091B032209)、四川省重点研发项目(2023YFG0258)、机器人卫星实验室开放基金