Adaptive tracking control using synthesized velocity from attitude measurements

被引：145

作者：

Wong, H

de Queiroz, MS ^{[1
]}

Kapila, V

机构：

[1] Polytech Univ, Dept Mech Engn, Brooklyn, NY 11201 USA

[2] Louisiana State Univ, Dept Mech Engn, Baton Rouge, LA 70803 USA

来源：

AUTOMATICA | 2001年 / 37卷 / 06期

基金：

美国国家航空航天局;

关键词：

attitude tracking; adaptive control; output feedback; spacecraft;

D O I：

10.1016/S0005-1098(01)00038-3

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

The attitude tracking control problem of uncertain rigid spacecraft without angular velocity measurements is addressed in this paper. The adaptive control law, which incorporates a velocity-generating filter from attitude measurements, is shown to ensure the asymptotic convergence of the attitude and angular velocity tracking errors despite unknown spacecraft inertia. Simulation results are presented to illustrate the theoretical results. (C) 2001 Elsevier Science Ltd. All rights reserved.

引用

页码：947 / 953

页数：7

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