Research of typical frame section of a fuselage against crash

Abstract This study focused on a typical fuselage section of a certain type of civil aircraft. Optimization of parameters such as the angle of floor-mounted columns, column structural forms, and column stiffness was conducted. Finite element models were developed for each parameter configuration. Commercial software was used to simulate the crash process of the fuselage section. By analyzing key crashworthiness parameters such as fuselage deformation and acceleration at the floor, it was determined that the fuselage section exhibited minimal acceleration overload when the column angle was 20°. The optimal design for crashworthiness was found to be the H-shaped column with moderate stiffness.