Title

Feedback Linearization and Solar Pressure Satellite Attitude Control

Document Type

Article

Publication Date

4-1996

Publication Title

IEEE Transactions on Aerospace and Electronic Systems

Volume

32

Issue

2

First page number:

732

Last page number:

741

Abstract

The question of large angle pitch attitude maneuver of satellites using solar radiation pressure is considered. For pitch axis maneuver, two highly reflective control surfaces are used to generate radiation moment. Based on dynamic feedback linearization, a nonlinear control law is derived for large pitch attitude control. In the closed-loop system, the response characteristics of the pitch angle are governed by a fourth-order linear differential equation. Robustness of control system is obtained by the integral error feedback. Simulation results are presented to show that in the closed-loop system, attitude control of the satellite is accomplished in spite of the parameter uncertainty in the system.

Keywords

Artificial satellites – Attitude; Artificial satellites – Attitude control systems; Artificial satellites – Attitude – Effect of radiation pressure on; Feedback control systems; Radiation pressure; Solar radiation

Disciplines

Mechanical Engineering | Navigation, Guidance, Control and Dynamics | Space Vehicles

Language

English

Permissions

Use Find in Your Library, contact the author, or interlibrary loan to garner a copy of the item. Publisher policy does not allow archiving the final published version. If a post-print (author's peer-reviewed manuscript) is allowed and available, or publisher policy changes, the item will be deposited.

Identifier

DOI: 10.1109/7.489516

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