Extended state observer-based third-order sliding mode finite-time attitude tracking controller for rigid spacecraft

2018 ◽  
Vol 62 (1) ◽  
Author(s):  
Chutiphon Pukdeboon
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Third Order ◽  
Attitude Tracking ◽  
Tracking Controller ◽  
Rigid Spacecraft

scholarly journals Attitude control for the rigid spacecraft with the improved extended state observer

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Yuteng Cao ◽  
Qi Liu ◽  
Guiqin He ◽  
Qiuling Zhao ◽  
Fang Liu
Keyword(s):  
Sliding Mode Control ◽  
Rigid Body ◽  
Attitude Control ◽  
Control Method ◽  
Sliding Mode ◽  
State Observer ◽  
Extended State Observer ◽  
Solar Array ◽  
Extended State ◽  
Rigid Spacecraft

Abstract In this article, a three-axis attitude manoeuvre spacecraft consisting of a central rigid body and a rotating solar array is studied. The rotating solar array is considered a disturbance to the spacecraft. In the design of the controller, the coupled terms and the rotating solar array are considered a disturbance. The improved extended state observer is proposed by combing the sliding mode observer with the originally extended state observer to estimate the disturbance. The sliding mode control method is adopted to adjust the attitude of the spacecraft. Numerical simulations are presented to demonstrate the outstanding performance of the present observer.

scholarly journals Extended-State-Observer-Based Terminal Sliding Mode Tracking Control for Synchronous Fly-Around with Space Tumbling Target

2019 ◽  
Vol 2019 ◽  
pp. 1-15
Author(s):  
Zhijun Chen ◽  
Yong Zhao ◽  
Yuzhu Bai ◽  
Dechao Ran ◽  
Liang He
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Coupling Effect ◽  
External Disturbance ◽  
Fast Response ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Terminal Sliding Mode ◽  
Tumbling Target

This paper presents a robust controller with an extended state observer to solve the Synchronous Fly-Around problem of a chaser spacecraft approaching a tumbling target in the presence of unknown uncertainty and bounded external disturbance. The rotational motion and time-varying docking trajectory of tumbling target are given in advance and referred as the desired tracking objective. Based on dual quaternion framework, a six-degree-of-freedom coupled relative motion between two spacecrafts is modeled, in which the coupling effect, model uncertainties, and external disturbances are considered. More specially, a novel nonsingular terminal sliding mode is designed to ensure the convergence to the desired trajectory in finite time. Based on the second-order sliding mode, an extended state observer is employed to the controller to compensate the closed-loop system. By theoretical analysis, it is proved that the modified extended-state-observer-based controller guarantees the finite-time stabilization. Numerical simulations are taken to show the effectiveness and superiority of the proposed control scheme. Finally, Synchronous Fly-Around maneuvers can be accomplished with fast response and high accuracy.

scholarly journals Finite-Time Anti-Disturbance Inverse Optimal Attitude Tracking Control of Flexible Spacecraft

2013 ◽  
Vol 2013 ◽  
pp. 1-13 ◽  
Author(s):  
Chutiphon Pukdeboon ◽  
Anuchit Jitpattanakul
Keyword(s):  
Optimal Control ◽  
Lyapunov Function ◽  
Finite Time ◽  
Estimation Error ◽  
State Observer ◽  
Flexible Spacecraft ◽  
Extended State Observer ◽  
Inverse Optimal Control ◽  
Extended State ◽  
Attitude Tracking

We propose a new robust optimal control strategy for flexible spacecraft attitude tracking maneuvers in the presence of external disturbances. An inverse optimal control law is designed based on a Sontag-type formula and a control Lyapunov function. An adapted extended state observer is used to compensate for the total disturbances. The proposed controller can be expressed as the sum of an inverse optimal control and an adapted extended state observer. It is shown that the developed controller can minimize a cost functional and ensure the finite-time stability of a closed-loop system without solving the associated Hamilton-Jacobi-Bellman equation directly. For an adapted extended state observer, the finite-time convergence of estimation error dynamics is proven using a strict Lyapunov function. An example of multiaxial attitude tracking maneuvers is presented and simulation results are included to show the performance of the developed controller.

Robust Attitude Control of Quadrotor Vehicle via Extended State Observer

2013 ◽  
Vol 373-375 ◽  
pp. 1445-1448 ◽  
Author(s):  
Dang Jun Zhao ◽  
Bing Yan Jiang
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Output Feedback Control ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Attitude Tracking ◽  
Mode Method ◽  
Attitude Tracking Control ◽  
Feedback Control Strategy

Extended state observer (ESO) based output-feedback control strategy is proposed for the attitude control of a quadrotor aerial vehicle in this paper. By using ESO technique, the generalized disturbances are estimated from output signals. According to the sliding mode method, the attitude controller with disturbance compensations is proposed for the attitude tracking control of a quadrotor vehicle. The theoretical analysis reveals that all signals in the closed-loop system are ultimately uniformly bounded. The simulation results validate the efficiency of the proposed method.

scholarly journals Finite Time Output Feedback Attitude Tracking Control for Rigid Body Based on Extended State Observer

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Meng Duan ◽  
Yingmin Jia
Keyword(s):  
Output Feedback ◽  
Finite Time ◽  
Tracking Control ◽  
Lyapunov Method ◽  
State Observer ◽  
Extended State Observer ◽  
Extended State ◽  
Attitude Tracking ◽  
Control Scheme ◽  
Attitude Tracking Control

In this paper, the attitude tracking control problem of output feedback is investigated. A finite time extended state observer (FTESO) is designed through the homogeneous Lyapunov method to estimate the virtual angular velocity and total disturbances. Based on these estimated states, a finite time attitude tracking controller is developed. The numerical simulations are given to illustrate the effectiveness of the proposed control scheme.

Extended state observer-based finite-time guidance laws on account of thruster dynamics

2019 ◽  
Vol 233 (12) ◽  
pp. 4583-4597 ◽  
Author(s):  
Meijun Duan ◽  
Di Zhou ◽  
Dalin Cheng
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Angular Rate ◽  
State Observer ◽  
Extended State Observer ◽  
Line Of Sight ◽  
Switching Frequency ◽  
Extended State ◽  
Guidance Law ◽  
Guidance Laws

Guidance laws are designed for a near space interceptor with line-of-sight angle as input and on–off type thrust as output. The dynamics of thruster is viewed as a first-order lag with on–off working style and is integrated with the target–interceptor engagement dynamics to design bang-bang type sliding mode guidance laws. An extended state observer is designed to estimate the line-of-sight angular rate and the acceleration of target with the line-of-sight angle as a measurement. It is rigorously proved that the states of guidance system converge to a neighborhood of sliding mode in finite time and the line-of-sight angular rate converges to a neighborhood of the origin along the sliding mode in finite time under the designed guidance laws. Furthermore, in order to reduce the switching frequency of thruster, a sliding mode guidance law with hysteresis-band according to the sufficient condition for finite time convergence is proposed. Then, it is integrated with the bang-bang type sliding mode guidance law to yield a composite guidance law. Simulation results show that the extended state observer can effectively estimate the line-of-sight angular rate and the target acceleration, and the proposed sliding mode guidance laws have better performance than typical proportional guidance law.

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