Time-Optimal De-tumbling Control of a Rigid Spacecraft

Chao, Yang; Wu, Chia‐Ju

doi:10.1177/1077546307080034

Cited by 8 publications

(3 citation statements)

References 20 publications

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“…Yet some significant advances have been made in the early part of this century. This includes papers by Lee et al [1], Yoshida et al [2], Aghili [3,4], Yang and Wu [5], Liu et al [6], and Zhang et al [7], who have considered the maneuvering for attitude or angular rate acquisition problems using classical methodologies. Sharma and Tewari [8] have addressed the issue of nonlinear tracking of spacecraft attitude manoeuvers while Hegrenas et al [9] have considered the maneuvering for attitude or angular rate acquisition problem by means of explicit model predictive control, via a nonlinear programming approach.…”

Section: Introductionmentioning

confidence: 99%

Optimal Trajectory Synthesis and Tracking Control for Spacecraft Large Attitude Manoeuvers

Vepa¹

2020

Advances in Spacecraft Attitude Control

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The classical approach to the problem of synthesizing an optimal attitude manoeuver trajectory, involves the use of the calculus of variations and the use Lagrange multipliers or co-states. The nonlinear large attitude manoeuver trajectory is controlled by a set of nonlinear evolving co-states. In this paper, following a review of the methodologies available for trajectory synthesis followed by tracking control, the optimal trajectory for a typical optimal attitude manoeuver is synthesized by solving for the states and co-states defined by a two point boundary value problem. Gravity gradient torques are included as a matter of course. Following the synthesis of the optimal attitude-rate trajectory, tracking control laws are synthesized by re-formulating the optimal control as a feedback law. The approximate linear tracking feedback controls are evaluated by relating the optimal state and costate vector by a linear relation. The control laws are synthesized numerically. The problem of optimal attitude orientation trajectory synthesis is also addressed. The methodologies are applied to typical sample problems and results are presented. Quantitative comparisons of the results of the methods are made to the results obtained by the application of other linear and nonlinear methods, to illustrate the key features of the methodologies.

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Section: Introductionmentioning

confidence: 99%

Optimal Trajectory Synthesis and Tracking Control for Spacecraft Large Attitude Manoeuvers

Vepa¹

2020

Advances in Spacecraft Attitude Control

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“…There appear to be three main areas where the dynamics of tumbling and its control have been studied: 1) control of the orientation of a rigid body using the motion of internal parts [1][2][3][4][5], the study of tumbling dynamics of biological species and their internal control mechanisms through limbs or tails [6,7], and applications in bioinspired robots [8][9][10]; 2) work on attitude dynamics in the aerospace field (e.g., [11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26][27][28][29][30]); and 3) tumbling of biological species such as proteins, red blood cells, and flying insects (e.g., [31][32][33][34]). More recently, there has been activity in the capture of tumbling objects in space in which, for example, the use of optimal control methods for attitude orientation to capture tumbling objects was worked on [35].…”

Section: Introductionmentioning

confidence: 99%

Dynamics and Precision Control of Tumbling Multibody Systems

Koganti

Udwadia

2017

Journal of Guidance, Control, and Dynamics

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Tumbling is an inherently nonlinear phenomenon, and this paper uses a generic model of a tumbling multibody system made up of a rigid body to which discrete masses are attached; it obtains the equations of motion of the system explicitly, exhibiting the highly nonlinear nature of the dynamics. Particularizations of the generic model used here are useful in applications such as liquid sloshing in rockets, biodynamics, and capture and refurbishing of space debris. It is assumed that the mathematical description of the system is accurately known. A uniform analytical dynamics-based approach is used to obtain both the equations of motion of the system as well as the requisite control torques and forces to satisfy control requirements. No linearizations or approximations of the nonlinear dynamics are made, and closed-form controls are obtained that precisely track user-specified time-dependent control requirements on the tumbling multibody system. The methodology is demonstrated using two examples of tumbling systems with internal degrees of freedom in a constant gravity field that possess significant nonlinear internal motions. Precision tumbling control of such tumbling-vibrating multibody systems is achieved with considerable ease, making the approach presented herein useful for real-time control.

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“…On the other hand for the purpose of comparison, for fully actuated spacecraft, aiming at minimizing the detumbling maneuver time, several studies developed control solutions for the time-optimal detumbling maneuvers. Yang and Wu solved the timeoptimal control problem using an iterative procedure for solving the non-linear programming problem [72]. Romano derived an analytic solution for detumbling and nutation cancellation maneuvers for axisymmetric spacecraft [73].…”

Section: Detumbling Maneuversmentioning

confidence: 99%

Algorithms and Optimal Control for Spacecraft Magnetic Attitude Maneuvers

Desouky¹

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Time-Optimal De-tumbling Control of a Rigid Spacecraft

Cited by 8 publications

References 20 publications

Optimal Trajectory Synthesis and Tracking Control for Spacecraft Large Attitude Manoeuvers

Optimal Trajectory Synthesis and Tracking Control for Spacecraft Large Attitude Manoeuvers

Dynamics and Precision Control of Tumbling Multibody Systems

Algorithms and Optimal Control for Spacecraft Magnetic Attitude Maneuvers

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