Predefined-Time Attitude Stabilization of Receiver Aircraft in Aerial Refueling

Wu, Cihang; Yan, Jianguo; Shen, Jing-Chung; Wu, Xiangqing; Xiao, Bing

doi:10.1109/tcsii.2021.3067695

Cited by 47 publications

(36 citation statements)

References 19 publications

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“…In order to demonstrate the effectiveness of the proposed fixed-time control scheme, numerical simulations are performed and presented in this section. The comparison with the finite-time control strategy can be observed in our previous work (Wu et al, 2021a). In this section, we mainly focus on the control performance of the adaptive control law and its implementation in the noisy environment.…”

Section: Validation Of the Fixed-time Controllermentioning

confidence: 97%

Predefined-time sliding manifold-based fixed-time attitude stabilization control of receiver aircraft with measurement noises

Yan

et al. 2022

Transactions of the Institute of Measurement and Control

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This paper investigates the challenging attitude stabilization control problem of receiver aircraft subject to uncertain and time-varying inertia, and wind disturbances in the aerial refueling task. An adaptive fixed-time control strategy is proposed. In this approach, a predefined-time sliding manifold is preliminarily developed. The main feature is that the settling time is not only independent of initial conditions but also can be simply and explicitly defined in advance through a single parameter in the sliding mode phase. On this basis, an adaptive control law is developed to guarantee that the trajectory of attitude can be stabilized into a small region containing the origin. The upper bound of unknown disturbance is not required to implement the proposed controller, which relaxes the restrictions of design for control systems. Moreover, the measuring noises are explicitly considered and addressed to make this approach still available in the noisy measurement environment. The Lyapunov stability analysis and numerical simulations verify the effectiveness of the proposed control strategy.

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Section: Validation Of the Fixed-time Controllermentioning

confidence: 97%

Predefined-time sliding manifold-based fixed-time attitude stabilization control of receiver aircraft with measurement noises

Yan

et al. 2022

Transactions of the Institute of Measurement and Control

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“…Compared with the time‐varying technique used in the works, 26‐28 the time‐varying function used in this article is

{C}^{\infty }

for

t\in \left(0,+\infty \right)

. The present control scheme can make the attitude tracking errors converge to a preset‐bounded region around zero in a preset time without dependence on initial conditions. In contrast to the preset‐time control law reported in the work, 19 the preset‐time stability in the sliding phase can be ensured as well. Compared with the preset‐time controllers presented in the works, 20‐22 the implementation of the control scheme derived here does not have any singularity problem.…”

Section: Introductionmentioning

confidence: 98%

“…An outstanding feature of the preset‐time control is that the settling time (or the upper limit of the settling time) can be prescribed by the controller designer a priori, independently of initial conditions and/or any other controller parameters. By virtue of the sliding mode control, preset‐time controllers have been designed for stabilization of robotic manipulators 19 and for the attitude control problem 20‐23 . However, the preset‐time stability cannot be ensured during the sliding phase in the work 19 as a linear sliding mode manifold is used, and there is a singularity problem in implementing the predefined‐time controllers presented in the works 20‐22 .…”

Section: Introductionmentioning

confidence: 99%

“…Because the electromagnetic docking system is a second‐order nonlinear system, the proposed approach might be applied to the spacecraft electromagnetic docking problem if the time‐varying delay and fault signals are not taken into account. The contributions of this article are: Different from the works, 19‐24 a smooth time‐varying scaling function is introduced in this article to derive the preset‐time control scheme. Compared with the time‐varying technique used in the works, 26‐28 the time‐varying function used in this article is

{C}^{\infty }

for

t\in \left(0,+\infty \right)

Section: Introductionmentioning

confidence: 99%

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Attitude tracking control of spacecraft with preset‐time preset‐bounded convergence

Zou

Liu

2022

Intl J Robust & Nonlinear

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This article addresses the issue of attitude tracking control of rigid spacecraft in the existence of bounded external disturbances. By introducing a smooth time-varying scaling function, a preset-time sliding mode surface is designed. Then, a nonsingular and continuous preset-time preset-bounded attitude tracking control scheme is developed. The distinctive feature of the present control law is that the size of the convergence region and the settling time can be prescribed a priori. In addition, the proposed control scheme exhibits superiority in reducing the magnitude of the applied control torques and saving energy.At last the feasibility of the derived control protocol is illustrated by numerical simulations including a comparative example.

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“…Lemma 1. [30,31] Suppose there is a radially unbounded Lyapunov function V : S → R + for (1) such that…”

Section: Introductionmentioning

confidence: 99%

Predefined-time anti-saturation fault-tolerant attitude control for tailless aircraft with guaranteed output constraints

et al. 2022

Nonlinear Dyn

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This work investigates the anti-saturation attitude tracking control for the tailless aircraft with guaranteed output constraints, in presence of uncertain inertia parameters, bounded external disturbance, and actuator faults/failures. A predefined-time adaptive backstepping attitude control scheme has been proposed, the main features of this scheme lie in (a) designing a predefined-time filter to deal with the 'explosion of complexity' and singularity problem; (b) introducing a nonlinear state-dependent function to handle the asymmetric time-varying output constraints; (c) compensating for the impact of the actuator faults/failures and input saturation by a nonlinear function and bounded estimation simultaneously. Moreover, the proposed control scheme can ensure all signals in the closed-loop system converge to a residual set around the origin within a predefined time, and this time constant can be set freely by the designer, independently of initial conditions. Article Finally, numerical simulations have been conducted to verify the performance of the proposed predefined-time fault-tolerant control scheme.

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Predefined-Time Attitude Stabilization of Receiver Aircraft in Aerial Refueling

Cited by 47 publications

References 19 publications

Predefined-time sliding manifold-based fixed-time attitude stabilization control of receiver aircraft with measurement noises

Predefined-time sliding manifold-based fixed-time attitude stabilization control of receiver aircraft with measurement noises

Attitude tracking control of spacecraft with preset‐time preset‐bounded convergence

Predefined-time anti-saturation fault-tolerant attitude control for tailless aircraft with guaranteed output constraints

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