Numerical simulation method for continuous layup of composite material at right angle

Abstract

The present invention relates to the technical field of aircraft structure design, and specifically provides a numerical simulation method for continuous layering of right-angle turns of composite materials. Firstly, a 3D shell geometric model of composite materials is established, including horizontal bead areas, corner areas and vertical bead areas, and then Establish the Cartesian coordinate system of the horizontal bead area and the Cartesian coordinate system of the vertical bead area, and establish the cylindrical coordinate system of the corner area, and then define the composite layer properties of the horizontal bead area, corner area and vertical bead area respectively, and according to the law To adjust the reference direction of the layup datum in the above three areas respectively, select the coordinate system corresponding to the layup in the above three areas, and ensure that the layup in the above three areas is continuous and the angle of the same layup is consistent, and then the composite material 3D shell geometry The model is meshed, constraints and loads are imposed on the geometric model to obtain a finite element model, and finally the static strength field variables of the finite element model are obtained.

Description

technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to a numerical simulation method for quarter-turn continuous layering of composite materials. Background technique [0002] The structural characteristics of the R zone at the junction of the vertical edge plates of the composite laminate structure widely exist in various aircraft composite parts, such as stringers, ribs and beams. There is a turning lay of the prepreg in the R area, and the coordinate system will change. In the general overall finite element analysis, each independent surface refers to its own rectangular coordinate system, and the problem of rotation angle and layup continuity is not considered, and the output results cannot reflect the reality. The stress situation of the structure, such as the composite wing rib of a certain type of aircraft, due to the early delamination of the edge strip and the corner area of ​​the web, led to the abandonmen...

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Problems solved by technology

There is a turning lay of the prepreg in the R area, and the coordinate system will change. In the general overall finite element analysis, each independent surface refers to its own rectangular coordinate system, and the problem of rotation angle and layup continuity is not considered, and the output results cannot reflect the reality. The stress of the structure, such as the composite wing rib of a certain type of aircraft, due to the early delamination of the flange and the web corner area, the composite wing rib scheme was abandoned

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