scholarly journals Reaction Wheel Installation Deviation Compensation for Overactuated Spacecraft with Finite-Time Attitude Control

2013 ◽  
Vol 2013 ◽  
pp. 1-10 ◽  
Author(s):  
Aihua Zhang ◽  
Jianfei Ni ◽  
Hamid Reza Karimi
Keyword(s):  
Finite Time ◽  
Attitude Control ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Technique ◽  
Adaptive Sliding Mode Control ◽  
Reaction Wheel ◽  
Compensation Control ◽  
Attitude Tracking ◽  
Attitude Tracking Control

A novel attitude tracking control scheme is presented for overactuated spacecraft to address the attitude stabilization problem in presence of reaction wheel installation deviation, external disturbance and uncertain mass of moment inertia. An adaptive sliding mode control technique is proposed to track the uncertainty. A Lyapunov-based analysis shows that the compensation control law can guarantee that the desired attitude trajectories are followed in finite-time. The key feature of the proposed control strategy is that it globally asymptotically stabilizes the system, even in the presence of reaction wheel installation deviation, external disturbances, and uncertain mass of moment inertia. The attitude track performance using the proposed finite-time compensation control is evaluated through a numerical example.

Robust spacecraft attitude tracking control with integral terminal sliding mode surface considering input saturation

2018 ◽  
Vol 41 (2) ◽  
pp. 405-416 ◽  
Author(s):  
Haitao Chen ◽  
Shenmin Song ◽  
Xuehui Li
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
External Disturbance ◽  
Input Saturation ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Modeling Uncertainty ◽  
Finite Time Convergence ◽  
Attitude Tracking ◽  
Attitude Tracking Control

This paper studies the finite time spacecraft attitude tracking control problem, while considering modeling uncertainty, external disturbances and control input saturation. A novel integral terminal sliding mode surface (ITSMS) is designed by combining the fast terminal sliding mode surface (FTSMS) with a low pass filter to achieve a fast finite time convergence rate for the control system, without input singularity. An auxiliary signal is used to compensate for the effects of actuator saturation. The basic controller is first formulated based on the ITSMS, fast-TSM-type reaching law and auxiliary system, in the presence of an external disturbance and input saturation. Then, an adaptive control procedure is introduced, which simultaneously handles modeling uncertainty and external disturbance, thereby creating an adaptive attitude tracking controller. The proposed controller provides a fast finite time convergence rate for the control system, based on the newly designed ITSMS, while simultaneously compensating for modeling uncertainty, external disturbances and input saturation, without restricting the parameter selection process nor requiring repeated differentiation of nonlinear functions. Finally, digital simulation results are presented and demonstrate the effectiveness of the proposed controllers.

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.

scholarly journals SMC-Based Synchronization of Multiple Inertial Measurement Units with Application to Attitude Tracking Control

2021 ◽  
Vol 2021 ◽  
pp. 1-9
Author(s):  
Yuping He ◽  
Shijie Zhang
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
External Disturbance ◽  
Zero Drift ◽  
Consensus Algorithm ◽  
Inertial Measurement Units ◽  
Inertial Measurement ◽  
Attitude Tracking ◽  
Measurement Units ◽  
Attitude Tracking Control

In this paper, the attitude control of aircraft with multiple inertial measurement units under the influence of unknown gyro zero drift and external disturbance is studied. First of all, the observers are designed to estimate the zero drift biases based on the consensus algorithm. The angular velocity used for aircraft control is obtained by compensating the biases. Then, considering the external disturbance in the aircraft motion, this paper introduces a super-twisting sliding-mode algorithm to design the observer in order to compensate the disturbance. In addition, based on the proposed observers, a controller is designed to realize attitude control of the aircraft with the gyro zero drift and the external disturbance. Finally, the simulation results are given to verify the effectiveness of the proposed control law.

Finite time attitude tracking control of an autonomous airship

2016 ◽  
Vol 40 (1) ◽  
pp. 155-162 ◽  
Author(s):  
Yueying Wang ◽  
Pingfang Zhou ◽  
Ji-An Chen ◽  
Dengping Duan
Keyword(s):  
Finite Time ◽  
Attitude Control ◽  
Tracking Control ◽  
Feedback Linearization ◽  
Sliding Mode ◽  
Uncertain System ◽  
External Disturbances ◽  
Attitude Tracking ◽  
System Uncertainties ◽  
Attitude Tracking Control

The problem of station-keeping attitude tracking control for an autonomous airship with system uncertainties and external disturbances is investigated. Adaptive laws are applied to estimate the upper bounds of uncertainties and disturbances, and a nonlinear finite time control scheme is proposed by combing input/output feedback linearization with integral sliding mode technique. Different from the existing works on attitude control of airship, the developed controller can guarantee the yaw, pitch and roll angle trajectories track the desired attitude in finite time in spite of uncertain system uncertainties and external disturbances. Simulation results are provided to illustrate the attitude tracking performance.

