Dynamics and fuzzy control for short tethered satellite

Author

Liu Yingying ; Zhou Jun

Author_Institution

Inst. of Precision Guidance & Control, Northwestern Polytech. Univ., Xi´an, China

Volume

2

fYear

2009

fDate

20-22 Nov. 2009

Firstpage

679

Lastpage

683

Abstract

Dynamic and control for short tethered satellite in short distance space operation is studied. The dynamic model of the tethered satellite is established. The deploy method for short tethered satellite is discussed. The dynamic characters of the system in the developing phase are analyzed. The subsatellite could be deployed to directions other than the vertical direction with an initial velocity. Fuzzy control scheme is designed considering the precision of the tether direction and the output character of the thrusters. The fuzzy control system can keep the sub-satellite in the ideal direction. The angles of the tether are within 0.5 deg from the ideal values and angular velocity is within 0.03 deg/s during the developing period. Thrusters do not need to work frequently. Numerical simulation testified the efficiency of the system.

Keywords

artificial satellites; dynamics; fuzzy control; angular velocity; dynamic model; fuzzy control system; initial velocity; numerical simulation; short distance space operation; short tethered satellite; Angular velocity; Earth; Fuzzy control; Numerical simulation; Power generation; Satellites; Space missions; Stability; System testing; Transportation; developing phase; dynamic model; fuzzy control; tetherd satellite;

fLanguage

English

Publisher

ieee

Conference_Titel

Intelligent Computing and Intelligent Systems, 2009. ICIS 2009. IEEE International Conference on

Conference_Location

Shanghai

Print_ISBN

978-1-4244-4754-1

Electronic_ISBN

978-1-4244-4738-1

Type

conf

DOI

10.1109/ICICISYS.2009.5358306

Filename

5358306