Attitude tracking and vibration suppression of flexible spacecraft using implicit adaptive control law

被引：9

作者：

Shahravi, M ^{[1
]}

Kabganian, M ^{[1
]}

机构：

[1] Amirkabir Univ Technol, Dept Mech Engn, Tehran, Iran

来源：

ACC: Proceedings of the 2005 American Control Conference, Vols 1-7 | 2005年

关键词：

D O I：

10.1109/ACC.2005.1470076

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

Control degree of freedom is much fewer than the motion degree of freedom when a flexible system is commanded to track a desired trajectory. Many control strategies that succeed in the conventional rigid systems, can not be directly applied to control of flexible systems. In this paper, a nonlinear control scheme is proposed as a solution of these problems in attitude control of a flexible spacecraft. In particular, to cope with the existing model uncertainty, an adaptive version of the control law is proposed. The model of the spacecraft considered as a rigid central body and two elastic appendages. Stability proof of the overall closed loop system is given via Lyapunov analysis. Numerical simulations show the effectiveness of the proposed controller.

引用

页码：913 / 918

页数：6

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