Laminated board structural damage simulating method based on elastobrittle damage mode

A technology of structural destruction and simulation methods, applied in special data processing applications, instruments, electrical digital data processing, etc., to achieve the effect of avoiding dependence

Inactive Publication Date: 2018-02-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for simulating the damage of a laminate structure ba...

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  • Laminated board structural damage simulating method based on elastobrittle damage mode
  • Laminated board structural damage simulating method based on elastobrittle damage mode
  • Laminated board structural damage simulating method based on elastobrittle damage mode

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[0043] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a laminated board structural damage simulating method based on an elastobrittle damage mode, and relates to the technical field of analysis of composite material laminated boards. The laminated board structural damage simulating method based on the elastobrittle damage mode comprises the following steps: step one, dividing a laminated board into a plurality of entity unit bodies in the thickness direction, taking each unit body as an analyzed object, and describing damage features of a single layer of composite material by symmetric second-order damage tensor; introducing a damage mode of a material integration point into numerical calculation, introducing an equivalent displacement concept, and taking a non-linear evolution law in an exponential form as a damage evolution model of the material integration point; calculating a damage variable evolution law according to the equivalent displacement concept and the non-linear evolution law which are introduced in the step two; step four, calculating damage rigidity of a single layer of unit body; and step five, constructing a constitutive relation between the laminated board and a damaged fiber reinforced composite material. The laminated board structural damage simulating method based on the elastobrittle damage mode has the advantage that dependence to tests and experiences of researchers is avoided.

Description

technical field [0001] The invention relates to the technical field of progressive damage analysis of composite laminate structures, in particular to a damage simulation method for laminate structures based on an elastic-brittle damage model. Background technique [0002] With a large number of applications of composite material structures in the fields of aviation, aerospace, navigation and construction, their applications are becoming more and more complex. Taking aviation as an example, looking at the development trend of international civil aircraft manufacturers using composite materials in civil aircraft structures, it can be found that whether it is Boeing or Airbus, the application of composite materials is gradually shifting from secondary load-bearing structures to large main bearings. power structure transition. Compared with the secondary load-bearing structure, the main load-bearing structure bears a larger load, and the thickness of its parts is much thicker t...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 曹效昂杨杰
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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