The application belongs to the technical field of
aviation structure
impact dynamics, and is a kind of
crash dynamics modeling method for simplifying
fuselage frame section structure of an
airplane. A
fuselage frame section model is established by corresponding structural characteristics of the
fuselage frame section, the position and deformation mode of a
large deformation region in the fuselage frame section model are determined, the
large deformation region is simulated into a
plastic hinge, and torque and
axial force performance parameters corresponding to the
plastic hinge are determined. Different gravity fields and initial velocities are given to the fuselage frame section, and the response of the
plastic hinge of the fuselage frame section structure at different deformation degrees is calculated. Based on the plastic
large deformation principle, the advantages of simple connection relationship model, fast calculation efficiency and high calculation accuracy of the
finite element method are fully combined, the calculation efficiency of the
crash finite
element analysis of the fuselage frame section of the
airplane is improved, and potential calculation non-convergence problems in the calculation of the plastic large deformation region of the fuselage frame section structure of the
airplane can be avoided, the
design cycle of the airplane structure adaptability is shortened, and the application prospect is great.