Aircraft lateral linear parameter varying model predictive control with time varying weight

被引：0
作者：
Zhu, Qi-Dan [1 ]
Wang, Li-Peng [1 ]
Zhang, Zhi [1 ]
Wen, Zi-Xia [1 ]
机构：
[1] College of Automatic, Harbin Engineering University, Harbin, 150001, Heilongjiang
来源：
Kongzhi Lilun Yu Yingyong/Control Theory and Applications | 2015年 / 32卷 / 01期
基金：
中国国家自然科学基金;
关键词：
Automatic landing; Lateral control; Linear matrix inequalities; Linear parameter-varying; Model predictive control;
D O I：
10.7641/CTA.2015.40224
中图分类号：
学科分类号：
摘要：
The concept and calculation method of arresting risk function are provided for the carrier aircraft hanging and arresting stage. Time-varying weight matrix of states and controlling inputs can be acquired by means of off-line calculation. The varied relation-ship between different states could be adjusted by employing time-varying states weight matrix in real time. At the same time, the controlling peak of aileron and rudder can be adjusted by varying controlling inputs weight matrix to avoid inputs saturation in real time. Therefore, the efficiency and safety of aircraft automatic landing could be improved. Time-varying system output constraint function is established to increase the feasibility of controller in the aircraft initial leading stage. Carrier aircraft lateral landing model is set up based on state deviations. For many states of the aircraft could not be measured directly, an off-line states observer is designed to estimate the real states of aircraft. Optimal solutions are solved by linear matrix inequalities. The simulation results verify the feasibility of the algorithm in the aircraft automatic landing three-dimensional simulation platform. ©, 2015, South China University of Technology. All right reserved.
引用
收藏
页码：101 / 109
页数：8
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