飞行器姿态系统变结构控制的研究

RESEARCH ON ATTITUDE SYSTEM OF FLYING VEHICLE WITH VARIABLE STRUCTURE CONTROL

对于具有纯延迟、惯性和由开关控制的非线性飞行器姿态系统，本文提出了采用解耦变结构控制的方法。计算机仿真结果表明，本方法行之有效，具有优良的鲁棒性。

For nonlinear attitude system of flying vehicle with pure time-delay, inertia and bang-bang control a control method using decoupling variable structure is given. Results of computer simulation indicate that it is effective for the method and has advantages of excellent robustness, simple design method and easily realized digital control etc.