Fang Xinxiang, Wen Ming
Hunan Mechanical and Electrical Ploytechnic, Changsha, Hunan, China.
Hunan Mingxiang Aviation Technology Co., Ltd., Changsha, Hunan, China.
PLoS One. 2025 Jul 17;20(7):e0328622. doi: 10.1371/journal.pone.0328622. eCollection 2025.
The significance of spacecraft in modern aerospace and technology is indisputable, with attitude control systems (ACS) playing a vital role in ensuring mission accuracy and safety. This study presents a dual-loop sliding mode variable structure control approach for spacecraft attitude regulation, leveraging integral sliding mode control (SMC) to design robust switching functions. The outer loop generates the angular velocity command [Formula: see text] by tracking the desired attitude angle [Formula: see text], while the inner loop ensures accurate torque control based on this command. The control architecture comprises an inner velocity loop and an outer position loop, with the inner loop deliberately designed to converge faster, ensuring overall system stability. Numerical simulations validate the proposed strategy's effectiveness and highlight its potential for real-world aerospace applications.
航天器在现代航空航天和技术中的重要性是无可争议的，姿态控制系统（ACS）在确保任务准确性和安全性方面发挥着至关重要的作用。本研究提出了一种用于航天器姿态调节的双回路滑模变结构控制方法，利用积分滑模控制（SMC）设计鲁棒切换函数。外环通过跟踪期望姿态角[公式：见原文]生成角速度指令[公式：见原文]，而内环基于该指令确保精确的转矩控制。控制架构包括一个内速度环和一个外位置环，内环比刻意设计为收敛更快，以确保整个系统的稳定性。数值模拟验证了所提出策略的有效性，并突出了其在实际航空航天应用中的潜力。
