Scholarlink

This work presents an attitude control strategy for a small satellite in a low Earth orbit (LEO) equipped with solar panels on all sides except the underside, where the payload is located. The proposed approach employs reaction wheels as actuators to produce torque along the three axes of the satellite, configured in a typical way to ensure three-axis attitude control in a low earth orbit. A controller PD is employed to distribute three-dimensional torque and commands optimally. The simulated attitude control system was subjected to external disturbances caused by gravity gradient and magnetic torques affecting its performance in open-loop control. This controller uses unit quaternions to achieve accurate stabilization of the three-axis attitude. Numerical simulations are performed to assess the effectiveness of the closed-loop system, taking advantage of the proposed attitude control strategy.

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PD Controller Design for Three-Axis Attitude Stabilization of a Microsatellite Using Reaction Wheels

  • 会议论文

  • 发表日期：

    2025年

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  • B. Khouane,
  • J. E. Benmansour,
  • I. Rached,
  • A. S. Zemouli

摘要

This work presents an attitude control strategy for a small satellite in a low Earth orbit (LEO) equipped with solar panels on all sides except the underside, where the payload is located. The proposed approach employs reaction wheels as actuators to produce torque along the three axes of the satellite, configured in a typical way to ensure three-axis attitude control in a low earth orbit. A controller PD is employed to distribute three-dimensional torque and commands optimally. The simulated attitude control system was subjected to external disturbances caused by gravity gradient and magnetic torques affecting its performance in open-loop control. This controller uses unit quaternions to achieve accurate stabilization of the three-axis attitude. Numerical simulations are performed to assess the effectiveness of the closed-loop system, taking advantage of the proposed attitude control strategy.