Global finite-time set stabilization of spacecraft attitude with disturbances using second-order sliding mode control

Zhou, Guo; Wang, Zuo; Li, Shihua

doi:10.1007/s11071-022-07245-5

Cited by 19 publications

(5 citation statements)

References 53 publications

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“…Lemma 1. Consider the following nonlinear system [24] ẋ = f (t, x), x(0) = x 0 (1) where x ∈ R n is the system state and f is a nonlinear function. Let there exist a continuous Lyapunov function V(x), such that…”

Section: Preliminariesmentioning

confidence: 99%

“…In order for spacecraft to successfully accomplish their missions, an attitude control system with high control performance is of paramount importance. Therefore, the problem of attitude control design has become one of the most important and broadly studied topics, and numerous control strategies have been employed to develop attitude controls for spacecraft, approaches such as sliding mode control [1], back-stepping control [2], passivity-based control [3], adaptive control [4], fuzzy control [5], neural networks control [6], and observer-based control [7], just to mention a few. Although these control results provide satisfactory performance, they are based on the assumption that full-state measurements are available to construct the controller.…”

Section: Introductionmentioning

confidence: 99%

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Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

et al. 2023

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This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted to convert an attitude system with immeasurable angular velocity into a new system. All states of the new converted system are measurable and available for feedback; however, the system contains mismatched uncertainty resulting from the coordinate transformation. Then, an adaptive nonsingular back-stepping control with practical predefined-time convergence is designed. To resolve the problem of input saturation, an anti-windup compensator is developed. It is analytically proved that the spacecraft attitude and angular velocity are practical predefined-time stable, such that the convergence time is a given tunable constant. The simulation results reveal that the proposed control framework provides rapid attitude maneuver and actuator saturation elimination.

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Section: Preliminariesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

et al. 2023

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“…However, the strict stability constraints add to the computational cost of the optimizer, limiting the range of applicability. In addition, sliding mode control also has an important role in spacecraft state tracking [30,31]. For traditional sliding mode control, the chattering phenomenon will occur when the state of the system is near the sliding mode surface, which will waste fuel and even pose significant risk to the spacecraft [32].…”

Section: Introductionmentioning

confidence: 99%

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Zhao,

Dai

2024

Nonlinear Dyn

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Detumbling is a crucial first step for on-orbit service and space debris removal. Recently, plume has become an efficient medium for detumbling failed spacecraft, which can avoid direct contact to improve operation safety. However, the traditional molecular plume may lead to an unaffordable fuel consumption, so it is necessary to propose a novel strategy to solve this problem. The Hall effect thruster is a common high specific impulse engine, which can generate high-speed plasma plume for contactless detumbling. The traditional plume models present difficulties for practical implementation due to the contradiction between the requirement of real-time computation and the limited computing capability of the spaceborne computer. To address the challenge of calculating the impact force, a fully analytical plasma plume model is proposed to substantially enhance the computing efficiency without loss of accuracy. A guidance law for optimal detumbling is proposed to mitigate the spin angular velocity while stabilizing nutation under multiple complex constraints. To facilitate the development of the detumbling control, a terminal non-singular sliding mode controller based on the saturation function (TSM-sat) is proposed, which can converge in finite time and avoid the chattering phenomenon. The Numerical results indicate that the proposed plasma plume model can significantly improve the computing efficiency and the optimal guidance law can stabilize the target within a reasonable time.

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“…The total uncertainty which is composed of the inertia matrix uncertainty and the space disturbance can significantly increase the attitude error and deteriorate the pointing accuracy. Despite the fact that linear controls such as PID control [5,6] have extensively been employed in spacecraft attitude control design, they are not able to provide specified performance due to the existence of the total uncertainty and nonlinearities in the spacecraft dynamics [7]. Therefore, nonlinear control strategies including variable structure control [8], backstepping control [9], feedback linearization [10], adaptive control [11], and learning-based control [12] have been developed.…”

Section: Introductionmentioning

confidence: 99%

Constrained Nonsingular Terminal Sliding Mode Attitude Control for Spacecraft: A Funnel Control Approach

2023

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This paper presents an adaptive constrained attitude control for uncertain spacecraft. Inspired by the concept of nonsingular terminal sliding mode control and funnel control for nonlinear systems, a novel adaptive attitude control is introduced which contains a time-varying gain to handle the constraints imposed on the spacecraft attitude. Indeed, when the attitude trajectory approaches the boundary of the constraint set, the control effort as well as the time-varying gain will increase in order to preclude the trajectory from intersecting the boundary. Then, it is analytically proved that the system trajectories converge to an arbitrary small region around the origin within a fixed time where the smallest upper bound of the convergence time is determined as an independent parameter in the controller. Further, the proposed control scheme is nonsingular without having to use any piecewise continuous function which simplifies stability analysis. These properties distinguish the proposed control scheme from the existing finite/fixed-time attitude controls. Finally, several simulation results confirm the robustness and performance of the proposed control framework.

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Global finite-time set stabilization of spacecraft attitude with disturbances using second-order sliding mode control

Cited by 19 publications

References 53 publications

Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Constrained Nonsingular Terminal Sliding Mode Attitude Control for Spacecraft: A Funnel Control Approach

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