A Global Fast Integral Operator Terminal Adaptive Sliding-Mode Controller

2012 ◽  
Vol 190-191 ◽  
pp. 880-885
Author(s):  
Lu Cao ◽  
Xiao Qian Chen ◽  
Yong Zhao
Keyword(s):  
Control System ◽  
Integral Operator ◽  
Attitude Control ◽  
High Performance ◽  
Sliding Mode ◽  
High Reliability ◽  
Sliding Mode Controller ◽  
Limited Time ◽  
Attitude Control System ◽  
Adaptive Sliding Mode Controller

Attitude Control System(ACS); Terminal; Adaptive; Integral operator Abstract: Attitude Control System (ACS) with high performance, high precision, and high reliability is the kernel technology of the research of spacecraft, which directly affects the whole performance of spacecraft. Hence, a global fast integral operator Terminal adaptive sliding-mode controller is proposed to come true the high performance control. The theory of this controller is to introduce the limited time mechanics—Terminal mode to the sliding-mode control and introduce the integral operator to the sliding-mode plane, which can realize the convergence of spacecraft attitude in “limited time” in the condition of serious disturbance , in order to enhance the performance of fast response. At last, the simulation results demonstrate the high reliability and advantages of the control approach.

scholarly journals Adaptive Sliding Mode Controller Design For Attitude Small UAV

2015 ◽  
Vol 4 (3) ◽  
pp. 219
Author(s):  
Samaneh Amini
Keyword(s):  
Attitude Control ◽  
Controller Design ◽  
Sliding Mode ◽  
External Disturbance ◽  
Sliding Mode Controller ◽  
Attitude Control System ◽  
Strongly Coupled ◽  
Adaptive Sliding Mode ◽  
Adaptive Sliding Mode Controller ◽  
Aerial Vehicle

The dynamic of Unmanned Aerial Vehicle (UAV) is nonlinear, strongly coupled, multi-input multi-output (MIMO), and subject to uncertainties and external disturbances.  In this paper, an adaptive sliding mode controller (ASMC) is integrated to design the attitude control system for an inner loop fixed wing UAV. In the proposed scheme, sliding mode control law parameters due to uncertainty are assumed to be unknown and are estimated via adaptation laws. The synthesis of the adaptation laws is based on the positivity and Lyapunov design principle. Navigation outer loop parameters are regulated via PID controllers. Simulation results indicate that the proposed controller design can stabilize the nonlinear system, and it is robust to parametric model uncertainties and external disturbance.

scholarly journals Fault Reconstruction Approach for Distributed Coordinated Spacecraft Attitude Control System

2015 ◽  
Vol 2015 ◽  
pp. 1-9
Author(s):  
Mingyi Huo ◽  
Yanning Guo ◽  
Xing Huo
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Large Scale ◽  
Sliding Mode ◽  
Reconstruction Error ◽  
Spacecraft Attitude ◽  
Alignment Error ◽  
Spacecraft Attitude Control ◽  
Attitude Control System ◽  
Fault Reconstruction

This work presents a novel fault reconstruction approach for a large-scale system, that is, a distributed coordinated spacecraft attitude control system. The attitude of all the spacecrafts in this distributed system is controlled by using thrusters. All possible faults of thruster including thrust magnitude error and alignment error are investigated. As a stepping stone, the mathematical model of thruster is firstly established based on the thruster configuration. On the basis of this, a sliding mode observer is then proposed to reconstruct faults in each agent of the coordinated control system. A Lyapunov-based analysis shows that the observer asymptotically converges to the actual faults. The key feature of this fault reconstruction approach is that it can achieve a faster reconstruction of the fault in comparison with the conventional fault reconstruction schemes. It can globally reconstruct thruster faults with zero reconstruction error, and this is accomplished within finite time. The effectiveness of the proposed approach is analytically authenticated via simulation study.

Gain adaptive sliding mode controller for flight attitude control of MAV

2013 ◽  
Vol 21 (5) ◽  
pp. 1183-1191 ◽  
Author(s):  
李迪 LI Di ◽  
陈向坚 CHEN Xiang-jian ◽  
续志军 XU Zhi-jun
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Sliding Mode Controller ◽  
Adaptive Sliding Mode ◽  
Adaptive Sliding Mode Controller

Fuzzy Adaptive Sliding Mode Control Based on Fuzzy Compensation for Ammunition Auto-Loading Robot

2013 ◽  
Vol 816-817 ◽  
pp. 363-366
Author(s):  
Yu Feng Li ◽  
Kui Wu Li ◽  
Yu Tian Pan ◽  
Bao Quan Guo
Keyword(s):  
Control System ◽  
Fuzzy Systems ◽  
Sliding Mode ◽  
Adaptive Sliding Mode Control ◽  
Sliding Mode Controller ◽  
Disturbance Compensation ◽  
Adaptive Sliding Mode ◽  
Adaptive Sliding Mode Controller ◽  
Simulation Results ◽  
Fuzzy Adaptive

