Crash simulation analysis of an aircraft fuselage section with an auxiliary fuel tank

Abstract Aircraft crash analysis and design methods are important aspects of aircraft design. A full-scale finite element model of the B737-200 fuselage section containing 6 frame sections with an auxiliary fuel tank is developed using the explicit finite element code, Pamcrash, to perform simulated analysis. The simulation result outputs the fuselage’s maximum deformation. Seat tracks’ acceleration responses are compared with the drop test to determine the method’s correctness. This method is then applied to simulate the crash of an airplane fuselage section with an auxiliary fuel tank in the cargo compartment at a velocity of 9.144m/s to provide reference for engineering applications.