Method for post-processing engineering-based composite material laminated board ply after optimization

Abstract

The invention provides a method for processing engineering-based composite material laminated board ply after optimization. After fine design optimization for the composite material laminated board structure, the method can guarantee smoothness and continuation in the thickness of each optimization unit ply of the laminated board after post-processing, so as to eliminate deformed units such as 'bulge' and 'dent', and realize engineering rationalization for the single layer ply thickness and the ply angle of each optimization unit. The method adopts multinomial surface fitting method based on least-squares method to perform surface fitting in the thickness direction for the design optimization result of the composite material laminated board ply, exerts mechanical constraint, then performs equivalent rigidity conversion for all optimization unit in the composite material laminated board after the fitting processing to ensure that the ply angle of each single layer in each optimization unit is converted to four common angles including 0 DEG, + / -45 DEG, and 90 DEG and that the single layer thickness in each optimization unit is converted to designated single layer thickness, under the condition that each optimization unit of the laminated board is guaranteed to have the same rigidity and basically the same mass.

Description

technical field [0001] The invention is an engineering-based post-processing method for optimization of composite material laminate layer laying, which belongs to the field of composite material structure design, and is used in the design optimization of composite material laminate structure. For the purpose of engineering application, the optimization result can be realized by engineering post-processing. Background technique [0002] Composite materials have the advantages of high specific strength, high specific stiffness, low density and designability, and have been widely used in the optimal design of aircraft structures. In the design optimization of composite laminate structures, the design variables involve ply angle, ply thickness and ply position, etc., and the number of design variables is huge. [0003] At present, in the design optimization method of composite material laminates, aiming at the problem of optimization difficulties caused by huge design variables...

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Problems solved by technology

[0006] The present invention designs an engineering-based post-processing method for composite material laminate layup optimization just for the above-mentioned prior art situation, and its purpose is to solve the problem that the composite material laminate structure cannot be used in engineering applications The problem of being realized

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