Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft

Author

Zhu, Liangkuan ; Liu, Yaqiu ; Wang, Dailin ; Hu, Qinglei

Author_Institution

Northeast Forestry Univ., Harbin

fYear

2008

fDate

2-4 July 2008

Firstpage

887

Lastpage

891

Abstract

A novel hybrid robust control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. Based on the backstepping, a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.

Keywords

aircraft control; attitude control; control system synthesis; electric sensing devices; feedback; flexible structures; motion control; numerical analysis; piezoelectric actuators; piezoelectric materials; robust control; space vehicles; vehicle dynamics; vibration control; active vibration reduction; attitude motion control; backstepping-based attitude maneuver control; flexible spacecraft; piezoelectric materials; robust attitude control law; robust control design method; strain rate feedback control; vibration stabilization; vibration supression; Aircraft manufacture; Attitude control; Backstepping; Capacitive sensors; Design methodology; Motion control; Robust control; Space vehicles; Strain control; Vibration control; Attitude maneuvering; Backstepping; Flexible spacecraft;

fLanguage

English

Publisher

ieee

Conference_Titel

Control and Decision Conference, 2008. CCDC 2008. Chinese

Conference_Location

Yantai, Shandong

Print_ISBN

978-1-4244-1733-9

Electronic_ISBN

978-1-4244-1734-6

Type

conf

DOI

10.1109/CCDC.2008.4597441

Filename

4597441