Mohammad Ghalandari¹, Ibrahim Mahariq², Farhad Ghadak³, Oussama Accouche², Fahd Jarad^4,5,*

CMC-Computers, Materials & Continua, Vol.70, No.3, pp. 5569-5581, 2022, DOI:10.32604/cmc.2022.020884 - 11 October 2021

Abstract In aircraft wings, aileron mass parameter presents a tremendous effect on the velocity and frequency of the flutter problem. For that purpose, we present the optimization of a composite design wing with an aileron, using machine-learning approach. Mass properties and its distribution have a great influence on the multi-variate optimization procedure, based on speed and frequency of flutter. First, flutter speed was obtained to estimate aileron impact. Additionally mass-equilibrated and other features were investigated. It can deduced that changing the position and mass properties of the aileron are tangible following the speed and frequency of More >

I.S.Hwang, W.Kang

The International Conference on Computational & Experimental Engineering and Sciences, Vol.19, No.2, pp. 37-38, 2011, DOI:10.3970/icces.2011.019.037

Abstract Recently composite materials are widely used in the building of transport airplanes. The first significant application of composite materials in commercial transports was an all composite rudder for A300/310 by Airbus in 1983. In 1985, Airbus introduced a composite vertical tail fin in the same airplanes. With the success of A300/310, Airbus introduced a full composite tail structure for A320. The composite weight of A320 is totaled to 15% of structure weight. In the late of 1970, NASA and major airframe companies such as Boeing, Lockheed, MD started the ACEE program. The main goal of… More >

Chyanbin Hwu^1,2, Mengchun Yu¹

CMES-Computer Modeling in Engineering & Sciences, Vol.67, No.2, pp. 151-174, 2010, DOI:10.3970/cmes.2010.067.151

Abstract A comprehensive finite element model incorporating the features of comprehensive wing model and finite element method is developed in this paper. This new model extends the applicability of comprehensive wing model from uniform composite wings to tapered composite wings. It preserves the simplicity of one-dimensional finite element but performs like three-dimensional finite element for wing structural analysis. To verify its accuracy and show its efficiency, this model which is applicable to the general dynamic analysis is reduced to two simple cases: static analysis and free vibration analysis. Based upon the reduction results for static and More >