Buckling Analysis of Fuselage Frame Using CAD/CAM Software

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Dr. M. Satheesh, Mr. Arun M P

Abstract

The objective of this project is to study the strength of an aircraft fuselage when subjected to buckling due external load acting on it for different materials and composites. Literature survey designates some structural problems due to the external loads leads to this work. This involves design of an aircraft fuselage which has been modeled using CATIA and buckling analysis using ANSYS. This briefly explains the basics of the aircraft structures, composites, finite element method and its application using ANSYS. The analysis is carried out in ANSYS. Composite materials are used for the production of fuselage and that have very high range of load carrying capacity. From this work it is clear that there is a tremendous progress in the buckling load carrying capacity. To felicitate as a research,incorporated fuselage of an aircraft that would utilize the benefits of designing software, and structural analysis using ANSYS Software to designate the buckling analysis under external loads.

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How to Cite
, D. M. S. M. A. M. P. (2017). Buckling Analysis of Fuselage Frame Using CAD/CAM Software. International Journal on Future Revolution in Computer Science &Amp; Communication Engineering, 3(11), 108–111. Retrieved from http://www.ijfrcsce.org/index.php/ijfrcsce/article/view/274
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