Buckling Analysis on Aircraft Fuselage Structure Skin

  Joseph Clint,  Santhosh Kumar,  Nazumuddin Shaik

Fuselage buckling of a stiffened composite cylinder is a very complex phenomenon that involves complex interactions between the skin and the stiffeners. Considering different configurations of the skin and stiffener, different types of buckling failure modes and failure loads are observed in stiffened cylinders. In this work failure modes and the buckling loads of stiffened composite cylinders under uniaxial loading condition is investigated by using analytical and experimental approaches. Initially, a developed model for buckling problem of an isogrid stiffened composite cylinder. In these models the stiffness contributions of the stiffeners is computed by analyzing the moment and force effect of the stiffener on the unit cell. The equivalent stiffness of the stiffener/shell panel is computed by superimposing the stiffness contribution of the stiffeners and the shell. Once the equivalent stiffness parameter is determined for the whole panel buckling load is calculated using the energy method. A 3-D finite-elements model was also built which takes into consideration the exact geometric configuration and the orthotropic properties of the stiffeners and the shell. Based on finite-elements model, a discussion is made on the different buckling failure modes observed. The results of these three types of analysis methods are compared and comments are made on the reliability of the analytical models developed and finally a parametric study was carried out and general conclusions were drawn regarding the optimum configurations of the different parameters of the grid-stiffened cylinder.

Keywords- buckling analysis, fuselage, stiffened composite cylinder, isogrid

Unique Identification Number - IJEDR1404015
Page Number(s) - 3461-3474
Pubished in - Volume 2 | Issue 4 | Dec 2014
DOI (Digital Object Identifier) -   
Publisher - IJEDR (ISSN - 2321-9939)

  Joseph Clint,  Santhosh Kumar,  Nazumuddin Shaik,   "Buckling Analysis on Aircraft Fuselage Structure Skin", International Journal of Engineering Development and Research (IJEDR), ISSN:2321-9939, Volume.2, Issue 4, pp.3461-3474, Dec 2014, Available at :http://www.ijedr.org/papers/IJEDR1404015.pdf