Space Flyaround and In-orbit Inspection Coupled Control Based on Dual Numbers

2018 ◽  
Vol 71 (5) ◽  
pp. 1088-1110
Author(s):  
Lijun Zhang ◽  
Hanqiu Li ◽  
Jianping Liu ◽  
Shan Qian ◽  
Yi Lu ◽  
...  
Keyword(s):  
Control System ◽  
Feedback Control ◽  
Sliding Mode Control ◽  
Sliding Mode ◽  
Coupling Effect ◽  
Variable Structure ◽  
Dual Numbers ◽  
Control Laws ◽  
Mode Control ◽  
Dynamics Models

In this paper, both the proportional derivative feedback control and variable-structure sliding mode control approaches based on dual numbers are presented to design space flyaround and in-orbit inspection missions. Dual-number-based spacecraft kinematics and dynamics models are formulated. The integrated translational and rotational motions can be described in one compact expression, and the mutual coupling effect can be considered. A space flyaround and in-orbit inspection mission model based on dual numbers is derived. Both proportional derivative feedback control and variable-structure sliding mode control laws are designed using dual numbers. Simulation results indicate that both the proposed control system can provide high-precision control for relative position and attitude. Of the two systems, the variable-structure sliding mode control system performs the best.

scholarly journals Optimal Sliding Mode Controllers for Attitude Stabilization of Flexible Spacecraft

2011 ◽  
Vol 2011 ◽  
pp. 1-20 ◽  
Author(s):  
Chutiphon Pukdeboon
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Sliding Mode Control ◽  
Control Problem ◽  
Attitude Control ◽  
Sliding Mode ◽  
Flexible Spacecraft ◽  
Attitude Control System ◽  
Control Laws ◽  
Mode Control

The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sliding mode control laws that ensure the exponential convergence of the attitude control system are developed. Integral sliding mode control (ISMC) is applied to combine the first-order sliding mode with optimal control and is used to control quaternion-based spacecraft attitude manoeuvres with external disturbances and an uncertainty inertia matrix. For the optimal control part the state-dependent Riccati equation (SDRE) and optimal Lyapunov techniques are employed to solve the infinite-time nonlinear optimal control problem. The second method of Lyapunov is used to guarantee the stability of the attitude control system under the action of the proposed control laws. An example of multiaxial attitude manoeuvres is presented and simulation results are included to verify the usefulness of the developed controllers.

Fast Terminal Sliding-Mode Control with an Integral Filter Applied to a Longitudinal Axis of Flying Vehicles

2019 ◽  
Vol 16 (8) ◽  
pp. 3141-3153 ◽  
Author(s):  
Elham Ramezani ◽  
Seyyed Mohammad Hosseini Rostami
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
Sliding Mode Controller ◽  
Terminal Sliding Mode Control ◽  
Terminal Sliding Mode ◽  
Mode Control ◽  
Fast Terminal Sliding Mode

The automatic pilot flight control system is undoubtedly one of the most important parts of the flying vehicle that provide stability and to operate appropriately in the guidance section. Considering to nonlinear, dynamic and time-varying system, structural and parametric uncertainties of the flying vehicles, in flight control, varietal control approach have to achieve stability, proper operation as well as decreasing effect of uncertainties and modeling errors. In this paper, designing of the longitudinal flying vehicles autopilot a Fast Terminal Sliding Mode Control (FTSMC). Variable structure systems because of the robustness effect on uncertainty and the effects on disturbances which a contributor to widespread efficiency. One of the methods for controlling the variable structure is a sliding mode, which is one of the nonlinear controllers that can control the system in the structured uncertainties and unstructured uncertainties. Additionally, in the method of classic sliding Mode Control is got convergence of states equilibrium point by an asymptotic curve. While proportional Integral Sliding Mode Control has the convergence of states to the equilibrium point in finite time. One of the issues is that finite time cannot determine the time of convergence when the state turn initial position to a final position. The proposed method is based on the Lyapunov stability theory and has guaranteed stability of the control system. The controller is robust to external disturbances and unmodified dynamics. Three types of controllers which are multi-input-multi-output (MIMO) system with random uncertainty are designed. Furthermore, the classic sliding mode controller, the proportional-integral sliding mode controller as well as the integral terminal sliding mode controller are reviewed. A glance at the results simulates shows an improved in the proposed method. Simulations are done using MATLAB software.

scholarly journals Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

Energies ◽  
2020 ◽  
Vol 13 (18) ◽  
pp. 4841
Author(s):  
Khaoula Derbel ◽  
Károly Beneda
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
Control Law ◽  
Power Ratio ◽  
Mode Control ◽  
Turbojet Engine ◽  
Discharge Temperature ◽  
And Control

The interest in turbojet engines was emerging in the past years due to their simplicity. The purpose of this article is to investigate sliding mode control (SMC) for a micro turbojet engine based on an unconventional compound thermodynamic parameter called Turbofan Power Ratio (TPR) and prove its advantage over traditional linear methods and thrust parameters. Based on previous research by the authors, TPR can be applied to single stream turbojet engines as it varies proportionally to thrust, thus it is suitable as control law. The turbojet is modeled by a linear, parameter-varying structure, and variable structure sliding mode control has been selected to control the system, as it offers excellent disturbance rejection and provides robustness against discrepancies between mathematical model and real plant as well. Both model and control system have been created in MATLAB® Simulink®, data from real measurement have been taken to evaluate control system performance. The same assessment is conducted with conventional Proportional-Integral-Derivative (PID) controllers and showed the superiority of SMC, furthermore TPR computation using turbine discharge temperature was proven. Based on the results of the simulation, a controller layout is proposed and its feasibility is investigated. The utilization of TPR results in more accurate thrust output, meanwhile it allows better insight into the thermodynamic process of the engine, hence it carries an additional diagnostic possibility.

