Boundary control of flexible aircraft wings for vibration suppression

被引：5
作者：
He, Xiuyu [1 ,2 ]
He, Wei [1 ,2 ]
Chen, Yunan [1 ,2 ]
Mu, XinXing [1 ,2 ]
Yu, Yao [1 ,2 ]
Sun, Changyin [3 ]
机构：
[1] Univ Sci & Technol Beijing, Minist Educ, Sch Automat & Elect Engn, Beijing, Peoples R China
[2] Univ Sci & Technol Beijing, Minist Educ, Key Lab Knowledge Automat Ind Proc, Beijing, Peoples R China
[3] Southeast Univ, Sch Automat, Nanjing, Jiangsu, Peoples R China
来源：
INTERNATIONAL JOURNAL OF CONTROL | 2019年 / 92卷 / 11期
基金：
北京市自然科学基金; 中国国家自然科学基金;
关键词：
Partial differential equation; boundary control; flexible aircraft wings; distributed parameter system; flexible structure; EULER-BERNOULLI BEAM; FLIGHT DYNAMICS; PDE BOUNDARY; STABILIZATION; SYSTEMS;
D O I：
10.1080/00207179.2018.1442025
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In this paper, we propose a boundary control strategy for vibration suppression of two flexible wings. As a basic approach, Hamilton's principle is used to ascertain the system dynamic model, which includes governing equations - four partial differential equations and boundary conditions - several ordinary differential equations. Considering the coupled bending and torsional deformations of flexible wings, boundary control force and torque act on the fuselage to regulate unexpected deformations of flexible wings. Then, we present the stability analysis of the closed-loop system through Lyapunov's direct method. Simulations are carried out by using finite difference method. The simulation experimental results illustrate the significant effect of the developed control strategies.
引用
收藏
页码：2499 / 2508
页数：10
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