Title

Feedback Linearization and Solar Pressure Satellite Attitude Control

Document Type

Article

Publication Date

4-1996

Publication Title

Institute of Electrical and Electronics Engineers 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; Artificial satellites — Attitude — Effect of radiation pressure on; Control systems; Differential equations; Error correction; Feedback control systems; Linear control systems; Linear feedback control systems; Nonlinear dynamical systems; Nonlinear systems; Robust control systems; Solar energy; Solar power generation; Solar radiation; Uncertain systems

Permissions

Use Find in Your Library, contact the author, or use interlibrary loan to garner a copy of the article. Publisher copyright policy allows author to archive post-print (author’s final manuscript). When post-print is available or publisher policy changes, the article will be deposited

Identifier

DOI: 10.1109/7.489516

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