A Continuous First-Order Sliding Mode Control Law

2017 ◽  
Author(s):  
Keyvan Mohammadi ◽  
Andrea L’Afflitto
Keyword(s):  
Feedback Control ◽  
Sliding Mode Control ◽  
Closed Loop ◽  
Sliding Mode ◽  
Nonlinear Differential Equations ◽  
Nonlinear Observer ◽  
Control Architecture ◽  
Control Law ◽  
Control Laws ◽  
Mode Control

Sliding mode control is a technique to design robust feedback control laws. In its classical formulation, this approach involves discontinuous controls that arise several theoretical and practical challenges, such as the existence of non-unique solutions of nonlinear differential equations and chattering. Numerous variations of the sliding mode control architecture, such as the higher-order sliding mode method, have been presented to overcome these issues. In this paper, we present an alternative sliding mode control architecture that involves Hölder continuous feedback control laws, is simpler to implement than other non-classical nonlinear robust control techniques, guarantees robustness and uniform asymptotic stability of the closed-loop system, and ensures both existence and uniqueness of the closed-loop system’s trajectory. Our results are applied to design a robust nonlinear observer in the same form as the Walcott and Żak observer. Moreover, a numerical example illustrates our theoretical results and compares the proposed control law to the classical sliding mode control, the second order sliding mode control, and the super-twisting control.

Sliding Mode Control for Wheeled Inverted Pendulum

2014 ◽  
Vol 971-973 ◽  
pp. 714-717 ◽  
Author(s):  
Xiang Shi ◽  
Zhe Xu ◽  
Qing Yi He ◽  
Ka Tian
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
High Performance ◽  
Inverted Pendulum ◽  
Sliding Mode ◽  
Experimental Results ◽  
Control Law ◽  
Collaborative Simulation ◽  
Mode Control ◽  
Wheeled Inverted Pendulum

To control wheeled inverted pendulum is a good way to test all kinds of theories of control. The control law is designed, and it based on the collaborative simulation of MATLAB and ADAMS is used to control wheeled inverted pendulum. Then, with own design of hardware and software of control system, sliding mode control is used to wheeled inverted pendulum, and the experimental results of it indicate short adjusting time, the small overshoot and high performance.

Simulation of Control System for Permanent Magnet Synchronous Machine

2011 ◽  
Vol 66-68 ◽  
pp. 1422-1427
Author(s):  
Ting You ◽  
Pei Jiang Li
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Permanent Magnet ◽  
Disturbance Rejection ◽  
Sliding Mode ◽  
Synchronous Machine ◽  
Permanent Magnet Synchronous Machine ◽  
Mode Control ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control

For optimal control of synchronous machine, chattering phenomenon will appear if traditional slider control is adopted because permanent magnet synchronous machine is a complex nonlinear time-dependent system with strong coupling of current and rotational speed to cause the deterioration of system control performance with load or load disturbance. In this article, based on the mathematical model of permanent magnet synchronous machine, a control system for it, which combines sliding mode control and active disturbance rejection control, is proposed to improve the dynamic performance and robustness of control system. In the control system, sliding mode control is adopted to control the inner current of machine and active disturbance rejection control is adopted to control the outer speed. The load disturbance of system is also estimated and offset. The results of matlab simulation show that the control system can eliminate serious chattering phenomenon existing in sliding mode control, improves the robustness of system for load and system parameter disturbance as well as has great dynamic and static performance.

scholarly journals A New Control Method for Second-Order Multiple Models Control System Based on Global Sliding Mode

2018 ◽  
Vol 2018 ◽  
pp. 1-8 ◽  
Author(s):  
Dan-xu Zhang ◽  
Yang-wang Fang ◽  
Peng-fei Yang ◽  
You-li Wu ◽  
Tong-xin Liu
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Finite Time ◽  
Sliding Mode ◽  
Second Order ◽  
Multiple Models ◽  
Finite Time Convergence ◽  
Mode Control ◽  
Global Sliding Mode Control ◽  
Control Scheme

This paper proposed a finite time convergence global sliding mode control scheme for the second-order multiple models control system. Firstly, the global sliding surface without reaching law for a single model control system is designed and the tracking error finite time convergence and global stability are proved. Secondly, we generalize the above scheme to the second-order multimodel control system and obtain the global sliding mode control law. Then, the convergent and stable performances of the closed-loop control system with multimodel controllers are proved. Finally, a simulation example shows that the proposed control scheme is more effective and useful compared with the traditional sliding mode control scheme.

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