Adaptive Fuzzy PD+ Control for Attitude Maneuver of Rigid Spacecraft

Chen, Zhen; Li, Zhong; Liu, Xiangdong; Cong, Beihua

doi:10.1002/asjc.1116

Cited by 11 publications

(17 citation statements)

References 27 publications

(63 reference statements)

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“…In Figs 1 and 4, all the states are staying at the equilibrium state without more transient process, however Figs 7,11,18 show that the states will pass though the equilibrium. Two reasons can be given to explain this point of difference between controller (11) [14] and the proposed controller (23).…”

Section: Remark 15mentioning

confidence: 94%

“…functions in controller (11) [14] and apply similar constraint on control input for both the controllers under consideration. Certainly, reduced steady state precision can be seen for controller (11) [14].…”

Section: Remark 15mentioning

confidence: 99%

“…The ACS efficacy is measured on robustness against uncertainty, convergence speed, pointing accuracy, and steady state precision. To ensure the efficacy, different control methods like optimal control , adaptive control , PD control, sliding mode control , terminal sliding mode control (TSM) , and fuzzy control have been extensively explored by researchers.…”

Section: Introductionmentioning

confidence: 99%

“…Control input when controller(11)[14] is applied for initial condition of Case 1. [Color figure can be viewed at wileyonlinelibrary.com] Sliding surface s = + kq v response when controller (11)[14] is applied for initial condition of Case 1.…”

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confidence: 99%

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Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

Tiwari

Janardhanan

un-Nabi

2017

Asian Journal of Control

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This paper presents an anti-unwinding control method for the attitude stabilization of a rigid spacecraft. Quaternion has double stable equilibrium and this may cause unwinding problems in spacecraft attitude control if both the equilibria are not considered in control design. Here, the initial condition of scalar quaternion is included in sliding surface and an anti-unwinding control method is formulated in second-order sliding mode. The presented second-order sliding mode controller can alleviate chattering and ensure a smooth control for actuator. Further, to eliminate the need of advance information about bounds of uncertainty and external disturbance, adaptive laws are applied to estimate the controller gains. The closed-loop stability is proved using the Lyapunov stability theory. In conclusion, a simulation is conducted in the presence of inertia uncertainty and external disturbances and it is found that the presented control method is efficient to negate the effect of inertia uncertainty and external disturbances, alleviate chattering, eliminate unwinding, and ensure high accuracy and steady state precision. P. M. Tiwari received his M.Tech and PhD in Control Engineering from Aligarh Muslim University Aligarh and Indian Institute of Technology Delhi in 2005 and 2016, respectively. Currently, he is a faculty with the Department of Electrical Engineering, Amity University Uttar Pradesh Noida. His research interests include sliding mode control, adaptive control, attitude control, and process control. S. Janardhanan received his M.Tech and PhD in Systems and Control Engineering from Indian Institute of Technology Bombay in 2002 and 2006, respectively. Currently, he is a faculty with the Department of Electrical Engineering, Indian Institute of Technology Delhi. He has over 100 publications in journals and conferences of international repute to his credit. His research interests include discrete-time systems, model order reduction, sliding mode control and robotics. M. Un-Nabi received his M.Tech and PhD in Control Engineering from Indian Institute of Technology Kanpur and Indian Institute of Technology Mumbai in 2003 and 2005, respectively. Currently, he is a faculty with the Department of Electrical Engineering, Indian Institute of Technology Delhi. He has around 60 publications in journals and conferences of international repute to his credit. His research interests include model order reduction, guidance and control, and sliding mode control.

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Section: Remark 15mentioning

confidence: 94%

Section: Remark 15mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

Tiwari

Janardhanan

un-Nabi

2017

Asian Journal of Control

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“…e results showed that the adaptive fuzzy PID controller was significantly more efficient than the conventional PID. Chen et al [50] proposed an adaptive fuzzy PD + controller for the attitude manoeuvre of a rigid spacecraft. Chak et al [51] discussed a new composite control scheme combining disturbance observer-based control and fuzzy PD control for flexible spacecraft attitude control in the presence of external and internal disturbances caused by flexible appendages.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

et al. 2020

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Modern spacecraft are often equipped with large-scale, complex, and lightweight solar arrays whose deployment involves a highly dynamic movement. This paper proposed a novel adaptive proportional-derivative typed fuzzy logic control scheme for the attitude stabilization of a flexible spacecraft during the deployment of a composite laminated solar array. First, a constrained rigid-flexible coupling spacecraft model consisting of a rigid main body and a flexible solar array was proposed. The solar array, which is composed of composite laminated shells, was described by the absolute nodal coordinate formulation. Then, the detailed derivation of the adaptive fuzzy PD controller for attitude stabilization of the spacecraft was discussed. In addition, the spacecraft dynamic model which integrated the adaptive fuzzy PD controller was derived as a set of differential-algebraic equations. Several simulations were developed to investigate the solar array deployment dynamics and to verify the effectiveness of the proposed adaptive fuzzy PD controller. The results suggested that the proposed dynamic model is able to exactly describe the deployment dynamics of the composite laminated solar array. The solar array deployment causes obvious translational and rotational motions of the spacecraft. The proposed adaptive fuzzy PD control scheme has better performance in terms of the control precision and time response in stabilizing spacecraft during the deployment of the composite laminated solar array, comparing with that of the conventional PD controller.

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Vector‐Based Adaptive Attitude Observer and Controller on Special Orthogonal Group

Jia

Matsuno

2016

Asian Journal of Control

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An adaptive attitude observer-controller scheme is proposed for attitude tracking of a rigid body. In the derived observer, the vector measurements are directly utilized to estimate gyro bias, and thus estimates of gyro bias are obtained independent to attitude estimates. The proposed observer is even robust towards fluctuation of gyro bias. Then an adaptive controller is proposed on the Special Orthogonal Group to track the reference trajectory subject to uncertain inertia parameters. This controller belongs to the non-certainty-equivalent framework, and the vector signals are also utilized into estimation of inertia parameters. It is ensured that the estimates of inertia parameters can converge towards real values to some degrees. Simulation results compared with previous observer and controller schemes verify the effectiveness of the proposed scheme.

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Adaptive Fuzzy PD+ Control for Attitude Maneuver of Rigid Spacecraft

Cited by 11 publications

References 27 publications

Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

Spacecraft Anti‐Unwinding Attitude Control Using Second‐Order Sliding Mode

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

Vector‐Based Adaptive Attitude Observer and Controller on Special Orthogonal Group

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