DocumentCode :
3370741
Title :
Fuzzy attitude control for flexible satellite during orbit maneuver
Author :
Yingying, Liu ; Jun, Zhou
Author_Institution :
Inst. of Precision Guidance & Control, Northwestern Polytech. Univ., Xi´´an, China
fYear :
2009
fDate :
9-12 Aug. 2009
Firstpage :
1239
Lastpage :
1243
Abstract :
Satellite with a large solar panel is taken as practical background. The dynamic model of the satellite is established via Lagrange equations. This model includes the orbit motion, the attitude motion and the flexible vibration of the solar panel. The coupling relations between the orbit control force, the attitude and the flexible vibration are studied. The orbit control force would stimulate the vibration of the flexible panel when the satellite takes orbital maneuver, and disturbance torque would also affect the attitude of the satellite. Attitude control law is designed based on fuzzy control theory considering the output character of the thrusters. Numerical simulation was carried out to testify the efficiency of the control system. The attitude angles are controlled within 0.6deg for all three axes and angular velocity is within 0.04deg/s during the orbit maneuver period.
Keywords :
artificial satellites; attitude control; flexible structures; fuzzy control; matrix algebra; motion control; position control; Lagrange equation; angular velocity; attitude angles; attitude motion; control law design; coupling relation; disturbance torque; flexible satellite; flexible vibration; fuzzy attitude control; orbit control force; orbit maneuver; orbit motion; satellite dynamic model; solar panel; translation matrix; Attitude control; Equations; Force control; Fuzzy control; Lagrangian functions; Numerical simulation; Satellites; System testing; Torque control; Vibration control; attitude control; flexible satellite; fuzzy control; orbit maneuver;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Mechatronics and Automation, 2009. ICMA 2009. International Conference on
Conference_Location :
Changchun
Print_ISBN :
978-1-4244-2692-8
Electronic_ISBN :
978-1-4244-2693-5
Type :
conf
DOI :
10.1109/ICMA.2009.5246588
Filename :
5246588
Link To Document :
بازگشت