Disturbance observer-based fault-tolerant attitude tracking control for rigid spacecraft with finite-time convergence

2017 ◽  
Vol 233 (2) ◽  
pp. 616-628 ◽  
Author(s):  
Qun Zong ◽  
Xiuyun Zhang ◽  
Shikai Shao ◽  
Bailing Tian ◽  
Wenjing Liu
Keyword(s):  
Finite Time ◽  
Tracking Control ◽  
Disturbance Observer ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Terminal Sliding Mode ◽  
Nonsingular Terminal Sliding Mode ◽  
Attitude Tracking ◽  
Rigid Spacecraft ◽  
Attitude Tracking Control

In this paper, finite-time fault-tolerant attitude tracking control is investigated for rigid spacecraft system with external disturbances, inertia uncertainties and actuator faults. A novel finite-time disturbance observer combined with a nonsingular terminal sliding mode controller is developed. Using an equivalent output error injection approach, a finite-time disturbance observer with simple structure is firstly designed to estimate lumped uncertainty. Then, to remove the requirement of prior knowledge about lumped uncertainty and reduce chattering, an adaptive finite-time disturbance observer is further proposed, and the estimations converge to the neighborhood of the true values. Based on the designed observer, a unified finite-time attitude controller is obtained automatically. Finally, both additive and multiplicative faults are considered for simulations and the results illustrate the great fault-tolerant capability of the proposed scheme.

Distributed Finite-Time Coordinated Attitude Tracking Control for Multiple Spacecraft with Actuator Saturation

2020 ◽  
Vol 29 (13) ◽  
pp. 2050212
Author(s):  
Zhi Gao ◽  
Zhihao Zhu ◽  
Yu Guo
Keyword(s):  
Finite Time ◽  
Tracking Control ◽  
Actuator Saturation ◽  
Sliding Mode ◽  
Terminal Sliding Mode ◽  
Mode Function ◽  
Nonsingular Terminal Sliding Mode ◽  
Attitude Tracking ◽  
Multiple Spacecraft ◽  
Attitude Tracking Control

For multi-spacecraft with actuator saturation, inertia uncertainties and external disturbances, a distributed finite-time coordinated attitude tracking control problem for the spacecraft with the communication topology containing fewer information paths is investigated. Aiming at reducing the communication path, a class of distributed finite-time state observers is designed. To speed up the convergence rate of the multiple spacecraft system, a fast nonsingular terminal sliding mode function is proposed. Moreover, an adaptive control term is proposed to suppress the impact of the external state-dependent disturbances and unknown time-varying inertia uncertainties. Further considering the actuator saturation owing to its physical limitations, a saturation function is designed. With the distributed finite-time observers, the fast nonsingular terminal sliding mode function, the adaptive update law and the saturation function, a distributed finite-time coordinated attitude tracking saturation controller is designed. Using the proposed controller, the follower can synchronize with the common leader with time-varying trajectory in finite time. Simulation results demonstrate the effectiveness of the designed controller.

Finite-time attitude tracking control of air bearing table for spacecraft rendezvous and docking

2016 ◽  
Vol 232 (1) ◽  
pp. 96-110 ◽  
Author(s):  
Cheng Huang ◽  
Yan Wang ◽  
Xing-lin Chen
Keyword(s):  
Finite Time ◽  
Tracking Control ◽  
Sliding Mode ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Finite Time Stability ◽  
Nonsingular Terminal Sliding Mode ◽  
Attitude Tracking ◽  
Attitude Tracking Control ◽  
Rendezvous And Docking

This paper studies the problem of attitude tracking control for spacecraft rendezvous and docking based on a physical ground simulation system. Two finite-time controllers based on quaternion are proposed by using a novel fast nonsingular terminal sliding mode surface associated with the adaptive control, the novel fast nonsingular terminal sliding mode surface not only contains the advantages of the fast nonsingular terminal sliding mode surface, but also can eliminate unwinding caused by the quaternion. The first controller, which is continuous and chattering-free, can compensate unknown constant external disturbances, while the second controller can both compensate parametric uncertainties and varying external disturbances with unknown bounds without chattering. Lyapunov theoretical analysis and simulation results show that the two controllers can make the closed-loop system errors converge to zero in finite time and guarantee the finite-time stability of the system.

