为了明确由损耗导致航天器应用中的磁悬浮控制力矩陀螺温升问题，需要对损耗和温度分布进行分析计算。本文针对额定转速12 000 r/m，最大角动量200 N·m·s的单框架磁悬浮控制力矩陀螺，通过建立理论模型进行分析计算，得到了框架力矩电机、径向磁轴承、轴向磁轴承和转子高速电机的铁损以及铜损;对陀螺三维有限元模型进行了热场仿真分析，得到在各类损耗影响下的温度分布，并进行了热-结构耦合仿真分析。分析得到最大温度位于高速电机定子，最大温度是48.3 ℃;最后，进行了样机温升实验验证，检测温度最大值位于高速电机定子，最大值为51.8 ℃，与计算值误差为6.8%。通过温升检测实验验证了损耗计算和有限元热场分析。实验结论为整体结构优化提供了理论参考。

To investigate the temperature rise caused by loss of the magnetically suspended control moment gyroscope for the spacecraft application, it is necessary to analyze and calculate the loss and temperature distribution. In this paper, theoretical loss models that consider the iron and copper losses were established. The losses in a single gimbal magnetically suspended control moment gyroscope (SGMSCMG), which consists of a frame torque motor, radial magnetic bearing, axial magnetic bearing, high-speed motor of rotor system, with a rated speed of 12 000 r/m and maximum angular momentum of 200 N·m·s were calculated. These losses were then used to determine the temperature distribution, which was based on a three-dimensional finite-element model. A thermal-structure coupled simulation analysis was also performed. The results reveal that the maximum temperature occurs at the stator of the high-speed motor and has a value of 48.3 ℃. Finally, the temperature rise of the prototype is verified by experiment. According to the experiments, the maximum temperature occurs at the stator of the high-speed motor, and its maximum value is 51.8 ℃. The error is 6.8% when the experimental results are compared with predicted values. The loss calculation and finite element analysis of the thermal field are verified by the temperature rise experiment. The experimental results provide theoretical reference for overall structure optimization.