Engineering optimization method for adjusting composite material layering

A composite material and engineering optimization technology, which is applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of focusing on one thing and losing another, and achieve the effect of reducing the probability of modification, reducing the amount of data, and improving work efficiency

Inactive Publication Date: 2013-11-20
AVIC SAC COMML AIRCRAFT
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Problems solved by technology

And due to the consideration of various professional factors involved in the adjustment process, the ad

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  • Engineering optimization method for adjusting composite material layering
  • Engineering optimization method for adjusting composite material layering
  • Engineering optimization method for adjusting composite material layering

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Embodiment

[0055] Embodiment: The present invention comprehensively analyzes the structural features of the composite material layup storehouse and composite material parts when carrying out multi-thickness area composite material laminate layup design, so as to obtain the layup that meets the professional requirements such as structure, strength, and manufacturing. layer design results.

[0056]In order to realize the above-mentioned technical solution, the present invention includes a ply ratio adjustment and optimization method and a directional ply stack adjustment method. The ply ratio adjustment and optimization method is based on the initial ply data of the current structure of the composite material laminate part input by design, including The division of the ply area, the total number of ply layers in each area, and the number of ply layers at each angle in each area, with the minimum change in the ply angle ratio difference AML index of the overall structure as the optimization ...

example

[0122] According to the practice of an international civil aircraft project, the original lay-up design scheme shown in Figure 7(a), the result of the optimization method of the present invention, and the result of manual adjustment in the real product are compared as shown in Figure 7(b); Figure 8 Shown is a comparison of the safety margins of the two. The results show that the two have the same level of safety margin, but the work efficiency is increased by 10 times, and the designer does not need a high level of experience.

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Abstract

The invention discloses an engineering optimization method for adjusting composite material layering, and belongs to the technical filed of composite materials. The method comprises a layering proportion adjustment optimization method and an orientation layering stacking adjustment method. The layering proportion adjustment optimization method comprises the steps as follows: on the basis of initial layering data of a current structure of a composite material laminated board part, an AML (assembly micro library) index of a layering angel proportion difference of an integral structure is changed and minimized to be an optimization objective, by means of a planning solution calculation method, layering proportion data which are compatible mutually are obtained; then the layering proportion data obtained with a layering proportion adjustment optimization method are taken as inputs; and an orientation layering stacking adjustment method is performed, so that final layering data used for manufacture is obtained. According to the method, various design possibilities are analyzed through a computer magnanimously, and insufficient experience of the designer is made up; the working efficiency is improved, the design working hours are saved; and at the same time, according to specific project requirements, restricted conditions are changed, results are acquired in a short time, the confidence level of the output result is increased, and the design risks are reduced.

Description

technical field [0001] The invention is an engineering optimization method for adjusting the layup of a composite material laminate structure. Background technique [0002] At present, the ply adjustment of composite laminate structures is mainly performed manually by designers according to relevant design criteria, which takes up a lot of time for designers. Moreover, since most of the design principles of composite layup are qualitative principles, the design quality of layup adjustment depends entirely on the experience level of the designer. Moreover, it is difficult for the designer to judge whether the adjustment results are good or bad during the adjustment process, and they can only wait for the follow-up strength check. This often leads to several rounds of iterations, causing delays in design nodes. [0003] During the technology transfer process of the C-series central wing box with Bombardier and Spain's AERNNOVA in 2010, a foreign designer with ten years of ex...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 苌伟鹏方采文李同杨学萌薛大鹏张树军何续斌
Owner AVIC SAC COMML AIRCRAFT
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