Robust attitude control of low earth orbit small satellite subject to actuator saturation

The electromagnetic torquer is the most common method to generate torque for attitude control of low earth orbit (LEO) small satellite. Due to power consideration, an actuator saturation is one of serious problem in practice. In this paper, we propose the scheme to design the robust controller to st...

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Bibliographic Details
Published inECTI-CON 2010 : the 2010 ECTI International Confernce on Electrical Engineering/Electronics, Computer, Telecommunications and Information Technology : 19-21 May 2010 pp. 713 - 717
Main Authors Artitthang, Peerawat, Malyavej, Veerachai, Aorpimai, Manop
Format Conference Proceeding
LanguageEnglish
Published IEEE 01.05.2010
Subjects
Actuators
Attitude control
Low earth orbit satellites
Magnetic fields
Open loop systems
Regulators
Robust control
Small satellite
Space vehicles
Torque control
Uncertainty
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ISBN9781424456062
1424456061

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Summary:The electromagnetic torquer is the most common method to generate torque for attitude control of low earth orbit (LEO) small satellite. Due to power consideration, an actuator saturation is one of serious problem in practice. In this paper, we propose the scheme to design the robust controller to stabilize a satellite attitude by considering the actuator saturation as a structured uncertainty which is based on integral quadratic constraint. The proposed robust controller is of linear time varying controller that has similar structure as conventional linear quadratic regulator (LQR). The simulation results show that our proposed robust controller outperforms an LQR controller.
ISBN:9781424456062
1424456061