本文首先介绍了逆系统方法的基本思想，然后将其用于航天器非线性姿态控制系统的设计中。
In this paper, the basic theory of the inverse system method is introduced, and is used in the design of a spacecraft attitude control system.
这样通过非线性状态变换和非线性状态反馈，将飞行器原来的6阶非线性姿态模型部分精确线性化为二阶线性系统。
Thus by nonlinear state transformation and nonlinear state feedback, the original 6 order nonlinear attitude model of a spacecraft is partially precisely linearized into a 2 order linear system.
利用多重时间尺度奇异摄动理论，结合非线性动态逆方法设计了基本姿态控制器，包括快逆回路和慢逆回路两部分。
According to the singularity perturbation theory, dynamic inversion is adopted to design the basic attitude controller including fast inverse loop and slow inverse loop.
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