Hardware Implementation of Aircraft Landing Controller by Evolutionary Computation and DSP
نویسندگان
چکیده
This paper presents a hybrid control scheme for the aircraft automatic landing system. PID control law is adopted in the controller design. Disturbance adaptive capability is demonstrated through hardware in the loop simulations. The control scheme uses PID controller with evolutionary computation technique. Control gains are selected by real-valued genetic algorithms. Different crossover methods are utilized to improve the performance of conventional automatic landing system. Hardware implementation of this intelligent controller is performed by a DSP with VisSim platform. The proposed intelligent controllers can successfully expand the controllable environment in severe wind shear conditions.
منابع مشابه
Intelligent Computation and Dsp-based Landing Control
This paper presents several digital signal processor (DSP) based intelligent controllers for aircraft automatic landing systems (ALSs). Proportional-Integral-Derivative (PID) control law is adopted in the intelligent controller design. A fuzzy cerebellar model articulation controller (CMAC) is utilized to compensate for the PID control signal. Control gains are selected by evolutionary computat...
متن کاملOptimized Fuzzy Logic for Nonlinear Vibration Control of Aircraft Semi-active Shock Absorber with Input Constraint (TECHNICAL NOTE)
Landing impact and runway unevenness have proximate consequence on performance of landing gear system and conduce to discomfort of passengers and reduction of the pilot’s capability to control aircraft. Finally, vibrations caused by them result in structure fatigue. Fuzzy logic controller is used frequently in different applications because of simplicity in design and implementation. In the pre...
متن کاملMathematical Model and Vibration Analysis of Aircraft with Active Landing Gear System using Linear Quadratic Regulator Technique
This paper deals with the study and comparison of passive and active landing gear system of the aircraft and dynamic responses due to runway irregularities while the aircraft is taxying. The dynamic load and vibration caused by the unevenness of runway will result in airframe fatigue, discomfort of passengers and the reduction of the pilot’s ability to control the aircraft. One of the objectiv...
متن کاملOscillation Control of Aircraft Shock Absorber Subsystem Using Intelligent Active Performance and Optimized Classical Techniques Under Sine Wave Runway Excitation (TECHNICAL NOTE)
This paper describes third aircraft model with 2 degrees of freedom. The aim of this study is to develop a mathematical model for investigation of adoptable landing gear vibration behavior and to design Proportional Integration Derivative (PID) classical techniques for control of active hydraulic nonlinear actuator. The parameters of controller and suspension system are adjusted according to be...
متن کاملOptimization of Aircraft Landing Route and Order: An approach of Hierarchical Evolutionary Computation
This paper focuses on the aircraft landing optimization problem where both the landing routes and the landing order of aircrafts should be optimized to minimize an occupancy time of airport, and proposes its optimization method which is robust to dynamical situations such as weather condition change and other aircrafts’ landing routes change. As a difficulty of this optimization problem, approp...
متن کامل