Design of Aircraft Control System Based on Adaptive Optimal Control

被引：0
|
作者：
Qiang, A. Jiajiu [1 ]
Meng, B. Xiuyun [2 ]
Wu, C. Guanghui [1 ]
机构：
[1] Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China
[2] Beijing Inst Technol, Beijing 100081, Peoples R China
来源：
2018 IEEE CSAA GUIDANCE, NAVIGATION AND CONTROL CONFERENCE (CGNCC) | 2018年
关键词：
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
For the uncertainty of the aircraft dynamics parameters, the adaptive control method was used to design the control parameters so as to ensure the stability of the aircraft control system. When designing the reference model of the controller, the linear quadratic optimal control method was used to make the reference model behave as a typical second-order link Based on the Lyapunov stability theory, the self-adaptation law was deduced to ensured the closed-loop stability of the system. The simulation results showed that the control method designed in this paper can keep track of the reference model when the aircraft dynamics parameters changed.
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页数：6
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