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A lay-up method for vertically and horizontally reinforced frame structures based on rtm forming composite materials

A composite material and lay-up technology, which is applied in the field of composite material liquid forming, can solve the problems of unreliable bonding between ribs and wall panels, precision deviation, etc., and achieve the effect of overcoming unreliable bonding

Active Publication Date: 2022-04-08
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In order to solve the above-mentioned technical problems, the present invention proposes a layering method based on RTM forming composite material vertically and horizontally reinforced frame structure, which can effectively solve the problems of unreliability and deviation of precision at the joint between ribs and wall panels

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  • A lay-up method for vertically and horizontally reinforced frame structures based on rtm forming composite materials

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Embodiment 1

[0023] As the basic embodiment of the present invention, with reference to the description attached figure 1 , the present invention comprises a kind of laying method based on RTM forming composite material vertically and horizontally reinforced frame structure, comprising the following steps:

[0024] a. First, plan the laying number N of sizing agent-loaded fabric 5 according to the wall thickness of the workpiece, where N=theoretical wall thickness of the workpiece / thickness of single-layer loaded fabric, and N=8 in this embodiment. Secondly, the laying direction of the continuous fiber layer is selected according to the force of the part, so that the direction of the continuous fiber layer is parallel to the direction of the force, that is, the direction of the ribs formed by the large unit 2.

[0025] b. Select the smallest block unit 3 separated by ribs for laying, the number of laying layers is M, assuming M=2. In this embodiment, there are nine small block units 3. Af...

Embodiment 2

[0028] As the best embodiment of the present invention, the present invention includes a layering method based on RTM forming composite material vertically and horizontally reinforced frame structure, comprising the following steps:

[0029] a. According to the wall thickness of the part, the number of laying layers N of the sizing agent-loaded fabric 5 is planned, and the N=the theoretical wall thickness of the part / the thickness of the single-layer load fabric; and the continuous fiber laying is selected according to the force of the part. direction, so that the direction of the continuous fiber layup is parallel to the direction of the force.

[0030] b. Select the smallest block unit 3 separated by ribs for laying, the number of laying layers is M, and after the small block unit 3 is laid up, proceed to the adjacent large block unit with the same direction as the continuous fiber laying 2 for stacking, and the number of stacked layers is N / 2-M. Among them, the triangular ...

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Abstract

The present invention relates to the technical field of composite material liquid molding, in particular to a layering method based on RTM forming composite material longitudinally and horizontally reinforced frame structure, comprising the following steps: determining the number of laying layers of the sizing agent-loaded fabric and continuous fiber laying For the laying direction, the laying up of the composite material frame structure follows the idea of ​​"large and small block units are nested step by step". The ribs are continuous. The laying method can effectively solve the problems of unreliability and precision deviation at the joint between the rib and the wall board.

Description

technical field [0001] The invention relates to the technical field of composite material liquid forming, in particular to a layer laying method for forming composite material vertically and horizontally reinforced frame structures based on RTM. Background technique [0002] Frame beams and frame structures are classic ideal support structures. Their structures are statically indeterminate or super-statically indeterminate structures composed of ribs, ribs, rods, tubes, etc., and the structures have large spans, strong scalability, material saving, and flexible structures. It has been widely used in the design of aircraft fuselage structure. [0003] With the improvement of composite material manufacturing technology, the application of composite materials on aircraft has gradually shifted from non-load bearing or secondary load bearing components such as radomes, skins, and rudders to corrugated beams, canard box sections, floor beams, and fuselage insulation. Promote it o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/48
CPCB29C70/345B29C70/48
Inventor 罗维张冕崔博程勇徐伟伟
Owner CHENGDU AIRCRAFT INDUSTRY GROUP