Robust output feedback attitude tracking control for rigid-flexible coupling spacecraft

Ye, Dong; Xiao, Yan

doi:10.1016/j.jfranklin.2017.02.031

Cited by 19 publications

(16 citation statements)

References 27 publications

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“…Therefore, the dynamics of the homogeneous transformation matrix in (21) can be mapped to vector form in the sense of Rodriguez parameters from (32) and (8) as…”

Section: Be a Measured Vector In The Body-frame Such That The Ith Bodmentioning

confidence: 99%

“…The performance of the proposed stochastic filter is compared to [17]. Let us define the dynamics of the homogeneous transformation matrix T as in (21). Let the angular velocity input signal be   (m/sec) and the initial position P (0) = 0 3 .…”

Section: Simulationsmentioning

confidence: 99%

“…Moreover, pose estimators such as [14,15,16,17,18] disregard the noise in the filter design assuming only constant bias introduced in the measuring process. Therefore, successful spacecraft control applications, such as, [21,22,23] cannot be achieved without pose filters robust against uncertain measurements.…”

Section: Introductionmentioning

confidence: 99%

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Nonlinear stochastic position and attitude filter on the Special Euclidean Group 3

Hashim

Brown

McIsaac

2019

Journal of the Franklin Institute

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This paper formulates the pose (attitude and position) estimation problem as nonlinear stochastic filter kinematics evolved directly on the Special Euclidean Group SE (3). This work proposes an alternate way of potential function selection and handles the problem as a stochastic filtering problem. The problem is mapped from SE (3) to vector form, using the Rodriguez vector and the position vector, and then followed by the definition of the pose problem in the sense of Stratonovich. The proposed filter guarantees that the errors present in position and Rodriguez vector estimates are semi-globally uniformly ultimately bounded (SGUUB) in mean square, and that they converge to small neighborhood of the origin in probability. Simulation results show the robustness and effectiveness of the proposed filter in presence of high levels of noise and bias associated with the velocity vector as well as body-frame measurements.

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“…Therefore, the dynamics of the homogeneous transformation matrix in (21) can be mapped to vector form in the sense of Rodriguez parameters from (32) and (8) as…”

Section: Be a Measured Vector In The Body-frame Such That The Ith Bodmentioning

confidence: 99%

Section: Simulationsmentioning

confidence: 99%

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Nonlinear stochastic position and attitude filter on the Special Euclidean Group 3

Hashim

Brown

McIsaac

2019

Journal of the Franklin Institute

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“…The development of feedforward and feedback control strategies for active vibration suppression and attitude control of a flexible spacecraft using modified component synthesis vibration suppression (CSVS) method has been proposed by Hu et al [5]. A robust output feedback controller to solve the attitude tracking control problem of a flexible spacecraft in the presence of disturbances is considered by Ye and Xiao [6]. Liu et al [7] have presented an improved mixed H 2 /H ∞ control technique combined with pole assignment theory to achieve attitude stabilization and vibration suppression, simultaneously, for a flexible spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Fast Attitude Maneuver of a Flexible Spacecraft with Passive Vibration Control Using Shunted Piezoelectric Transducers

Albassam

2019

International Journal of Aerospace Engineering

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This paper is concerned with designing a bang-bang control input to perform a quick rotational maneuver of a rigid spacecraft hub connected with flexible appendages. The control design is based on only the rigid body mode making it very simple to design and at the same time achieve the quickest maneuver possible. The induced vibrations are suppressed using piezoelectric transducers bonded to the appendages and connected to an electric circuit with the objective of converting the vibrational energy to electrical energy and then dissipating it using passive electric elements, such as a resistance and an inductor. The proposed control design method is applied to a spacecraft containing a rigid hub and flexible appendages. The attitude control torque is produced using either the reaction wheels contained inside the rigid hub or jet thrusters mounted outside it. The control design process starts with deriving the nonlinear partial differential equations of motion for the spacecraft using Hamilton’s principle which accounts for the electromechanical coupling and the presence of resistive or resistive-inductive circuits. To simplify the analysis, the nonlinear ordinary differential equations of motion are then obtained using the assumed mode method. The effectiveness of the control design method is numerically tested on a spacecraft that is required to perform a quick attitude maneuver and, simultaneously, suppress the induced vibrations. The simulations show a quick and accurate maneuver has been achieved combined with very low levels of vibrations resulting from the reduced coupling between flexible and rigid motions as well as the damping added as a result of the passive shunt circuit. Furthermore, the resistance-inductance shunt circuit is shown to be more effective in damping the vibrations than the resistance shunt circuit.

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“…Hu has studied many novel control approaches for attitude tracking of a flexible spacecraft subject to different constraints [17,[23][24][25]. A novel fault tolerant attitude tracking control scheme, to perform attitude tracking in presence of actuator effectiveness fault, is investigated in [17].…”

Section: Introductionmentioning

confidence: 99%

Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft

Chu

Ma³

et al. 2018

Acta Astronautica

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This paper investigates the multi-objective attitude tracking problem of a flexible spacecraft in the presence of disturbances, parameter uncertainties and imprecise collocation of sensors and actuators. An integrated robust H∞ controller, including an output feedback component and a feedforward component, is proposed, and its gains are calculated by solving Linear Matrix Inequalities. The output feedback component stabilizes the integrated control system while the feedforward component can drive the attitude motion to track the desired angles. The system robustness against disturbances, parameter uncertainties and imprecise collocation is addressed by the H∞ approach and convex optimization. Numerical simulations are finally provided to assess the performance of the proposed controller.

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Robust output feedback attitude tracking control for rigid-flexible coupling spacecraft

Cited by 19 publications

References 27 publications

Nonlinear stochastic position and attitude filter on the Special Euclidean Group 3

Nonlinear stochastic position and attitude filter on the Special Euclidean Group 3

Fast Attitude Maneuver of a Flexible Spacecraft with Passive Vibration Control Using Shunted Piezoelectric Transducers

Multi-objective integrated robust H∞ control for attitude tracking of a flexible spacecraft

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