Design of Attitude Control System for Flexible Inflatable Spacecraft

doi:10.12382/bgxb.2021.0593

Abstract

Abstract: An attitude control method based on the theory of active disturbance rejection control is proposed to accurately control the attitude of flexible inflatable spacecraft. A rigid-flexible coupling dynamic model is established， and a coupling attitude control system is designed using the linear active disturbance rejection controller，attitude maneuver path planning algorithm，pulse-width pulse-frequency (PWPF) modulator and low-pass filter. The control system can be used to control the attitude and suppress the elastic vibration simultaneously. The numerical simulations are conducted to verify the effectiveness of the proposed system. In contrast to the traditional PID control，the simulated results show that the attitude control system for flexible inflatable spacecraft designed by the proposed attitude control method can adapt to large-angle attitude maneuver and effectively suppress the flexible vibration of inflatable capsule，improve the attitude accuracy of flexible spacecraft and avoid frequent on-off of the engine to save fuel.

Key words: inflatablespacecraft, attitudecontrol, activedisturbancerejectioncontrol, rigid-flexiblecoupling

CLC Number:

V448.2

ZHAO Chunming， JIAO Shenghai， WANG Xiaofei， YAO Yuemin， HUANG Chaodong. Design of Attitude Control System for Flexible Inflatable Spacecraft[J]. Acta Armamentarii, 2022, 43(6): 1346-1354.

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