Attitude-control of a 3 Rotor Gyrostat in the Presence of Uncertainty

Document Type

Article

Publication Date

9-1-1987

Publication Title

Journal of the Astronautical Sciences

Volume

35

First page number:

329

Last page number:

345

Abstract

A nonlinear control law for large angle rotational maneuvers of spacecraft using reaction wheels in the presence of uncertainty is presented. The derivation of this suboptimal control law does not require any information on the values of the system parameters and the disturbance torques acting on the spacecraft. The controller includes a dynamic system in the feedback path. The control law is a nonlinear function of the attitude error, the rate of the attitude error and the compensator state. Simulation results are presented to show that large angle rotational maneuvers can be performed in spite of the uncertainty in the system.

Keywords

Astrodynamics; Nonlinear equations; Rolling moments; Rotary gyroscopes; Satellite attitude control; Spacecraft control; Spacecraft maneuvers

Disciplines

Aerodynamics and Fluid Mechanics | Aeronautical Vehicles | Aerospace Engineering | Electrical and Computer Engineering | Navigation, Guidance, Control and Dynamics | Signal Processing | Structures and Materials | Systems and Communications

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.


Search your library

Share

COinS