scholarly journals Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite

2014 ◽  
Vol 2014 ◽  
pp. 1-15 ◽  
Author(s):  
Mingyi Huo ◽  
Xing Huo ◽  
Hamid Reza Karimi ◽  
Jianfei Ni
Keyword(s):  
Upper Bound ◽  
Finite Time ◽  
Sliding Mode ◽  
Tracking System ◽  
External Disturbance ◽  
Adaptive Sliding Mode Control ◽  
Tracking Errors ◽  
Time Control ◽  
Attitude Tracking ◽  
Inertia Parameters

The problem of finite-time control for attitude tracking maneuver of a rigid spacecraft is investigated. External disturbance, unknown inertia parameters are addressed. As stepping stone, a sliding mode controller is designed. It requires the upper bound of the lumped uncertainty including disturbance and inertia matrix. However, this upper bound may not be easily obtained. Therefore, an adaptive sliding mode control law is then proposed to release that drawback. Adaptive technique is applied to estimate that bound. It is proved that the closed-loop attitude tracking system is finite-time stable. The tracking errors of the attitude and the angular velocity are asymptotically stabilized. Moreover, the upper bound on the lumped uncertainty can be exactly estimated in finite time. The attitude tracking performance with application of the control scheme is evaluated through a numerical example.

scholarly journals Gliding-Guided Projectile Attitude Tracking Controller Design Based on Improved Adaptive Twisting Sliding Mode Algorithm

2020 ◽  
Vol 2020 ◽  
pp. 1-15
Author(s):  
Wenguang Zhang ◽  
Wenjun Yi
Keyword(s):  
Finite Time ◽  
Tracking Control ◽  
Controller Design ◽  
Sliding Mode ◽  
Closed Loop System ◽  
Finite Time Convergence ◽  
Attitude Tracking ◽  
Control Scheme ◽  
Chattering Attenuation ◽  
Attitude Tracking Control

The finite-time attitude tracking control for gliding-guided projectile with unmatched and matched disturbance is investigated. An adaptive variable observer is used to provide estimation for the unmeasured state which contains unmatched disturbance. Then, an improved adaptive twisting sliding mode algorithm is proposed to compensate for the matched disturbance dynamically with better transient quality. Finally, a proof of the finite-time convergence of the closed-loop system under the disturbance observer and the adaptive twisting sliding mode-based controller is derived using the Lyapunov technique. This attitude tracking control scheme does not require any information on the bounds of uncertainties. Simulation results demonstrate that the proposed method which is able to acquire the minimum possible values of the control gains guaranteeing the finite-time convergence performs well in chattering attenuation and tracking precision.

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.

scholarly journals Adaptive output feedback integral sliding mode attitude tracking control of spacecraft without unwinding

2017 ◽  
Vol 9 (7) ◽  
pp. 168781401771040 ◽  
Author(s):  
Anuchit Jitpattanakul ◽  
Chutiphon Pukdeboon
Keyword(s):  
Output Feedback ◽  
Tracking Control ◽  
Sliding Mode ◽  
Control Technique ◽  
Control Law ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Integral Sliding Mode ◽  
Attitude Tracking ◽  
Attitude Tracking Control

This article studies an output feedback attitude tracking control problem for rigid spacecraft in the presence of parameter uncertainties and external disturbances. First, an anti-unwinding attitude control law is designed using the integral sliding mode control technique to achieve accurate tracking responses and robustness against inertia uncertainties and external disturbances. Next, the derived control law is combined with a suitable tuning law to relax the knowledge about the bounds of uncertainties and disturbances. The stability results are rigorously proved using the Lyapunov stability theory. In addition, a new finite-time sliding mode observer is developed to estimate the first time derivative of attitude. A new adaptive output feedback attitude controller is designed based on the estimated results, and angular velocity measurements are not required in the design process. A Lyapunov-based analysis is provided to demonstrate the uniformly ultimately bounded stability of the observer errors. Numerical simulations are given to illustrate the effectiveness of the proposed control method.

scholarly journals Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix

2015 ◽  
Vol 2015 ◽  
pp. 1-9 ◽  
Author(s):  
Yong Guo ◽  
Shen-Min Song ◽  
Xue-Hui Li
Keyword(s):  
Finite Time ◽  
Control Method ◽  
Sliding Mode ◽  
Rotation Matrix ◽  
Sliding Mode Controller ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Attitude Tracking ◽  
Sliding Manifold ◽  
Attitude Tracking Control

Two finite-time controllers without unwinding for the attitude tracking control of the spacecraft are investigated based on the rotation matrix, in which a novel modified nonsingular fast terminal sliding manifold is developed to keep tr(R~)≠-1. The first terminal sliding mode controller can compensate external disturbances with known bounds, while the second one can compensate external disturbances with unknown bounds by using an adaptive control method. Since the first terminal sliding mode controller is continuous, it is able to avoid chattering phenomenon. Theoretical analysis shows that both the two controllers can make spacecraft follow a time-varying reference attitude signal in finite time. Numerical simulations also demonstrate that the proposed control schemes are effective.

Sign in / Sign up

Export Citation Format

Share Document