Oscillation Control of Aircraft Shock Absorber Subsystem Using Intelligent Active Performance and Optimized Classical Techniques Under Sine Wave Runway Excitation (TECHNICAL NOTE)

Abstract

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.