[1]尉明军,王长青,徐 骋.基于改进LQR的航向静不稳定飞行器控制方法研究[J].控制与信息技术(原大功率变流技术),2019,(04):85-90.[doi:10.13889/j.issn.2096-5427.2019.04.014]
 WEI Mingjun,WANG Changqing,XU Cheng.Research on Heading Statically Unstable Aircraft Control Method Based on Improved LQR[J].High Power Converter Technology,2019,(04):85-90.[doi:10.13889/j.issn.2096-5427.2019.04.014]
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基于改进LQR的航向静不稳定飞行器控制方法研究()
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《控制与信息技术》(原《大功率变流技术》)[ISSN:2095-3631/CN:43-1486/U]

卷:
期数:
2019年04期
页码:
85-90
栏目:
“中国飞行力学学术年会”专刊
出版日期:
2019-08-05

文章信息/Info

Title:
Research on Heading Statically Unstable Aircraft Control Method Based on Improved LQR
文章编号:
2096-5427(2019)04-0085-05
作者:
尉明军王长青徐 骋
(复杂系统控制与智能协同技术重点实验室,北京 100074)
Author(s):
WEI MingjunWANG ChangqingXU Cheng
( Science and Technology on Complex System Control and Intelligent Agent Cooperation Laboratory, Beijing 100074, China )
关键词:
航向静不稳定改进LQR控制器增稳控制回路
Keywords:
heading static instability improved LQR controller augmented stability control loop
分类号:
V249.1
DOI:
10.13889/j.issn.2096-5427.2019.04.014
文献标志码:
A
摘要:
针对航向静不稳定飞行器横航向强耦合的特点,文章研究其横航向增稳控制方法。首先建立航向静不稳定飞行器的横航向耦合数学模型;之后针对常规LQR(线性二次型调节器)控制器存在稳态误差以及侧滑角不易测量的问题,利用准增广LQR方法设计了横航向增稳控制回路;最后进行了飞行器跟踪不同指令时的弹道仿真。仿真结果表明,本文所提增稳回路设计方法能够使得航向静不稳定飞行器实现输入指令的无静差跟踪,而且响应过程无超调、调节时间短。
Abstract:
Aiming at the characteristics of strong coupling between lateral and heading of heading statically unstable aircraft, the control method of lateral and heading stabilization was studied in this paper. Firstly, a lateral-heading coupling mathematical model of the course-statically unstable aircraft was established. Then, aiming at the steady-state error of the conventional LQR controller and the difficulty of measuring the sideslip angle, a quasi-augmented LQR method was used to design the lateral-heading stabilization control loop. Finally, the trajectory simulation of the aircraft tracking under different commands was carried out. Simulation results show that the method of stabilization loop design in this paper can make the course statically unstable aircraft achieve no static error tracking of input commands, and the response process is not overshoot, and the adjustment time is short.

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备注/Memo

备注/Memo:
收稿日期:2019-05-15
作者简介:尉明军(1994—),男,工程师,主要研究方向为导航制导与控制。
更新日期/Last Update: 2019-08-20