Adaptive output feedback control of spacecraft with flexible appendages

Author

Zhang, Rong ; Singh, Sahjendra N.

Author_Institution

Dept. of Electr. & Comput. Eng., Nevada Univ., Las Vegas, NV, USA

Volume

4

fYear

2001

fDate

2001

Firstpage

3103

Abstract

An adaptive control system for the rotational maneuver and vibration suppression of an orbiting spacecraft with flexible appendages is designed. The model of the spacecraft includes unstructured modelling uncertainties. For the purpose of control, a moment generating device is located on the rigid hub. For the synthesis of the control law, only the output variable (pitch angle) is used for feedback. An adaptive feedback linearizing control law is derived for the trajectory control of the pitch angle. The structure of the controller is independent of the dimension of the state space of the spacecraft model, since unmodeled functions appearing in the inverse (feedback linearizing) control law are estimated using a high-gain observer for feedback. Simulation results for the spacecraft model of different dimensions show precise trajectory control and vibration suppression

Keywords

adaptive control; control system synthesis; feedback; position control; space vehicles; adaptive control system; adaptive feedback; control system synthesis; moment generating device; orbiting spacecraft; rotational maneuver; spacecraft; state space; trajectory control; unstructured modelling uncertainties; vibration suppression; Adaptive control; Control system synthesis; Linear feedback control systems; Output feedback; Programmable control; Space vehicles; State feedback; State-space methods; Uncertainty; Vibration control;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 2001. Proceedings of the 2001

Conference_Location

Arlington, VA

ISSN

0743-1619

Print_ISBN

0-7803-6495-3

Type

conf

DOI

10.1109/ACC.2001.946396

Filename

946396