一种微型航天器姿态跟踪的四元数实现方法  

A Quaternion Method for Attitude Tracking of Micro Spacecraft

作　　者：冯路明 路坤锋[1,2] 刘晓东 Feng Luming;Lu Kunfeng;Liu Xiaodong(Beijing Aerospace Automatic Control Institute,Beijing 100854,China;National Key Laboratory of Science and Technology on Aerospace Intelligence Control,Beijing 100854,China)

机构地区：[1]北京航天自动控制研究所,北京100854 [2]宇航智能控制技术国家级重点实验室,北京100854

出　　处：《航天控制》2023年第1期15-20,共6页Aerospace Control

摘　　要：针对航天器姿态跟踪问题,建立了基于误差四元数的姿态控制系统二阶数学模型。基于现代控制理论,通过设计四元数状态反馈控制器对姿态控制系统的极点进行配置,实现航天器姿态的稳定跟踪。仿真结果表明,设计的状态反馈控制器能够实现微型航天器的高精度姿态跟踪控制。Regarding the attitude tracking control of spacecraft,a second-order mathematical model of attitude control system based on error quaternion is established. Based on modern control theory,a state feedback controller based on error quaternion is designed to configure the poles of the attitude control system and realize the attitude stable tracking of spacecraft. The simulation results show that the state feedback controller can achieve high precision attitude tracking control of micro spacecraft.

关 键 词：微型航天器 误差四元数 姿态跟踪控制 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]