BUCKLING ANALYSIS OF AIRCRAFT STIFFENED PANEL CYLINDRICAL SHELLS

Amara Ramanjaneyulu, Ganapathi Ashok, P V Varaprasad

Abstract


For past decades devolopment of composite material had brought tremendous change in  AirFrames and Missiles. Due to composite stiffened panels implementation speed, distance and life of the Airframes and missiles had increased. During integration the composite cylindrical shell structure is provided with cutouts which reduce the strength of composite cylindrical shell and are porne to buckling. By adding Reinforcement around cutout will lead to improvement of strength. Generally T-section and I-section stiffened panel are used, but there is a disadvantage of using T-section, it can’t resist to deformation. So we designed an I-section stiffened panel (because I-section is more resistant to deformation) in CATIA and analysis in ANSYS. We considered three types of analysis in ANSYS, Modal analysis, Static analysis, Harmonic analysis respectively and also we considered two materials, one is aluminum and the other is carbon fiber. Aluminum is the common element used in the design of aircraft, but Carbon fiber is recently being used in aircrafts.


Keywords


1st Principle Stress; 2nd Principle Stress; Von Mises Stress;

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