Adaptive decoupling control for a class of spinning rockets considering actuator dynamics

被引：0
|
作者：
Shi Z. [1 ]
Zhu H. [2 ]
Zhao L. [1 ]
Liu Z. [3 ]
机构：
[1] School of Aerospace Engineering, Beijing Institute of Technology, Beijing
[2] School of Mechatronical Engineering, Beijing Institute of Technology, Beijing
[3] School of Automation and Electrical Engineering, University of Science and Technology Beijing, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 03期
基金：
中国国家自然科学基金;
关键词：
Actuator dynamics; Adaptive control; Decoupling control; Quadratic stability; Spinning rocket;
D O I：
10.7527/S1000-6893.2021.25068
中图分类号：
学科分类号：
摘要：
An adaptive decoupling control method considering aerodynamic uncertainty and actuator dynamics is proposed to solve the strong coupling problem caused by aerodynamic, inertial and control cross-coupling.Considering a type of canard controlled spinning rockets, an acceleration dynamic model considering actuator dynamics is established under the non-rolling body frame.Using the model reference adaptive control method as the basic framework, the tracking error integral is extended to the controlled system to improve the tracking performance of the closed-loop system.The error signal between the input and output of the actuator is fed back into the reference model to realize the decoupling between the pitch and yaw channels.Theoretical analysis and numerical simulation show the effectiveness of the proposed method.The simulation results show that the adaptive decoupling controller developed in our study can ensure stability of the closed-loop system and realize the decoupling between the pitch and yaw channels. © 2022, Beihang University Aerospace Knowledge Press. All right reserved.
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