Comparative study of various control methods for attitude control of a LEO satellite

Won, Chang-Hee

doi:10.1016/s1270-9638(00)86968-0

Cited by 58 publications

(24 citation statements)

References 6 publications

(5 reference statements)

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“…One reaction wheel is included as a hardware redundancy for the fault situation. The cone shape is known for the most efficient configuration with four reaction wheels [24][25]. The orientation matrix is given by sin cos sin sin cos sin cos sin sin cos sin cos sin sin cos sin cos sin sin cos …”

Section: Nonlinear Satellite Attitude Modelmentioning

confidence: 99%

Satellite Fault Detection and Isolation Scheme with Modified Adaptive Fading EKF

Lim¹,

Park²

2014

Journal of Electrical Engineering and Technology

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-This paper presents a modified adaptive fading EKF (AFEKF) for sensor fault detection and isolation in the satellite. Also, the fault detection and isolation (FDI) scheme is developed in three phases. In the first phase, the AFEKF is modified to increase sensor fault detection performance. The sensor fault detection and sensor selection method are proposed. In the second phase, the IMM filer with scalar penalty is designed to detect wherever actuator faults occur. In the third phase of the FDI scheme, the sub-IMM filter is designed to identify the fault type which is either the total or partial fault. An important feature of the proposed FDI scheme can decrease the number of filters for detecting sensor fault. Also, the proposed scheme can classify fault detection and isolation as well as fault type identification.

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Section: Nonlinear Satellite Attitude Modelmentioning

confidence: 99%

Satellite Fault Detection and Isolation Scheme with Modified Adaptive Fading EKF

Lim¹,

Park²

2014

Journal of Electrical Engineering and Technology

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“…6 This model assumes that the largest disturbance is the gravity gradient torque while other space disturbances are small and can thus be modeled as a stationary Wiener random process. Moreover the internal torques generated by a cluster of four reaction wheels and three thrusters are for use in controlling the attitude of the satellite.…”

Section: Mathematical Model Of Satellite With Reaction Wheels Andmentioning

confidence: 99%

Statistical Control Paradigm for Aerospace Structures Under Impulsive Disturbances

Pham

Robertson

2007

48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) AFRL-VS-PS-TP-2006-1047 SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)AFRL/VSSV SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. (Clearance #VS06-0327) SUPPLEMENTARY NOTESAccepted for publication in the 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 23-26 April 07, Sheraton Waikiki, Honolulu, Hawaii ABSTRACTIn this paper the newly developed statistical control theory is revisited to autonomously control the satellite attitude as well as to provide a means of actively attenuating impulsive disturbances caused by servicing dock and space debris. Simulations are performed using several docking and collision scenarios. The simulation results indicate that the existing attitude control system with an innovative and robust statistical controller design shows significant promise for use in attitude hold mode operation despite the presence of impulsive disturbances. In this paper the newly developed statistical control theory is revisited to autonomously control the satellite attitude as well as to provide a means of actively attenuating impulsive disturbances caused by servicing dock and space debris. Simulations are performed using several docking and collision scenarios. The simulation results indicate that the existing attitude control system with an innovative and robust statistical controller design shows significant promise for use in attitude hold mode operation despite the presence of impulsive disturbances. SUBJECT TERMS NomenclatureH C Angular momentum of the satellite about its center of mass measured in inertial frame {N } H W Angular momentum of the wheel cluster J C Satellite inertia J W Reaction wheel inertia ω S/N Angular velocity vector in fixed-body reference frame {S} ω W Angular velocity of the reaction wheels L Wheel orientation matrix τ thrt Absolute torque due to the thrusters τ W Absolute torque due to the reaction wheels τ grav Torque due to the earth gravity gradient τ mag Torque due to the earth magnetic field τ ...

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“…Several control schemes have been proposed for attitude control of satellites, ranging from linear control in (Parlos and Sunkel, 1992), H 2 and H ∞ in (Won, 1999), to the nonlinear control based on vectorial backstepping in (Bondhus et al, 2005).…”

Section: Introductionmentioning

confidence: 99%

bserver Based Sliding Mode Attitude Control: Theoretical and Experimental Results

Jørgensen

Gravdahl

2011

MIC

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In this paper we present the design of a sliding mode controller for attitude control of spacecraft actuated by three orthogonal reaction wheels. The equilibrium of the closed loop system is proved to be asymptotically stable in the sense of Lyapunov. Due to cases where spacecraft do not have angular velocity measurements, an estimator for the generalized velocity is derived and asymptotic stability is proven for the observer. The approach is tested on an experimental platform with a sphere shaped Autonomous Underwater Vehicle SATellite: AUVSAT, developed at the Norwegian University of Science and Technology.

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Comparative study of various control methods for attitude control of a LEO satellite

Cited by 58 publications

References 6 publications

Satellite Fault Detection and Isolation Scheme with Modified Adaptive Fading EKF

Satellite Fault Detection and Isolation Scheme with Modified Adaptive Fading EKF

Statistical Control Paradigm for Aerospace Structures Under Impulsive Disturbances

bserver Based Sliding Mode Attitude Control: Theoretical and Experimental Results

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