Fast fixed‐time attitude tracking control of spacecraft with prescribed performance

Zhang, Haichao; Chen, Zhaoyue; Xiao, Bing; Li, Bo

doi:10.1002/rnc.6638

Cited by 10 publications

(2 citation statements)

References 43 publications

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“…Due to the fact that many actual mechanical systems, including robot manipulator systems [32], unmanned aerial vehicles [33,34], and spacecraft attitude control systems [35,36], are typically described by the Lagrangian dynamic equations of motion, the study objective of this section is to develop a standard predefined-time controller design method for the Lagrangian system considering external disturbances. The associated mathematical model is given as follows:…”

Section: Standard Predefined-time Controller Designmentioning

confidence: 99%

Unified Sufficient Conditions for Predefined-Time Stability of Non-Linear Systems and Its Standard Controller Design

Xiao,

Zhang,

Zhao

et al. 2024

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This paper presents a unified Lyapunov-based predefined-time stability theorem that includes three sufficient conditions. The standard theoretical analysis method for achieving predefined-time stability of non-linear systems using this theorem is provided within the framework of Lyapunov theory. The developed Lyapunov-based theorem facilitates the establishment of equivalence between the existing Lyapunov theorems concerning predefined-time stability. Furthermore, when the presented sufficient conditions are relaxed, the predefined-time stability conclusion for non-linear systems degenerates into a finite-time one. Consequently, a standard non-singular sliding mode control framework based on the unified Lyapunov-based theorem is developed for a Lagrangian system to ensure its predefined-time stability. Exemplary numerical simulation results are subsequently given, in order to illustrate the convergence behavior of the system states and confirm that the controlled systems are predefined-time stable.

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Section: Standard Predefined-time Controller Designmentioning

confidence: 99%

Unified Sufficient Conditions for Predefined-Time Stability of Non-Linear Systems and Its Standard Controller Design

Xiao,

Zhang,

Zhao

et al. 2024

Actuators

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“…Most existing studies 14‐20 employ exponential and hyperbolic cotangent performance functions, which cannot guarantee state convergence time. The finite‐time convergence performance functions are studied in References 21 and 22, which can give the upper bound on the state convergence time. However, the state convergence performance of the above research is difficult to adjust freely, which is not conducive to matching the performance requirements in various scenarios.…”

Section: Introductionmentioning

confidence: 99%

Performance‐adjustable PPC policies for spacecraft attitude‐orbit coupled tracking under event‐triggered sampling

Niu,

Dai,

Gao

et al. 2023

Intl J Robust & Nonlinear

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This paper investigates a performance‐adjustable prescribed performance control (PPC) policy under event‐triggered sampling for spacecraft attitude‐orbit coupled tracking with consideration of limited communications and performance constraints. Firstly, a logarithmic barrier Lyapunov function is introduced to derive the attitude‐orbit coupled tracking controller with guaranteed transient and steady‐state behaviors by applying the PPC algorithm. Then, to reduce the burden of the signal transmission under limited communications, the event‐triggered mechanism is applied to determine when the above attitude‐orbit coupled tracking controller updates. Furthermore, an indirect adaptive method with less computation that does not involve complex regression matrices or neural networks is designed to resist external disturbances. Compared with the traditional spacecraft control policies, the proposed strategy fully considers the state convergence performance, sampling performance, and calculation performance. The proposed one here can arbitrarily adjust the sampling performance and state convergence performance in an excellent trade‐off. Finally, a group of illustrative examples is organized to demonstrate the effectiveness of the proposed control policy.

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Anti‐unwinding attitude maneuver control with predefined time for rigid spacecraft with input saturation

Xu,

Wu,

Dong

2024

Intl J Robust & Nonlinear

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In this article, anti‐unwinding sliding mode attitude maneuver control with predefined time is investigated for rigid spacecraft with input saturation. First, a nonsingular sliding function containing two equilibrium points is designed to ensure the predefined‐time convergence of system states and unwinding‐free performance of the closed‐loop system on the sliding phase. Then, an auxiliary system with a dynamic parameter is presented to compensate the impact of input saturation. With this parameter, the auxiliary system can handle input saturation that occurs. Based on the sliding function and the auxiliary system, an attitude maneuver controller is developed to guarantee the robustness of the closed‐loop system to bounded external disturbance. Under the designed controller, the states of the closed‐loop system are driven into a neighborhood of the sliding surface within a predefined time. Moreover, the unwinding phenomenon is also avoided on the reaching phase. Numerical simulation results illustrate the unwinding‐free performance and predefined‐time convergence of the closed‐loop system under the proposed control strategy.

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Fast fixed‐time attitude tracking control of spacecraft with prescribed performance

Cited by 10 publications

References 43 publications

Unified Sufficient Conditions for Predefined-Time Stability of Non-Linear Systems and Its Standard Controller Design

Unified Sufficient Conditions for Predefined-Time Stability of Non-Linear Systems and Its Standard Controller Design

Performance‐adjustable PPC policies for spacecraft attitude‐orbit coupled tracking under event‐triggered sampling

Anti‐unwinding attitude maneuver control with predefined time for rigid spacecraft with input saturation

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