Spacecraft attitude control and stabilization: Applications of geometric control theory to rigid body models

Crouch, P. E.

doi:10.1109/tac.1984.1103519

Cited by 395 publications

(189 citation statements)

References 10 publications

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“…More precisely, we analyze the controllability properties of the attitude dynamics of a spacecraft carrying an array of SGCMGs by treating the CMG gimbal rates as inputs. Attitude controllability under actuation by thrusters, reaction wheels or magnetic torquers has been studied previously [9], [10]. However, due to the presence of singular configurations, the problem of attitude controllability using CMGs as actuators is very different from the problem of attitude controllability using thrusters, reaction wheels or magnetic torquers as actuators.…”

Section: Introductionmentioning

confidence: 99%

Controllability of Spacecraft Attitude Using Control Moment Gyroscopes

Bhat

Tiwari

2009

IEEE Trans. Automat. Contr.

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Abstract-This paper describes an application of nonlinear controllability theory to the problem of spacecraft attitude control using control moment gyroscopes (CMGs). Nonlinear controllability theory is used to show that a spacecraft carrying one or more CMGs is controllable on every angular momentum level set in spite of the presence of singular CMG configurations, that is, given any two states having the same angular momentum, any one of them can be reached from the other using suitably chosen motions of the CMG gimbals. This result is used to obtain sufficient conditions on the momentum volume of the CMG array that guarantee the existence of gimbal motions which steer the spacecraft to a desired spin state or rest attitude.

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Section: Introductionmentioning

confidence: 99%

Controllability of Spacecraft Attitude Using Control Moment Gyroscopes

Bhat

Tiwari

2009

IEEE Trans. Automat. Contr.

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“…Although satellite systems are quipped with at least three pairs of control momentum wheels, malfunction may occur to some wheels. It has been proved in [7] that this system is uncontrollable. How to stabilize the satellite around a desired attitude is a challenging problem.…”

Section: Lwilcox@npsedumentioning

confidence: 99%

An example of solving HJB equations using sparse grid for feedback control

Kang

Wilcox

2015

2015 54th IEEE Conference on Decision and Control (CDC)

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Abstract-It is well known that solving the Hamilton-JacobiBellman (HJB) equation in moderate and high dimensions (d > 3) suffers the curse of dimensionality. In this paper, we introduce and demonstrate an example of solving the 6-D HJB equation for the optimal attitude control of a rigid body equipped with two pairs of momentum wheels. The system is uncontrollable. To mitigate the curse-of-dimensionality, a computational method based on sparse grids is introduced. The method is causality free, which enjoys the advantage of perfect parallelism. The problem is solved using several hundred CPU cores in parallel. In the simulations, the solution of the HJB equation is integrated into a model predictive control for optimal attitude stabilization.

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“…Задача об управлении движением шара с помощью двух роторов рассматривалась в работе [12]. Применение роторов для курсовой стабилиза-ции при движении в жидкости изучалось в [15,16,34], а при движении спутника -в [17].…”

Section: Introductionunclassified

Control of the motion of an unbalanced heavy ellipsoid in an ideal fluid using rotors

Vetchanin¹,

Kilin²

2016

Nelin. Dinam.

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Spacecraft attitude control and stabilization: Applications of geometric control theory to rigid body models

Cited by 395 publications

References 10 publications

Controllability of Spacecraft Attitude Using Control Moment Gyroscopes

Controllability of Spacecraft Attitude Using Control Moment Gyroscopes

An example of solving HJB equations using sparse grid for feedback control

Control of the motion of an unbalanced heavy ellipsoid in an ideal fluid using rotors

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