结冰条件下的飞行控制律重构设计方法

doi:10.13700/j.bh.1001-5965.2018.0358

北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (3): 606-613.doi: 10.13700/j.bh.1001-5965.2018.0358

结冰条件下的飞行控制律重构设计方法

王良禹, 徐浩军, 李颖晖, 李哲

空军工程大学航空工程学院, 西安 710038

收稿日期:2018-06-13 出版日期:2019-03-20 发布日期:2019-04-04
通讯作者: 徐浩军,E-mail:xuhaojun1965@163.com E-mail:xuhaojun1965@163.com
作者简介:王良禹,男,硕士研究生。主要研究方向:飞行力学及飞行仿真;徐浩军,男,硕士,教授,博士生导师。主要研究方向:飞行力学及飞行安全、隐身。
基金资助:
国家"973"计划（2015CB755800）；民用飞机专项科研（MJ-2015-F-019）

Reconfigurable design method of flight control law under icing conditions

WANG Liangyu, XU Haojun, LI Yinghui, LI Zhe

College of Aeronautic Engineering, Air Force Engineering University, Xi'an 710038, China

Received:2018-06-13 Online:2019-03-20 Published:2019-04-04

摘要/Abstract

摘要： 针对飞机结冰条件下的飞行安全问题，在线性结冰影响模型的基础上构建了非线性结冰影响模型，并建立了结冰飞机纵向非线性动力学模型。利用反馈线性化理论与模糊控制原理相结合，重构设计了结冰条件下的纵向控制律，既保证了动态响应特性，又改善了控制器的抗干扰能力，使飞机具备一定的容冰飞行能力。通过仿真模拟了飞机在不同结冰严重程度以及干扰下的纵向响应，并与常规PID控制进行对比，验证了设计控制律的有效性和抗干扰能力。结果表明，该设计方案下的各状态参数动态响应均能较快较好地收敛，能更精准快速地跟踪俯仰角指令，且抗干扰能力、动态性能均优于常规PID控制。

关键词: 飞机结冰, 结冰影响模型, 反馈线性化, 模糊控制, 控制律重构

Abstract: For the flight safety of icing aircraft, the nonlinear icing effect model was built based on the linear icing effect model, and then the nonlinear longitudinal dynamics model of icing aircraft was established. Through the combination of feedback linearization and fuzzy control theory, the reconfigurable design of longitudinal control law under icing condition was completed, which ensures the dynamic response characteristic and promotes the anti-interference ability of the controller, allowing the aircraft to fly under icing condition. The simulation of the aircraft longitudinal dynamic response under various icing severity and interference conditions was carried out, and then by comparison with the conventional PID control, the effectiveness and anti-interference ability of the designed control law are verified. The results show that the dynamic response of each state parameter under the designed control law can converge quickly and greatly and track the pitch angle instructions faster and more accurately. In addition, the anti-interference capability and dynamic performance of the designed control law are better than those of the conventional PID control.

Key words: aircraft icing, icing effect model, feedback linearization, fuzzy control, reconfigurable control law

中图分类号:

V212

王良禹, 徐浩军, 李颖晖, 李哲. 结冰条件下的飞行控制律重构设计方法[J]. 北京航空航天大学学报, 2019, 45(3): 606-613.

WANG Liangyu, XU Haojun, LI Yinghui, LI Zhe. Reconfigurable design method of flight control law under icing conditions[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2019, 45(3): 606-613.

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结冰条件下的飞行控制律重构设计方法

Reconfigurable design method of flight control law under icing conditions

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