Abstract
In the modern era the aerospace technology plays a very significant role in the development of the mankind. The evolution of the light weight aircraft has a special focus in the present industrial trends. Several research organizations are in the process of developing Light Weight Aircraft, which is ideally suited for civil transport, aerial survey, training etc. This Light Weight Aircrafts are to be designed accordance to Federal Aviation Regulations part 23 (FAR-23). This paper deals with the analysis of the Aircraft's Fuel Tank under variable conditions. The analysis of aircraft fuel tank is carried out for different inertia load cases in addition to a test pressure of 3.5psi (24KPa), to validate whether the structure is safe or not. The size of the fuel tank has been taken as per the FAR-23 guidelines. The Finite Element Analysis is carried out to arrive at stresses and displacements in critical components using the Ansys software. The maximum shear stresses included are observed to be much less than the Yield strength of materials.
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