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Vibration Control of Aircraft Semi-Active Suspension System using PID-Bees Technique

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International Journal of Computer Applications
© 2014 by IJCA Journal
Volume 99 - Number 10
Year of Publication: 2014
Authors:
Ali Reza Toloei
Milad Zarchi
Behrooz Attaran
10.5120/17408-7980

Ali Reza Toloei, Milad Zarchi and Behrooz Attaran. Article: Vibration Control of Aircraft Semi-Active Suspension System using PID-Bees Technique. International Journal of Computer Applications 99(10):14-21, August 2014. Full text available. BibTeX

@article{key:article,
	author = {Ali Reza Toloei and Milad Zarchi and Behrooz Attaran},
	title = {Article: Vibration Control of Aircraft Semi-Active Suspension System using PID-Bees Technique},
	journal = {International Journal of Computer Applications},
	year = {2014},
	volume = {99},
	number = {10},
	pages = {14-21},
	month = {August},
	note = {Full text available}
}

Abstract

The dynamic load and vibration caused by landing impact and the unevenness of runway will result in airframe fatigue, discomfort of crew/passengers and the reduction of the pilot's ability to control the aircraft. The semi-active suspension system can provide good performance of both landing impact and taxi, and has the ability for adapting to various ground and operational conditions. This current paper designs Proportional Integral Derivative controller based on Bees Intelligent Algorithm as the optimization technique for nonlinear model of semi-active landing gear system that chooses damping performance of system at touchdown as object function. Optimal setting of controller parameters to achieve favorable time response using numerical software method based on Bees Algorithm is more simple and more effective than other traditional methods such as Ziegler-Nichols and experimental because it does not need high experience and complex calculations and leads to better results. This research develops nonlinear two-dimensional mathematical model to describe landing gear system with oleo-pneumatic shock absorber and linear tire. Based on this model, the dynamic equations are used to investigate the behavior of an aircraft semi-active landing gear system subject to runway disturbance excitation and the stability conditions of the landing system around static equilibrium position is studied. SIMULINK simulation software is applied to validate the theoretical analysis of system stability. Results of system numerical Simulation with optimized controller using Bees Algorithm in MATLAB software shows that the transmitted impact load to airframe, the vertical vibration of aircraft and time to return static equilibrium position at touchdown are significantly improved.

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