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A Composite Material Layup Scheme Database Construction Method Considering Laminate Compatibility

A composite material and scheme library technology, which is applied in the field of formulation of composite material layup schemes, can solve the problem of not finding the method of building a composite material layup scheme library considering the layup compatibility, so as to achieve rich scheme reference and full design Feasible domain effect

Active Publication Date: 2018-04-03
BEIHANG UNIV
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  • Description
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  • Application Information

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Problems solved by technology

[0004] At present, in view of the compatibility of composite material layup, there is no method for building a composite material layup scheme library considering the compatibility of the layup

Method used

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  • A Composite Material Layup Scheme Database Construction Method Considering Laminate Compatibility
  • A Composite Material Layup Scheme Database Construction Method Considering Laminate Compatibility
  • A Composite Material Layup Scheme Database Construction Method Considering Laminate Compatibility

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Embodiment

[0073] 1. Introduction of structural parameters and composite material layup process

[0074] In order to understand more fully the characteristics of this invention and its applicability to engineering practice, the present invention uses figure 2 Take the aircraft composite skin structure shown as an example to establish a composite material layup scheme library. The aircraft composite skin structure is formed by laying a fabric material symmetrically according to three angles, and the three angles are 0°, -45° and +45° respectively. According to the design plan, the skin structure is divided into 3 ply areas with different thicknesses, from thick to thin, they are respectively zone 1, zone 2 and zone 3. There are composite layup thickness change zones between Zone 1 and Zone 2 and between Zone 2 and Zone 3 of the skin structure, so the composite layup scheme of the skin structure must consider the compatibility of the layup. In addition, from the point of view of the com...

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Abstract

The invention provides a composite material layering scheme library establishing method taking layering compatibility into account. The method comprises the steps of encoding composite material layering schemes by using integers; traversing all combinations and establishing a composite material layering basic scheme library, which is a first-stage composite material layering scheme library; using binary numbers as layer breaking operation codes, and further obtaining a second-stage composite material layering scheme library on the basis of first-stage composite material layering schemes through layer breaking operation; performing layer breaking operation successively to obtain multiple stages of composite material layering scheme libraries. With the method, a composite material layering scheme library meeting the layering compatibility requirement can be obtained; effective transition in thickness changing areas of composite material layering is realized; a feasible layering scheme is provided for composite material layering process design; and foundation is laid for composite material structure optimization design.

Description

technical field [0001] The invention is mainly applicable to the formulation of a composite material layup scheme with one kind of layup material and a layup compatibility problem, and specifically relates to a method for building a composite material layup scheme database considering the layup compatibility. Background technique [0002] In view of the advantages of high specific strength and high specific stiffness of composite materials, the utilization rate of composite material structures in modern aerospace, automobile and other industrial fields is increasing, and the scope of application has gradually expanded from secondary load-bearing structures to primary load-bearing structures. According to reports, the B787 designed and produced by Boeing has a composite material coverage rate of 50% of the entire aircraft structure, and its wing component composite material coverage rate is as high as more than 90%. Compared with the previous traditional metal structure, the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/17G06F2111/04
Inventor 邱志平吕峥王晓军朱静静李晓孙佳丽夏海军
Owner BEIHANG UNIV
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