Coupled orbit-attitude dynamics and trajectory tracking control for spacecraft electromagnetic docking

Keke Shi, Chuang Liu, Zhaowei Sun, Xiaokui Yue

科研成果: 期刊稿件文章同行评审

66 引用 (Scopus)

摘要

In this paper, the simplified electromagnetic force/torque model and coupled orbit-attitude dynamics modeling in spacecraft electromagnetic docking are investigated, and an improved sliding mode control scheme based on planned trajectory is proposed. In this scenario, the docking two spacecraft are equipped with four energized solenoids with iron cores fixed in the body frame, and small-angle hypothesis is used to derive the simplified electromagnetic force/torque model, based on which the coupled orbit-attitude dynamics equation is established. With trajectory planning of relative orbit and attitude, where the tracking process of coupled orbit-attitude is divided into three successive parts with predefined time using three characteristic time instants, a sliding mode control strategy is proposed to solve the tracking problem. Simulation results illustrate the simplification rationality of electromagnetic force/torque model, and the good tracking performance of coupled orbit-attitude tracking controller at predefined time.

源语言英语
页(从-至)553-572
页数20
期刊Applied Mathematical Modelling
101
DOI
出版状态已出版 - 1月 2022

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