Velocity-free spacecraft attitude stabilization using two control torques

被引：6

作者：

Frias, Alexander ^{[1
]}

de Ruiter, Anton K. J. ^{[1
]}

Kumar, Krishna Dev ^{[1
]}

机构：

[1] Ryerson Univ, Dept Aerosp Engn, Toronto, ON M5B 2K3, Canada

来源：

AUTOMATICA | 2019年 / 109卷

基金：

加拿大自然科学与工程研究理事会;

关键词：

Inertial-pointing spacecraft; Time-varying output-feedback control; Underactuated systems; Velocity-free; MODEL-PREDICTIVE CONTROL; UNDERACTUATED SPACECRAFT; TRACKING CONTROL;

D O I：

10.1016/j.automatica.2019.108553

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 stabilization of an inertial-pointing underactuated rigid-body spacecraft using two torques under time-varying disturbances and inertia matrix uncertainties is examined. An observer-based time-varying output feedback control law is proposed where angular velocity measurements are not available. The stability of the combined controller-observer system is proven rigorously to show local ultimate boundedness of all states. A comprehensive numerical example is presented with sampled data implementation of the observer-based control law to demonstrate convergence even with very large initial attitude errors. (C) 2019 Elsevier Ltd. All rights reserved.

引用

页数：8

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