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This paper first derives the dynamic equation of a single gimbal control moment gyroscope (SGCMG), and provides the relationship between the gimbal angular velocity and the output moment of SGCMSs. Secondly, this article presents the control law used by SGCMSs, which allocates the required moment to the angular velocities of each gimbal. Finally, this article takes the pentagonal pyramid configuration as an example to simulate the attitude control of aircraft.

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Aircraft Attitude Control Based on Single Gimbal Control Moment Gyroscopes

  • 会议论文

  • 发表日期：

    2026年

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  • Wei Ze-yu,
  • Jiang Di-Kai,
  • Dong Peng-cheng,
  • Zheng Zai-ping,
  • Cui Pei-juan

摘要

This paper first derives the dynamic equation of a single gimbal control moment gyroscope (SGCMG), and provides the relationship between the gimbal angular velocity and the output moment of SGCMSs. Secondly, this article presents the control law used by SGCMSs, which allocates the required moment to the angular velocities of each gimbal. Finally, this article takes the pentagonal pyramid configuration as an example to simulate the attitude control of aircraft.