PARAMETER-ROBUST FLIGHT CONTROL-SYSTEM FOR A FLEXIBLE AIRCRAFT

被引：10

作者：

KUBICA, F ^{[1
]}

LIVET, T ^{[1
]}

LETRON, X ^{[1
]}

BUCHARLES, A ^{[1
]}

机构：

[1] CERT,ONERA,F-31400 TOULOUSE,FRANCE

来源：

CONTROL ENGINEERING PRACTICE | 1995年 / 3卷 / 09期

关键词：

FLIGHT CONTROL; OPTIMAL CONTROL; EIGENVALUE ASSIGNMENT; OPTIMIZATION; PARAMETER ROBUSTNESS;

D O I：

10.1016/0967-0661(95)00119-F

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

This paper discusses the design of a flight control system for a flexible aircraft, with significant coupling between flight mechanics and structural dynamics modes. Based on a longitudinal model, a normal acceleration control law is designed with a new synthesis technique, which is in fact a mixing of optimal control and eigenstructure assignment by means of constrained optimization. This technique is used to stabilize both rigid and elastic modes in an initial step, and to increase parameter robustness in the second.

引用

页码：1209 / 1215

页数：7

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