Dynamic Feedback Linearization and Large Pitch Attitude Control of Satellite Using Solar Radiation Pressure

Document Type

Conference Proceeding

Publication Date

6-21-1995

Publication Title

Proceedings of the American Control Conference

Publisher

Institute of Electrical and Electronics Engineers

Volume

5

First page number:

3131

Last page number:

3135

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

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

Disciplines

Acoustics, Dynamics, and Controls | Aerospace Engineering | Mechanical Engineering | Navigation, Guidance, Control and Dynamics | Space Vehicles

Language

English

Comments

Conference Held: 21 Jun 1995-23 Jun 1995; Seattle, WA

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.

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