Accurate Stick Model Development for Static Analysis of Complex Aircraft Wing-Box Structures

AIAA Journal ◽  
2009 ◽  
Vol 47 (9) ◽  
pp. 2063-2075 ◽  
Author(s):  
Mostafa S. A. Elsayed ◽  
Ramin Sedaghati ◽  
Mohammed Abdo
Keyword(s):  
Static Analysis ◽  
Model Development ◽  
Aircraft Wing ◽  
Box Structures ◽  
Stick Model ◽  
Wing Box

Static and Dynamic Analysis of Aluminium Composite in Wing Section Using ANSYS

2014 ◽  
Vol 984-985 ◽  
pp. 367-371
Author(s):  
E.S. Esakkiraj ◽  
S. Anish ◽  
V. Anish
Keyword(s):  
Static Analysis ◽  
Minimum Weight ◽  
Equivalent Stress ◽  
Model Analysis ◽  
Aluminium Composite ◽  
Aircraft Wing ◽  
Lower Stress ◽  
Static And Dynamic Analysis ◽  
Finite Element Software ◽  
Composite Wing

The cold of this cardboard is to abstraction and analyze the amount accustomed accommodation and weight accumulation of blended aircraft (Aluminium Silicon Carbide) addition with that of Aluminium wing and appropriately access the acceptable aircraft addition of minimum weight accomplished of address a accustomed changeless amount after failure. And also this paper presents a model and a static analysis of the aircraft wing, using the finite element software ANSYS. The geometry was created in CATIA V5 R18 and imported. The static and model analysis are carried out in analysis software ANSYS. The result of from the static analysis refers to the total deformation, equivalent stress, shear stress and shear intensity on the skin of the aircraft wing. The model analysis will be carried out to find out the first six modes of vibrations and the different mode shape in which wing can deform without the application of load. Compared to the conventional Aluminium wing, the hybridized composite wing experience far lower stresses and the aircraft wing weight nearly 40% and 50% lower stress.

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