Simple model-free attitude control design for flexible spacecraft with prescribed performance

Zhang, Chao; Ma, Guangfu; Sun, Yanchao; Li, Chuanjiang

doi:10.1177/0954410018786085

Cited by 14 publications

(11 citation statements)

References 27 publications

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“…This is why the second term of ( 38) is positive definite. Moreover, the positive definiteness of the first quadratic term in (38) depends upon the square matrix Q(q). The principal minor values of Q(q) are P 1 = q 0 , P 2 = q 2 0 + q 2 3 , and P 3 = 0.5q 0 .…”

Section: Stability Analysismentioning

confidence: 99%

“…This method has the attributes of achieving the pre-established desired rate of convergence, overshoot, and steady-state accuracy by transforming the system state into a new error variable using the prescribed performance function (PPF). Owing to the advantages PPC method, the control researchers have also explored this technique for spacecraft problems in [37][38][39][40], and references therein. However, the control schemes in these papers are developed within the framework of a continuous-time update.…”

Section: Introductionmentioning

confidence: 99%

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Prescribed Performance-Based Event-Driven Fault-Tolerant Robust Attitude Control of Spacecraft under Restricted Communication

et al. 2021

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This paper explores the problem of attitude stabilization of spacecraft under multiple uncertainties and constrained bandwidth resources. The proposed control law is designed by combining the sliding mode control (SMC) technique with a prescribed performance control (PPC) method. Further, the control input signal is executed in an aperiodic time framework using the event-trigger (ET) mechanism to minimize the control data transfer through a constrained wireless network. The SMC provides robustness against inertial uncertainties, disturbances, and actuator faults, whereas the PPC strategy aims to achieve a predefined system performance. The PPC technique is developed by transforming the system attitude into a new variable using the prescribed performance function, which acts as a predefined constraint for transient and steady-state responses. In addition, the ET mechanism updates the input value to the actuator only when there is a violation of the triggering rule; otherwise, the actuator output remains at a fixed value. Moreover, the proposed triggering rule is constituted through the Lyapunov stability analysis. Thus, the proposed approach can be extended to a broader class of complex nonlinear systems. The theoretical analyses prove the uniformly ultimately bounded stability of the closed-loop system and the non-existence of the Zeno behavior. The effectiveness of the proposed methodology is also presented along with the comparative studies through simulation results.

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Section: Stability Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Prescribed Performance-Based Event-Driven Fault-Tolerant Robust Attitude Control of Spacecraft under Restricted Communication

et al. 2021

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“…A model-free attitude control approach for flexible spacecraft with prescribed performance has been designed in Ref. 28.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional prescribed performance sliding mode guidance law for intercepting maneuvering target

Tan

Song

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article describes three-dimensional sliding mode guidance laws with prescribed performance. The proposed guidance laws can ensure that the line of sight (LOS) angle converges according to the prescribed performance, and the convergence rate, the steady-state error and the maximum overshoot can be preset in advance. By combining the LOS tracking error with the performance constraint function, a new error variable function is designed, and then the prescribed performance control problem is transformed into that of the boundedness of the error variable function. The key concept in this approach is to design a new sliding mode surface to ensure that the error variable function is bounded, so as to ensure that the system state converges according to the prescribed performance. Additionally, this article discusses the problem whereby the upper bound of the aggregate uncertainty, including the target information, is unavailable. An adaptive guidance law is presented for this scenario. Finally, simulations comparisons are conducted with other forms of guidance laws. Simulation results show that the guidance laws proposed in this article achieve effective performance.

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“…These methods are deemed inapplicable to missions with complex dynamics or uncertain inertias. To promote, a great number of modified control methods, including sliding mode control (SMC) [6,26], feedback control [27,28], and backstepping control [7,29], have been developed. Among these methods, the SMC enjoys the superiority of high robustness against uncertainty and external disturbance in a complex nonlinear system.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Finite-Time Control on SE(3) for Spacecraft Final Proximity Maneuvers with Input Quantization

Zhang

Yang

2021

International Journal of Aerospace Engineering

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In this paper, a bounded finite-time control strategy is developed for the final proximity maneuver of spacecraft rendezvous and docking exposed to external disturbance and input quantization. To realize the integrated control for spacecraft final proximity operation, the coupling kinematics and dynamics of attitude and position are modeled by feat of Lie group SE 3 . With a view to improving the convergence rate and reducing the chattering, an adaptive finite-time controller is proposed for the error tracking system with one-step theoretical proof of stability. Meanwhile, the hysteresis logarithmic quantizer is implemented to effectively reduce the frequency of data transmission and the quantization errors are reduced under the proposed controller. The algorithms outlined above are based on an integrated model expressed by SE 3 and denoted by uniform motion states, which can simplify the design progress and improve control precision. Finally, simulations are provided to exhibit the effectiveness and advantages of the designed strategy.

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Simple model-free attitude control design for flexible spacecraft with prescribed performance

Cited by 14 publications

References 27 publications

Prescribed Performance-Based Event-Driven Fault-Tolerant Robust Attitude Control of Spacecraft under Restricted Communication

Prescribed Performance-Based Event-Driven Fault-Tolerant Robust Attitude Control of Spacecraft under Restricted Communication

Three-dimensional prescribed performance sliding mode guidance law for intercepting maneuvering target

Adaptive Finite-Time Control on SE(3) for Spacecraft Final Proximity Maneuvers with Input Quantization

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