Optimal Control of Roll Axis of Aircraft Using PID Controller
01 Jan 2020-pp 961-969
TL;DR: The MATLAB simulation result shows that the PID controller tuned by the GA method for aviation aircraft dynamics gives better results.
Abstract: In this paper, the Proportional Integral Derivative (PID) controller is tuned using genetic algorithm. The optimally tuned controller is implemented in order to increase the stability and the performance of aircraft. The safety feature of flight system could be enhanced with the tuning of PID parameters of the controller for roll axis of any flight. The design of a mathematical model is necessary for describing the latitudinal roll axis of an aviation aircraft. The PID controller can be employed based on the dynamic as well as mathematical modelling of the aircraft system. The Zeigler Nichols (ZN) Method and Genetic Algorithm (GA) optimization technique are considered to tune the PID controller parameters. The fitness function considered for the optimization algorithm is an Integral Absolute Error (IAE) criterion. The MATLAB simulation result shows that the PID controller tuned by the GA method for aviation aircraft dynamics gives better results.
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11 Jan 2021
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References
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Book•
01 Jan 2003
TL;DR: In this paper, the authors present Controller Architecture Tuning Rules for PI Controllers Tuning rules for PID Controllers Performance and Robustness Issues Glossary of Symbols Used in the Book Some Further Details on Process Modeling
Abstract: Introduction Controller Architecture Tuning Rules for PI Controllers Tuning Rules for PID Controllers Performance and Robustness Issues Glossary of Symbols Used in the Book Some Further Details on Process Modeling.
1,399 citations
TL;DR: This work proposes a genetically based PID controller tuned with fixed PID parameters that tends to operate the CSTR process in its entire operating range to overcome the limitations of the linear PID controller.
Abstract: Genetic algorithm (GA) based PID (proportional integral derivative) controller has been proposed for tuning optimized PID parameters in a continuous stirred tank reactor (CSTR) process using a weighted combination of objective functions, namely, integral square error (ISE), integral absolute error (IAE), and integrated time absolute error (ITAE). Optimization of PID controller parameters is the key goal in chemical and biochemical industries. PID controllers have narrowed down the operating range of processes with dynamic nonlinearity. In our proposed work, globally optimized PID parameters tend to operate the CSTR process in its entire operating range to overcome the limitations of the linear PID controller. The simulation study reveals that the GA based PID controller tuned with fixed PID parameters provides satisfactory performance in terms of set point tracking and disturbance rejection.
113 citations
23 Dec 2010
TL;DR: A test platform is proposed that can be applied into models similar to real aircraft minimizing risks and increasing flexibility for design changes, as study case, results from a roll attitude autopilot system are presented.
Abstract: Presently there is vast interest in UAV (Unmanned Aerial Vehicle) development given its civilian and military applications. One of the main UAV components is the autopilot system. Its development invariably demands several lab simulations and field tests. Generally after an UAV crash few parts remain usable. Thus, before embedding an autopilot system, it has to be exhaustively lab tested. With educational and research purposes in autopilot control systems development area, a test platform is herein proposed. It employs Matlab/Simulink to run the autopilot controller under test, the flight simulator X-Plane with the aircraft to be commanded, a microcontroller to command model aircraft flight control surfaces and a servo to drive these control surfaces. These resources are interconnected through data communication buses. So that, the autopilot controller designed on Matlab/Simulink is tested by controlling an aircraft on X-Plane. The inputs given to the aircraft flight control surfaces in the X-Plane are simultaneously sent to the microcontroller which translates these commands into effective servo movement control. Through this platform, designed autopilot systems can be applied into models similar to real aircraft minimizing risks and increasing flexibility for design changes. As study case, tests results from a roll attitude autopilot system are presented.
93 citations
15 Jun 2011
TL;DR: An aircraft roll control system based on design an autopilot that controls the roll angle of an aircraft is modeled using Matlab/Simulink and it is showed that LQR controller deliver the best performance than fuzzy logic controller.
Abstract: In this paper, an aircraft roll control system based on design an autopilot that controls the roll angle of an aircraft is modeled using Matlab/Simulink. Firstly, modeling phase begins with a derivation of suitable mathematical model to describe the lateral directional motion of an aircraft. Then, the Linear Quadratic Controller (LQR) and Fuzzy Logic Controller (FLC) are developed for controlling the roll angle of an aircraft system. Simulation results of roll controllers are presented in time domain and the results obtained with LQR control are compared with the results of FLC. Finally, the performances of roll control systems are analyzed in order to decide which control method gives better performance with respect to the desired roll angle. According to simulation results, it is showed that LQR controller deliver the best performance than fuzzy logic controller.
36 citations
Journal Article•
TL;DR: A comparative assessment of modern and intelligent controllers based on time response specification performance for a yaw control of an aircraft system finds from simulation, LQR controller give the best performance compare to fuzzy Logic Controller.
Abstract: This paper presents a comparative assessment of modern and intelligent controllers based on time response specification performance for a yaw control of an aircraft system. The dynamic modelling of yaw control system is performed an autopilot that controls the yaw angle of an aircraft designed using two control design methods The mathematical model of the system is derived by substituting the known parameters of a standard aircraft in standard equations. The transfer function for the yaw control surface; i.e; rudder is derived and two separate controllers , Linear quadratic controller (LQR) and fuzzy logic controller (FLC) are designed for controlling the yaw angle. The effectiveness of each controllers are tested and verified using Matlab/Simulink platform. It is found from simulation, LQR controller give the best performance compare to fuzzy Logic Controller
28 citations