基于LQR的小卫星磁姿态控制设计

Abstract

Abstract: The attitude control problem of low earth orbit(LEO)satellites actuated by magnetorquers only is investigated.By linearizing the nonlinear dynamic and kinematic equations of rigid satellites,a linear periodically time-varing system is obtained.The linear quadratic optimal regulator theory is applied to design an optimal control law for magnetorquers.Simulation results show that the designed optimal magnetic control law can stabilize three-axis attitude of satellites effectively.

Key words: small satellite, attitude control, linear quadratic regulator(LQR), magnetic control

CLC Number:

V448.2

GUO Yanning;LI Chuanjiang;MA Guangfu

. An LQR-Based Magnetic Attitude Control Design for Small Satellite[J]., 2008, 34(5): 61-64.

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An LQR-Based Magnetic Attitude Control Design for Small Satellite

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