超低轨卫星气动舵机辅助姿态控制方法设计

Design of attitude control method for ultra-low-orbit satellite with pneumatic steering gear

针对超低轨卫星姿态控制差异化需求,开展了基于气动舵机辅助的姿态控制策略研究。完成了超低轨道稀薄大气下卫星气动舵机布局设计与气动特性研究,理论气动力可达10^(-1) N量级,气动力矩可达10^(-1) N·m量级。在此基础上,完成了基于气动舵机辅助的姿态控制策略研究。通过仿真验证,在x轴采用动量轮控制、y轴和z轴采用气动舵机辅助控制情况下,可实现优于0.004°的三轴指向精度和优于0.0007(°)/s的三轴姿态稳定度。所设计气动舵机辅助姿态控制策略对超低轨卫星技术应用与发展具有重要技术价值和工程意义。

To meet the differentiated needs of the attitude control of ultra-low orbit satellites,this study investigates the attitude control strategy with the assistance of pneumatic steering gears.The layout of the gear is designed and its aerodynamic characteristics are analyzed under the thin atmosphere of the ultra-low orbit,with the theoretical aerodynamic force up to the order of 10^(−1) N,and the aerodynamic torque the order of 10^(−1) N·m.On this basis,an attitude control strategy assisted by pneumatic steering gears is designed.Simulation results show that when the x-axis is controlled by the momentum wheel and the y-axis and z-axis are controlled by pneumatic steering gears,the three-axis pointing accuracy larger than 0.004°and the three-axis attitude stability larger than 0.0007(°)/s can be achieved.The attitude control strategy designed in this paper has important technical and engineering value for the application and development of ultra-low orbit satellites.