Finite element modeling method of special-shaped honeycomb skin structure

Abstract

The invention discloses a finite element modeling method of a special-shaped honeycomb skin structure, comprising the following steps of: step1, building a section geometric model of the special-shaped honeycomb skin structure; step2, generating a honeycomb central point of a certain ring; step3, screening intra-domain honeycombs; step4, executing step15 if no intra-domain honeycomb exists in the current ring, otherwise, executing step5; step5, generating a node for the intra-domain honeycomb in the current ring; step6, processing the honeycomb node; step7, executing step8 if the number of the intra-domain nodes is more than 2, otherwise, executing step13; step8, dividing linear units of the honeycomb; step9, dividing the corresponding skin units; step10, executing step11 if the number of skin unit nodes is 0, otherwise, executing step13; step11, outputting information of the skin units; step12, outputting information of skin nodes; step13, executing step5 if honeycombs of the current ring are not completely processed, otherwise, executing step14; step14, executing step2 if honeycombs of all rings are not completely processed, otherwise, executing step15; step15, outputting information of the honeycomb units; step16, outputting information of the honeycomb nodes; step17, outputting information of a unit collection in bounding parts of the honeycomb.

Description

(1) Technical field [0001] The invention relates to a finite element modeling method of a special-shaped honeycomb skin structure, belonging to the technical field of aviation propulsion. (2) Background technology [0002] The honeycomb skin structure is composed of two thin and strong panel materials sandwiched by a thick and light honeycomb core. The biggest feature of this type of material is light weight, high specific strength and high specific stiffness. In the 1900s, high-performance honeycomb manufacturing technology has matured, and honeycomb structures are widely used in aircraft, aviation and aerospace industries. Compared with traditional materials, honeycomb skin materials have the advantages of low density, low thermal conductivity, high specific stiffness, high specific strength, large compressive strain, good energy absorption characteristics, high designability, etc., and are suitable for the aerospace field. An important composite material. [0003] At pr...

AI Technical Summary

Problems solved by technology

The equivalent method uses the structural homogenization theory to derive the equivalent elastic parameters of the honeycomb skin structure. Its disadvantage is that it is difficult to analyze the influence of complex stress and strain caused by stress concentration.

The experimental method can only obtain the empirical value of the material properties of the honeycomb skin structure, and it is difficult to establish the design standard of the honeycomb skin structure

[0004] Obviously, the traditional equivalent method and experimental method are difficult to meet the analysis needs of the mechanical properties of the honeycomb skin structure, so the analysis of the mechanical properties of the honeycomb skin structure should tend to use the finite element method

However, the difficulty of using the finite element method to analyze the mechanical properties of the honeycomb skin structure is that the honeycomb skin structure, especially the special-shaped honeycomb skin structure with complex cutting boundaries, is difficult to establish a finite element model. Finite element modeling of honeycomb skin structures can only be done manually, which consumes a lot of time and resources, and for some large structures, manual modeling is not even possible

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