Moon Tracking Attitude Control Experiment of a Bias Momentum Micro Satellite ".MU.-LabSat"

Terui, Fuyuto; Kimura, Shinichi; Nagai, Yasufumi; Yamamoto, Hiroshi; Yoshihara, Keisuke; Yamamoto, Toru; Nakasuka, Shinichi

doi:10.2322/tjsass.48.28

Cited by 5 publications

(14 citation statements)

References 6 publications

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“…Attitude kinematics Figure 2 shows the coordinate system for the camera. Although the line of sight of the camera was coincident with the direction opposite to the z-axis in the study by Terui et al, 30) for simplicity, it is assumed in this study that the line of sight of the camera is coincident with the z-axis of the body frame. Under this assumption, the unit vector corresponding to the image center in the body-fixed coordinate system, c, is given as c ¼ ½0; 0; 1 T .…”

Section: Equations Of Motionmentioning

confidence: 97%

“…Note that the time derivative of p given by Eq. (4) was not integrated to obtain the current value of p in the study by Terui et al 30)…”

Section: Equations Of Motionmentioning

confidence: 99%

“…In this section, a sliding mode controller for a bias-momentum satellite is derived by referring to Terui et al, 30) with several modifications to the equations of their study.…”

Section: Sliding Mode Control Via Two Wheelsmentioning

confidence: 99%

“…29) Terui et al reported the attitude maneuvering of a bias momentum satellite using two wheels and verified their control scheme using ®-LabSat in orbit. 30) As reported by Terui et al, 30) the control system of a satellite based on image processing contains a time delay, which deteriorates the control performance, and a long time delay could make the system unstable.…”

Section: Introductionmentioning

confidence: 97%

“…Numerical simulation will show that attitude stabilization can be achieved by the proposed adaptive time-delay esti-mated sliding mode control (ATDESMC), and that AT-DESMC is effective for attitude maneuvering, as compared to the sliding mode control described by Terui et al 30) The remainder of this paper is organized as follows. In Section 2, the equations of motion and problem statement are presented.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive Time-delay Estimated Sliding Mode Control for a Bias Momentum Satellite with Two Reaction Wheels

Kojima

Trivailo

2019

Trans. Japan Soc. Aero. S Sci.

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An adaptive sliding mode control to stabilize the attitude of a bias momentum satellite with a time delay via two wheels is proposed. Stabilizing the attitude of a rigid body via two control torques is an under-actuated control problem, and belongs to the class of systems that are controllable but cannot be asymptotically stabilized via continuous state feedback because Brockett's necessary condition is not satisfied. The adaptive method combined with the sliding mode control estimates the time delay contained in the system by sensing the difference between the attitude predicted and the measured one at each sampling time and compensates for the time delay by predicting the current state using the past measured attitude and angular velocity. Provided that external disturbances and modeling uncertainties in the satellite moments of inertia are absent, the validity of the proposed adaptive time delay estimated sliding mode control for attitude control of a bias momentum satellite is verified through numerical simulations.

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Section: Equations Of Motionmentioning

confidence: 97%

“…Note that the time derivative of p given by Eq. (4) was not integrated to obtain the current value of p in the study by Terui et al 30)…”

Section: Equations Of Motionmentioning

confidence: 99%

“…In this section, a sliding mode controller for a bias-momentum satellite is derived by referring to Terui et al, 30) with several modifications to the equations of their study.…”

Section: Sliding Mode Control Via Two Wheelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Adaptive Time-delay Estimated Sliding Mode Control for a Bias Momentum Satellite with Two Reaction Wheels

Kojima

Trivailo

2019

Trans. Japan Soc. Aero. S Sci.

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Inertial Morphing as a Novel Concept in Attitude Control and Design of Variable Agility Acrobatic Autonomous Spacecraft

Trivailo

Kojima²

2022

Nonlinear Approaches in Engineering Application

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Enhancement of the attitude dynamics capabilities of the spinning spacecraft using inertial morphing

Trivailo

Kojima

2019

Aeronaut. j.

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ABSTRACTIn the previous works by the authors, an efficient method of control of the inversion of the spinning spacecraft was proposed. This method was prompted by the Dzhanibekov’s Effect or Tennis Racket Theorem, which are often seen by many as odd or even mysterious. For the spacecraft, initially undergoing periodic flipping motion, proposed method allows to completely stop these flips by transferring the unstable motion into the regular stable spin. Similarly, the method allows activation of the flipping motion of the spacecraft, which is initially undergoing its stable spin. In this paper, spacecraft designs, which have inertial morphing capabilities, are considered and their advantages are further investigated. For general formulation, the ability of the spacecraft to change its inertial properties, associated with all three principal axes of inertia, are assumed. For simulation of these types of spacecraft systems, extended Euler’s equations are used and peculiar dynamics of the spacecraft is illustrated with a several study cases. Complex spacecraft attitude dynamics manoeuvres, using geometric interpretation, employing angular momentum spheres and kinetic energy ellipsoids, are considered in detail. Contributions of the inertial morphing to the changes of the shape of the kinetic energy ellipsoid are demonstrated and are related to the resultant various feature manoeuvres, including inversion and re-orientation. A method of reduction of the compound rotation of the spacecraft into a single stable predominant rotation around one of the body axes was proposed. This is achieved via multi-stage morphing and employing proposed instalment into separatrices. Implementation of the morphing control capabilities are discussed. For the periodic inversion motions, calculation of the periods of the flipping motion, based on the complete elliptic integral of the first kind, is performed. Flipping periods for various combinations of inertial properties of the spacecraft are presented in a systematic way. This paper discusses strategies to the increase or reduction the flipping and/or wobbling motions. A discovered asymmetric ridge of high periods for peculiar combinations of the inertial properties is discussed in detail. Numerous examples are illustrated with animations in virtual reality, facilitating explanation of the analysis and control methodologies to a wide audience, including specialists, industry and students.

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Moon Tracking Attitude Control Experiment of a Bias Momentum Micro Satellite ".MU.-LabSat"

Cited by 5 publications

References 6 publications

Adaptive Time-delay Estimated Sliding Mode Control for a Bias Momentum Satellite with Two Reaction Wheels

Adaptive Time-delay Estimated Sliding Mode Control for a Bias Momentum Satellite with Two Reaction Wheels

Inertial Morphing as a Novel Concept in Attitude Control and Design of Variable Agility Acrobatic Autonomous Spacecraft

Enhancement of the attitude dynamics capabilities of the spinning spacecraft using inertial morphing

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