Title

Nonlinear decoupling sliding mode control and attitude control of spacecraft

Document Type

Article

Publication Date

9-1989

Publication Title

IEEE Transactions on Aerospace and Electronic Systems

Volume

25

First page number:

621

Last page number:

633

Abstract

Control of a class of uncertain nonlinear systems which can be decoupled by state-variable feedback is considered. A variable-structure-control (VSC) law is derived so that in the closed-loop system the output variables asymptotically track given output trajectories in spite of any uncertainty in the system. On the basis of this result, a control law is derived for the attitude control of an orbiting spacecraft in the presence of uncertainty using reaction jets. The controlled outputs are the three Euler angles which describe the orientation of the spacecraft relative to an orbital frame. Simulation results are presented to show that, in the closed-loop system, precise attitude control is accomplished in spite of the uncertainty in the system.

Keywords

Computer science; Control systems; Nonlinear control systems; Nonlinear systems; Output feedback; Sliding mode control; Space vehicles; State feedback; Trajectory; Uncertainty

Disciplines

Aeronautical Vehicles | Aerospace Engineering | Controls and Control Theory | Electrical and Computer Engineering | Electrical and Electronics | Multi-Vehicle Systems and Air Traffic Control | Power and Energy | Signal Processing | Space Vehicles | Systems Engineering and Multidisciplinary Design Optimization

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: http://dx.doi.org/10.1109/7.42079

UNLV article access

Search your library

Share

COinS