Feedback Control for Slew Maneuver Using On-Off Thrusters

Bang, Hyochoong; Park, Young-Woong; Han, Jungyoup; Han, Hao

doi:10.2514/2.4483

Cited by 15 publications

(12 citation statements)

References 19 publications

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“…Before the principle control law of this study is designed, the application of typical closed-loop feedback control strategy is made [13]. This will provide a fundamental motivation for this study by disclosing the nature of the problem.…”

Section: Control System Designmentioning

confidence: 99%

Attitude manoeuvre and vibration control of flexible spacecraft using computed feed-forward input commands and proportional-derivative feedback

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

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The current paper presents an investigation into development of feed-forward and feedback control strategies for active vibration and attitude control of a flexible spacecraft. In this approach, the feed-forward loop consists of a computed-torque scheme and a command shaping technique based on component synthesis vibration suppression (CSVS) method for shaping the input signal. For relaxing the requirement of dynamic linearity in traditional CSVS, a new approach is developed for designing the input component command by utilizing a structure, in which the modal forces of flexible modes vibration are shaped according to a predefined trajectory, to achieve the vibration suppression for the non-linear attitude dynamics. In addition, to follow the predefined trajectory identically or at least as closely as possible, a model-independent feedback control loop is employed, which can accomplish further reduction of the residual vibration of flexible appendages. This proposed control strategy is practical as it does not require direct measurement of mode vibration, and also has a simple structure with low online computational load. Numerical simulations demonstrate the effectiveness of the control strategy.

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Section: Control System Designmentioning

confidence: 99%

Attitude manoeuvre and vibration control of flexible spacecraft using computed feed-forward input commands and proportional-derivative feedback

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…One intuitive approach to effectively eliminate the vibration is to seek a feedback system that, while providing the essential smooth controls, is primarily targeted to control the tip displacement of flexible spacecraft in a way that less vibration motion should be induced by the center torque input. Based on this idea, a modified PD (Junkins and Bang, 1991;Bang, et al, 1999) control can be obtained in which a smooth reference trajectory is generated a priori, and the corresponding stabilizing control law is designed so that the reference trajectory should be tracked by satisfying the tip displacement constrain equation. The required torque is calculated by regarding the flexible spacecraft as a rigid body, see (Junkins and Bang, 1991;Agrawal and Bang, 1995…”

Section: Pd Feedback Control With Smooth Trajectorymentioning

confidence: 99%

Feed-Forward/Feedback Control for Active Vibration Suppression of Flexible Spacecraft During Attitude Maneuver

Liu

2005

IFAC Proceedings Volumes

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This paper presents an investigation into development of feed-forward and feedback control strategies for active vibration suppression and attitude control of flexible spacecrafts. The feed-forward loop consists of a computed-torque scheme and a command shaping technique based on component synthesis vibration suppression (CSVS) method which was developed based on linear systems theory. For relaxing the requirements of dynamic linearity in traditional input component command in CSVS method, a new approach is developed for designing the input component command by utilizing a structure in which the modal forces of flexible modes vibration are shaped according to a predefined trajectory, which improves the performance of CSVS method in vibration suppression for the nonlinear attitude dynamics. This proposed control strategy is practical as it does not require direct measurement of flexible appendage vibration, and also has a simple structure with low on-line computational load. Numerical simulations demonstrate the effectiveness of the control strategy.

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“…The difference between the modes can be simply the status of some actuators which are 'on' in some modes and 'off' in some other modes [1][2][3][4][5][6][7], the environmental conditions and/or the vehicle configuration which are different in different modes [8], etc. In general, a switching system is composed of several modes (with different dynamics) which at each instant only one of them is active.…”

Section: Introductionmentioning

confidence: 99%

Optimal Orbit Transfer with ON-OFF Actuators Using a Closed Form Optimal Switching Scheme

Heydari

Balakrishnan

2013

AIAA Guidance, Navigation, and Control (GNC) Conference

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The problem of optimal trajectory planning and control for orbit transfer with on-off actuators is considered in this paper. The emphasis is on finding an approximate closedform solution for a range of initial conditions but with marginal number of online computations. In order to achieve this goal, the problem is initially formulated in a general form, that is, to find the optimal switching schedule between different modes in a switching system. Afterward, a simple scheme for solving the problem without enforcing a specific mode sequence or a number of switching is introduced. Two representative problems are presented wherein optimal path planning is achieved with on-off actuators for control. Numerical results and analysis demonstrate the potential of the developed method.

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Feedback Control for Slew Maneuver Using On-Off Thrusters

Cited by 15 publications

References 19 publications

Attitude manoeuvre and vibration control of flexible spacecraft using computed feed-forward input commands and proportional-derivative feedback

Attitude manoeuvre and vibration control of flexible spacecraft using computed feed-forward input commands and proportional-derivative feedback

Feed-Forward/Feedback Control for Active Vibration Suppression of Flexible Spacecraft During Attitude Maneuver

Optimal Orbit Transfer with ON-OFF Actuators Using a Closed Form Optimal Switching Scheme

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