Method for analyzing interlaminar damage of composite material laminate

Abstract

The invention discloses a method for analyzing interlaminar damage of a composite material laminate. The degree of freedom of an auxiliary node of a combined interface unit is condensed out by deducing a rigidity equation of the combined interface unit, so that the combined interface unit is a whole in a finite element model and only has eight main nodes. By the combined interface unit and the finite element model, a simulation result is relatively good; a curve obtained by calculation is basically overlapped with a test curve on a linear segment and is consistent with the tendency of the test curve on a falling segment behind a peak value; simulation of the start of the interlaminar damage and simulation of a damage evolution process accord with the reality; and a load peak value obtained by calculation is 62.8 N, a test value is 63.1 N, and the error is -0.4 percent. Compared with the prior art, the method has the characteristics of small calculation scale and high calculation efficiency; and furthermore, the combined interface unit has a thickness and is easy to implement compared with a cohesion unit with zero thickness during pretreatment modeling.

Description

technical field [0001] The invention belongs to the field of computational mechanics, and in particular relates to a method for calculating and simulating interlaminar damage of composite material laminates. Background technique [0002] Composite laminates have been widely used in many fields, especially in aerospace structures. A laminate is a structural panel composed of multiple layers of single-layer boards bonded together to form a whole, and each single-layer board is called a sub-layer. According to the needs, the main direction of the material of the single-layer board can be laid in different directions and in different orders to obtain laminated boards with different mechanical properties, so the mechanical properties of the laminated boards can be designed. Interlaminar delamination is one of the main damage forms of laminates. The interlaminar strength is weaker than the in-plane strength, which makes laminates prone to interlaminar damage, especially under imp...

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Problems solved by technology

Compared with the plate and shell element, the solid element has a large amount of calculation. When the mesh is very fine, the calculation scale is very large, which limits the engineering application prospect of the CZM method.

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