Finite element modeling method for heterotype honeycomb structure

Abstract

The invention provides a finite element modeling method for a heterotype honeycomb structure, comprising thirteen steps: 1. establishing a cross section geometry model of the heterotype honeycomb structure; 2. generating a central point of the Kth ring honeycomb structure; 3. screening out an intra-domain honeycomb of the Kth ring honeycomb structure; 4. carrying out a step 11 if there is nonexistence of the intra-domain honeycomb in the Kth ring, otherwise carrying out a step 5; 5. generating nodes of each intra-domain honeycomb in the honeycomb structure on the Kth ring; 6. dealing with the nodes of the intra-domain honeycomb; 7. carrying out a step 8 if number of the nodes in the intra-domain honeycomb exceeds 2, otherwise carrying out a step 9; 8. dividing linear elements of the intra-domain honeycomb; 9. returning to carry out the step 5. if the finite element model of the intra-domain honeycomb on the Kth ring honeycomb structure is not completely generated, otherwise carrying out a step 10;10. returning to carry out the step 2, if the finite element model of the intra-domain honeycomb of thehoneycomb structures on all rings is not completely generated, otherwise carrying out a step 11; 11. outputting shell element information; 12.outputting node information; and 13.outputting element set information of the honeycomb structure sticking-joint.

Description

(1) Technical field [0001] The invention provides a finite element modeling method of a special-shaped honeycomb structure, which belongs to the technical field of aviation propulsion. (2) Background technology [0002] The honeycomb structure originated from bionics. In the 1950s and 1960s, the high-performance honeycomb manufacturing technology was mature, and the honeycomb structure was widely used in the aerospace industry. Compared with traditional filling materials, honeycomb structure 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] Generally speaking, there are two traditional analysis methods for the mechanical properties of honeycomb structures: equivalent method and experimental method. The equivalent method uses the t...

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Problems solved by technology

The equivalent method uses the theory of structural homogenization to derive the equivalent mechanical parameters of the honeycomb structure. Its disadvantage is that it is difficult to analyze the complex stress and strain caused by stress concentration and the influence of the cutting boundary of the honeycomb structure on the mechanical properties of the entire structure; while the experimental method only It is difficult to form and develop the design criteria of the honeycomb structure because it can obtain the empirical value of the mechanical properties of the honeycomb structure

[0004] At present, cutting and forming special-shaped honeycomb structures are widely used in engineering, and the structural forces are complex, and the mechanical properties at the boundary have a non-negligible impact on the strength, stiffness and vibration characteristics of the overall structure. Obviously, the traditional equivalent method Therefore, the analysis of mechanical properties of special-shaped honeycomb structures should tend to use finite element method

However, the difficulty of using the finite element method to analyze the mechanical properties of the honeycomb structure is that it is difficult to establish a finite element model of the honeycomb structure. Using the existing finite element preprocessing software to perform finite element modeling of the honeycomb structure can only be done manually, which will cost a lot time and resources, and for some large structures, manual modeling may not even be possible

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