低轨质量矩航天器姿态动力学与气动补偿控制

doi:10.12305/j.issn.1001-506X.2025.06.25

Abstract

Abstract:

Aiming at the serious interference of aerodynamic eccentric moment on the attitude control performance of ultra-low Earth orbit satellites, an adaptive dynamic compensation control method for micro-nano satellites based on mass moment technology is proposed. For the mass moment drive method based on ball screw pairs, considering the mechanism transmission friction, a complete dynamic model of mass moment satellite rotation, translation, and actuator translation is established to clarify the influence of various parameters on disturbance moment. To address the uncertainties in the aerodynamic environment and the unknown center of mass of the satellite, an adaptive dynamic compensation scheme is designed, which includes a radial basis function (RBF)-based disturbance observer, a sliding mode controller, and an integral separated proportional-integral-derivation (PID) controller. Simulation results show that the proposed compensation control method can accurately estimate and compensate for aerodynamic moment disturbances and effectively eliminate the influence of friction in the mass moment mechanism, and validate the effectiveness of the proposed aerodynamic compensation control method.

Key words: ultra-low Earth orbit satellite, attitude control, aerodynamic moment, friction characteristics, sliding mode control

CLC Number:

TN974

Zhengliang LU, Jiatong LI, Yuandong HU, Wenhe LIAO. Attitude dynamics and aerodynamic compensation control of low-orbit mass moment spacecraft[J]. Systems Engineering and Electronics, 2025, 47(6): 1975-1984.

Figures/Tables 13

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Table 1

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参数名称	参数值
质量	卫星壳体质量: 80 kg
质量	质量矩滑块质量: 20 kg
卫星参数	初始质心位置: [0.012 －0.003 0.009]mm
	转动惯量:
	壳体: $\left[\begin{array}{ccc}1664 & -8.1 & 16.63 \\-8.1 & 1329 & -26 \\16.63 & -26 & 600\end{array}\right] \times 10^{-2} \mathrm{~kg} / \mathrm{m}^2$
	滑块: $\left[\begin{array}{ccc}13 & 0 & 0 \\0 & 13 & 0 \\0 & 0 & 13\end{array}\right] \times 10^{-2} \mathrm{~kg} / \mathrm{m}^2$
初始姿态	初始姿态欧拉角: [20, －20, 0]^T/(°)
初始姿态	初始角速度: [0.5 0.5 0.5]^T/(°/s)
控制参数	姿态控制环参数: k=0.7, c=2
	干扰观测器参数: K=0.1
	积分分离PID参数: p=7, i=1, d=18
滚珠丝杠参数	公称直径: 5 mm
	弹性模量: 200 GPa
	黏度系数: 0.04
	丝杠导程: 2 mm
	滚珠直径: 1 mm
	摩擦系数: 0.002
	泊松比: 0.3
	滚珠数: 20
	黏压系数: 22 nm/N

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Attitude dynamics and aerodynamic compensation control of low-orbit mass moment spacecraft

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