A.R Toloei - Department of Aerospace Engineering, University of Shahid Beheshti, Tehran, Iran
M Zarchi - Department of Mechanical Engineering, university of Shaid Chamran, Ahwaz, Iran
B Attaran - Department of Mechanical Engineering, university of Shaid Chamran, Ahwaz, Iran

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 bees optimization algorithm by minimizing body acceleration objective function. The results of numerical simulation indicates that the active landing gear system based on bees intelligent algorithm increases passengers and ride comfort and structure fatigue life by decreasing displacement, acceleration and load transmitted to airframe and shock absorber system significantly about 70% and 80% averagely compared to passive performance during touchdown phase with sine wave runway disturbance.

PID Classical ControllerBees Intelligent Optimization AlgorithmHydraulic Nonlinear ActuatorActive PerformanceNumerical Simulation