大型航天器SGCMG系统基于模糊决策的操纵律设计研究

作为航天器制导、导航和控制系统的执行部件，单框架控制力矩陀螺是较为理想的大型航天器姿控系统的选择，但是单框架控制力矩陀螺系统（ＳＧＣＭＧ）存在严重的奇异现象，增加了操纵律的设计与开发的难度。本文对ＳＧＣＭＧ系统的奇异性进行了分析，利用模糊决策的思想确定了奇异测度，根据奇异测度梯度搜索法设计了基于模糊决策的ＳＧＣＭＧ系统操纵律。仿真试验表明该方法有效地保证了系统能够回避可避的奇异状态，为大型航天器操纵律设计提供了新的思路。

Study on Steering Law of Large Spacecraft SGCMG System Based on Fuzzy Decision

A single gimbal control moment gyro system is the best choice for large spacecraft attitude control systems, as executive components of spacecraft guidance, navigation, and control system. But the phenomenon of singularity exists in this system. This increases the difficulty in designing the steering law. Singularity of SGCMG system is analyzed in this paper. The singularity measurement is determined making use of a fuzzy decision. A singularity avoidance steering law of large spacecraft SGCMG system based on fuzzy decision is designed according to the idea of searching the singularity measurement's gradient. The simulation experiments show this method guarantees singularity avoidance of SGCMG system. This method provides a new idea for the steering law of large spacecraft.