高轨卫星角动量管理的太阳电池阵转角控制

doi:10.12305/j.issn.1001-506X.2024.11.26

Abstract

Abstract:

To extend the angular momentum unloading period of high-orbit satellites, a solar array angle control method for high-orbit satellite angular momentum management is proposed. Firstly, a solar array angle control model is constructed, and the solar array angle control used for satellite momentum management is transformed into a constrained optimization problem based on the solar array angle control model. Then, from an engineering perspective, the solar array angle control problem for momentum management is simplified based on the characteristics of commonly-used symmetric configuration of two-wing solar array panels, and a simple and practical control law for solar array angle is proposed. Finally, the proposed method is verified by numerical simulation and on-orbit environmental disturbance data of a remote sensing satellite. Simulation results show that the proposed method can significantly reduce the accumulation of satellite angular momentum and extend the momentum unloading period.

Key words: high-orbit satellite, solar array, angular momentum management, control law, constrained optimization

CLC Number:

V448.2

Yikang HE, Shuyu LIN, Sen YANG, Zhenhua WANG, Wen HE. Solar array angle control for high-orbit satellite angular momentum management[J]. Systems Engineering and Electronics, 2024, 46(11): 3835-3843.

Figures/Tables 11

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参数	数值
轨道类型	地球静止轨道
太阳电池阵面积/m²	9.5
+Y翼压心矢量/m	[0, 5.1, 0.4]^T
－Y翼压心矢量/m	[0, －4.9, 0.4]^T
镜面反射率C_rs	0.05
漫反射系数C_rd	0.22
初始角动量/Nms	[5.0, 0, －5.0]^T
卫星惯量矩阵/(kg·m²)	$ \left[\begin{array}{ccc} 7\ 540.0 & 80.2 & -105.8 \\ 80.2 & 6\ 437.0 & 269.3 \\ -105.8 & 269.3 & 4\ 610.0 \end{array}\right]$

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Solar array angle control for high-orbit satellite angular momentum management

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