A new fuzzy adaptive sliding mode controller based on fuzzy compensation for robot is proposed. The control architecture employs fuzzy systems to compensate adaptively for plant uncertainties to distinguish different disturbance compensation terms and approximate each of them respectively. By analyzing and comparing the simulation results, it is obviously shown that the control system can lighten the effect on the control system caused by different disturbance factors and eliminate the system chattering than that of traditional SMC.

scholarly journals Sliding Mode Control Techniques for Combined Energy and Attitude Control System

2014 ◽  
Vol 629 ◽  
pp. 310-317 ◽  
Author(s):  
Samira Eshghi ◽  
Renuganth Varatharajoo
Keyword(s):  
Control System ◽  
Energy Storage ◽  
Attitude Control ◽  
Sliding Mode ◽  
Storage System ◽  
Energy Storage System ◽  
Storage Device ◽  
Optimization Approach ◽  
Attitude Control System ◽  
The Mathematical Model

Combined Energy and Attitude Control System (CEACS) is an optimization approach that combines the energy storage system and the attitude control system. With a double counter rotating flywheel simultaneously serving as energy storage device and as attitude control actuator, CEACS requires an accurate control strategy to obtain the mission requirements. In addition, it is important to design the control law to be invariant to uncertainties and disturbances, and guarantee robustness as CEACS inherits these in-orbit uncertainties. This paper presents a nonlinear control employing sliding mode to enhance the CEACS attitude control capability. The mathematical model for the conventional and boundary layer sliding mode controls are developed herein for CEACS. The controller provides enhancement in pointing accuracies, reasonable transient responses and a robustness against uncertainties and in-orbit disturbances.

L1 neural network adaptive fault-tolerant controller for unmanned aerial vehicle attitude control system

2021 ◽  
pp. 095441002098409
Author(s):  
Yan Zhou ◽  
Huiying Liu ◽  
Huijuan Guo ◽  
Jing Li
Keyword(s):  
Neural Network ◽  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Attitude Control ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Attitude Control System ◽  
Attitude Tracking ◽  
Nonlinear Uncertainties ◽  
Aerial Vehicle

In this article, a L1 neural network adaptive fault-tolerant controller is exploited for an unmanned aerial vehicle attitude control system in presence of nonlinear uncertainties, such as system uncertainties, external disturbances, and actuator faults. A nonlinear dynamic inversion controller with sliding mode control law is designed as the outer-loop controller to track the attitude angles quickly and accurately which reduces dependence on model accuracy. A L1 neural network adaptive controller of the inner loop is introduced to compensate the nonlinear uncertainties and have a good attitude tracking. The radial basis function neural network technique is introduced to approximate a lumped nonlinear uncertainty and guarantee the stability and transient performance of the closed-loop system, instead of converting it to a half-time linear system by the parametric linearization method. Simulation results demonstrate the effectiveness of the proposed controller.

Increasing of Reliability of Spacecraft Control System on Base of Robust Diagnostic Models and Division Principle in Parity Space

2020 ◽  
Vol 21 (4) ◽  
pp. 249-256
Author(s):  
A. I. Zavedeev
Keyword(s):  
Control System ◽  
Attitude Control ◽  
High Reliability ◽  
System Model ◽  
Diagnostic Systems ◽  
Attitude Control System ◽  
Spacecraft Control ◽  
Mathematical System ◽  
Diagnostic Models ◽  
Parity Space

Different directions of creation high reliability integrate spacecraft control system are discussed on base of robust diagnostic models and division principle in parity space. Problems of synthesis spacecraft control system algorithms are examined with incomplete apriory and distorted current information, action of uncontrolled and random factors, information losses and equipment failures. The structure of onboard attitude control system is synthesized and control algorithms are chosen, which guarantee robust stability and failure stability in presence indignant factors and obstacles. An instrumental structure and operational modes of spacecraft attitude control system are described. Methods of dynamic research, computer technology and modeling particularities are indicated. Diagnostic and reconfiguration algorithms for onboard complex of connection, navigation, geodesy satellites and earth inspectoral satellite in prolonged space flight utilization are proposed. Testing procedure is contains two stage: discovering and eliminating faults. Given mathematical system model is researched by means of difference signals, which forms with arise at fault emergence. The failure character is established by deciding rules on base difference signals and measures to it eliminating are took. Questions of onboard spacecraft control system failure stable improving are discussed on base principle reconfiguration with apply to adaptive logic in testing and diagnostic algorithms. The mathematical system model is researching with implementation of analytic reserving. Difference signals are formed, which arise at fault appearance. The adaptive approach to development testing and diagnostic systems provide for realization of flexible logic of control system function to take into account factual onboard equipment state. Special attention is devote to problem influence liquid fuel reactive engine agility on spacecraft control attitude system dynamic characteristics and precision. The effectiveness of prepositional approaches and algorithms is confirmed by mathematical modeling results for several actual technical systems. Recommendations to their practical applications are given. 

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