Elastic Dynamic FEM Numerical Analysis Of Aerocraft Folded-wing

The folded-wing design technique, are applied widely in the aircraft armaments, which is a most favorite scheme to solve contradictions of geometric space. The design principles of the folded-wing mechanisms and the working reliability need to be supported by the accurate calculation and refined analysis, so as to get to know about the work course and evaluate the effects of technical parameters.The finite element method (FEM) has become an important means in modern engineering designs, which is used in many fields, such as structural stress analysis, deformational stiffness analysis, mechanic failure analysis, dynamic process analysis, heat analysis, electromagnetism filed analysis and so on. With the rapid development of the computer techniques, the finite element method and its application would be used in more and more engineering design fields.This Thesis is a FEM analysis of opening process of the folded horizontal tail wing of some aircraft, and the work includes modeling the detailed mechanic assembly of the tail wing, and computing its elastic dynamic process by large-scale FEM software system, ANSYS and LS-DYNA3D, as well with the postprocessor tool-LSPOST to take the computational results into visualization. In order to check up the elastic dynamic numerical simulation, this thesis also creates the rigid-body dynamic model of the tail wing and gets its comparative opening time. With these work groundings, the working stress levels for individual component of the folded-wing are evaluated.The thesis also involves some detailed techniques come across in the numerical simulation process of elastic dynamic FEM analysis, and remarks the theoretical foundation and applications to them, which covers mass scaling, hourglass deformation mode and dimensional compatibility.