Journal of Artificial Intelligence in Electrical Engineering
Volume:7 Issue: 28, Winter 2019

Control actuators' faults are among the major reasons to lose aircraft control while flights. The plane dynamics is severely dependent upon faults and errors in flight control systems and if the reformed control order is not issued by the fault tolerant controller there would be unpleasant outcomes such as inconsistency and the reduction of system performance and some dreadful aerial accidents will occur. This research includes the presentation of a fault tolerant control technique based on nonlinear optimal control method using Rekaty equation related to the state. The characteristics of nonlinear optimal control method entail the possibility of novel aircraft modeling and restructuring of the control systems when a fault occurs and this increases the possibility of flight save. The two scenarios of error and failure include the reduction of elevator efficiency and the exclusion of aileron of a great business aircraft from being controlled and the optimal function of nonlinear method compared with linear optimal control. It is the first time that this technique is used in local research projects as a control method. The results of simulations proved the effectiveness of the proposed approach in consistency retrieval and the preservation of flight route. Several linear and nonlinear controllers have been planned and implemented to control the position and status of flights. During some recent decades and due to lack of ability in linear control systems, there has been extending developments in methods such as linearization with feedback, interest tabling, return to past method, slide mode control, adjustment control, Thus, the goal of the present research is to design a nonlinear controller with a resistant approach for the systems. Also the simulation results showed efficiency of the controllers in flight consistency and system direction. The goal of the present study is to know different aircrafts especially Boeing 100-747, to study about the actuators' failures and to investigate about different types of aerial disasters and their reasons, to know different controlling and comparing techniques with nonlinear control technique and to design active controllers using nonlinear techniques for a Boeing 747 flight aircraft.

Since 1976, Shooting was include in Paralympics sport mach’s to establish same target conditions for different types of handicapped people, it is essential design a system of “laser target controls”. In this study, a laser target controller is designed by determinable of wave length of laser accuracy then, by using parameters, performance and ever redacting, theses wave length import as inputs to system. Finally constantly enchase shooting abilities of shooter.

It is difficult to control the movement of the robot arm due to its nonlinear structure. PID controller is still in the world because of its simplicity in designing this controller as the main controller. The nonlinear control technique is very complicated, and this is not very interesting in the controller. While fuzzy control has a better performance, it incorporates a fuzzy control with the PID controller to use the PID fuzzy control system to monitor the robot arm system with 5 DOF. This online control proposal is provided to get the best performance, which is possible with fuzzy supervisory control according to the simulation results in MATLAB.

The occurrence of catastrophic earthquakes necessitates further researches in the structure engineering for retrofitting construction structures. In this paper, the application of the active control in the structures’ seismic response has been addressed. A single degree of freedom nonlinear structure has been studied. The nonlinear dynamic of the structure is considered in which, the nonlinear part of the dynamic is modeled by Bouc-Wen model. The sliding mode controller is used to stabilize the system. The results show the effectiveness of the proposed method.

Power systems are composed of power units that are constantly connected to each other and the electric power flux is constantly moving between them. All systems must be implemented in such a way that not only under normal conditions but also unwanted inputs or disturbances, are applied. It also remains stable or returns to a stable name at the earliest possible time. The fundamental factors of stability control in a power system are the frequency of different areas and the power flux between different areas. Now that the main goals of controlling stability in a system of power are expressed, they must be maintained by designing and implementing controllers of these indicators in their optimal range. In this study, the frequency control function is initially expressed. Subsequently, the design of several additional controller parameters is based on this algorithm and ultimately, by applying additional controllers designed on the simulated power system, the results of the effect of each of them on the faster loss of frequency oscillations will be discussed.

Micro system technology is a relatively new scientific research that deals with the development and study of properties of materials in micro dimensions. Micro-grippers are widely used in switching, positioning, and assembling micron sized components in micro-robotics. In this study, the static and dynamic behavior of visco-elastic Micro-Tweezers under the thermal and electrostatic field is studied numerically. In order to consider more realistic assumptions, the visco-elastic behavior is investigated and thermal effects are simulated by considering both linear and nonlinear models. Considering Euler-Bernoulli beam theory, governing differential equation of motion are derived. Finally, the effect of different parameters such as the parameter of visco-elastic parameters, the effects of temperature and intensity of the electrostatic field on the dynamic and static characteristics of the Micro-Tweezers have been investigated. The results show that visco-elastic behavior has a significant effect on the dynamic behavior of Micro-Tweezers, and with its increase, the damping of the system increases and the amplitude of the Micro-Tweezers oscillations decreases. The system's damping increases from 0.01 to 0.08, the maximum amplitude of Micro-Tweezers decreases from 0.9 to 0.66.