Finite-time fault-tolerant attitude tracking control for spacecraft without unwinding

2018 ◽  
Vol 233 (6) ◽  
pp. 2119-2130 ◽  
Author(s):  
Bing Huang ◽  
Ai-jun Li ◽  
Yong Guo ◽  
Chang-qing Wang ◽  
Jin-hua Guo
Keyword(s):  
Finite Time ◽  
Tracking Control ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Attitude Tracking ◽  
Control Schemes ◽  
Fast Terminal Sliding Mode ◽  
Attitude Tracking Control

This paper investigates the finite-time attitude tracking control problem for spacecraft in the presence of external disturbances and actuator faults. Two anti-unwinding attitude tracking control schemes have been proposed based on the rotation matrix and sliding mode control technology. Utilizing a fast terminal sliding mode surface, the first controller can fulfill the finite-time attitude tracking control task with disturbance rejection ability. The second controller can improve the system reliability when the actuator fault occurs. Rigorous mathematical analysis and proof concludes that the proposed controllers can make a spacecraft track the desired attitude command in finite time. Numerical simulation results are presented to demonstrate the effectiveness of the proposed controllers.

Adaptive finite time attitude tracking control of a rigid spacecraft considering input magnitude and rate saturations

2021 ◽  
pp. 095441002110260
Author(s):  
Haitao Chen ◽  
Shenmin Song
Keyword(s):  
Finite Time ◽  
Tracking Control ◽  
Sliding Mode ◽  
Nonlinear Observer ◽  
Environmental Disturbance ◽  
Terminal Sliding Mode ◽  
First Order ◽  
Attitude Tracking ◽  
Rigid Spacecraft ◽  
Attitude Tracking Control

This article investigates the attitude tracking control problem of a rigid spacecraft under the modeling inaccuracy, environmental disturbance, and input magnitude and rate saturations. A robust controller is proposed based on several nonlinear control methods, including the integral terminal sliding mode control, adaptive control, backstepping control, auxiliary system, and nonlinear observer methods. Within the control framework, a new integral terminal sliding mode surface (ITSMS) is first designed which integrates the fast nonsingular terminal sliding mode surface (FNTSMS) with a first-order filter to achieve the finite time stability without the input singularity problem. And adaptive laws are employed to compensate for the modeling inaccuracy and environmental disturbance with no prior knowledge. To satisfy the input magnitude and rate saturation constraints, a dynamic model in the form of a first-order filter is built up to restrict the dynamics of the actuators, which is then associated with the auxiliary system. Meanwhile, a nonlinear observer is used to avoid calculating the derivative of the expected virtual control signal. Semi-globally uniformly ultimate bounded stability is proved for the closed-loop system, and the tracking errors can converge to small regions around the expected equilibrium in finite time. Finally, numerical simulation results are presented to demonstrate the effectiveness of the proposed controller.

A New Nonsingular Terminal Sliding Mode Control for Rigid Spacecraft Attitude Tracking

2017 ◽  
Vol 140 (5) ◽  
Author(s):  
Zeng Wang ◽  
Yuxin Su ◽  
Liyin Zhang
Keyword(s):  
Equilibrium Point ◽  
Finite Time ◽  
Sliding Mode ◽  
Tracking Errors ◽  
Robust Controller ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Nonsingular Terminal Sliding Mode ◽  
Attitude Tracking ◽  
Rigid Spacecraft

This paper addresses the finite time attitude tracking for rigid spacecraft with inertia uncertainties and external disturbances. First, a new nonsingular terminal sliding mode (NTSM) surface is proposed for singularity elimination. Second, a robust controller based on NTSM is designed to solve the attitude tracking problem. It is proved that the new NTSM can converge to zero within finite time, and the attitude tracking errors converge to an arbitrary small bound centered on equilibrium point within finite time and then go to equilibrium point asymptotically. The appealing features of the proposed control are fast convergence, high precision, strong robustness, and easy implementation. Simulations verify the effectiveness of the proposed approach.

scholarly journals Barrier Function-Based Adaptive Integral Sliding Mode Finite-time Attitude Control for Rigid Spacecraft

2021 ◽  
Author(s):  
Jie Wang ◽  
YuShang Hu ◽  
Wenqiang Ji
Keyword(s):  
Finite Time ◽  
Barrier Function ◽  
Attitude Control ◽  
Tracking Control ◽  
Sliding Mode ◽  
Initial Moment ◽  
Integral Sliding Mode ◽  
Attitude Tracking ◽  
Rigid Spacecraft ◽  
Attitude Tracking Control

Abstract This paper investigates the problem of the finite-time attitude tracking control for rigid spacecrafts with external disturbances and inertia uncertainties. Firstly, a finite-time approach is designed to achieve attitude tracking control of the rigid spacecraft in absence of disturbances and inertia uncertainties and the time of convergence can be chosen in advance. Then, the integral sliding mode combined with barrier function-based adaptive laws is proposed to reject the disturbances and inertia uncertainties, and at the same time, a barrier function-based adaptive method can also ensure the solutions of the rigid spacecraft system belonging to a stipulated vicinity of the intended variables starting from the initial moment and the uncertainties' upper bound is not overestimated. Finally, numerical simulation is provided to illustrate the efficiency of the proposed control protocol.

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