A post-buckling analysis method for fuselage stiffened panels based on finite element analysis

Abstract

Provided is a post-buckling analysis method for a composite fuselage stiffened wallboard structure based on finite element analysis. The method is based on finite element analysis software to determine a refined finite element modeling technology of the composite stiffened wallboard structure to achieve structural discretization simulation post-buckling analysis. The method introduces a suitable failure criterion to simulate a progressive failure process inside a material in the loading process of the structure; contact constraint is applied at a structural stacking position, the support action between structures is simulated, and geometric and material nonlinear factors are considered to effectively track a pre-buckling and post-buckling equilibrium path and accurately predict the ultimate bearing capacity; by aiming at various failure modes which may occur in the structural load-bearing process, the dimension of the structure is adjusted through iterative parameters such as process conformity, weight conformity and the like under the situation that the design load is satisfied, the lightweight design of the composite stiffened wallboard structure is completed, and the design process integration of the composite is achieved.

Description

technical field [0001] The invention relates to a post-buckling design method of a composite material structure of a civil aircraft, and belongs to the field of structural strength design of a composite material body. Background technique [0002] The design, manufacture and test technology of the reinforced panel structure of civil aircraft fuselage is one of the key technologies in the process of systematic development of the whole aircraft. At present, under the premise of ensuring reliability and comfort in the structural design of civil aircraft composite materials in China, the lightweight design of products has attracted the attention of designers. In actual use, as a typical structural form, the composite material reinforced panel structure is often subjected to compressive loads, and buckling instability is a common failure mode. The research shows that the initial buckling of the composite reinforced panel structure is not equal to failure, and the failure load of...

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Problems solved by technology

The main reason is that designers have not thoroughly studied the mechanical analysis methods and failure modes of composite material structures.

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