Structural Evaluation of Aircraft Stiffened Panel

A structure has to be designed to ensure the safety throughout the service life. To ensure this, the designer should first understand how the structure behaves with respect to the material, sectional and loading conditions. In the modern aircraft structural design, the high accuracy design to obtain the highest efficiency of the structure is possible through the consideration of selective design properties in particular to perform the analysis. Stiffener or longeron or stringer is a thin metal strip that is used as a supporting member in fuselage and wing. When we consider the issue i. e. resistance of the aircrafts skin towards the loads applied on it, due to frailty the aircraft skin is easily deformed. In order to solve this problem we designed a stiffened panel which can endure to deflection and stress levels. By changing the stiffened panel sections and by changing the material of the skin, the aircraft skin can withstand the deformation. In current study a representative stiffened panel from a transport aircraft is considered for the evaluation. The structural analysis of the stiffened panel will be carried out with the different cross-sections of the stiffeners with the varying material types. Von-misses stress and the deformation is determined with the varied cross-sections with change of materials to determine the better section for the development of the aircraft structural strength. The study includes material properties to sustain the loads induced with the cross-sectional behavior of the stiffened panels. This paper evaluates the robust material to use and to find out the best capable section for the Stiffened panel.