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Method for manufacturing panels of complex geometries in prepreg composites

A geometry, composite technology, applied in chemical instruments and methods, household components, applications, etc., that can solve problems such as increased probability of cavities and stress concentration points, unsatisfactory, and damage to the mechanical and structural integrity of the workpiece, Achieving the effect of a high production chain

Inactive Publication Date: 2011-12-14
AIRBUS OPERATIONS SL
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Considering the above factors, the direct application of conventional thermoforming and pressing techniques to panels of complex geometries proved to be unsatisfactory
Furthermore, even if the preformed block has sufficiently small dimensions and has an open profile, it is still impossible to obtain some workpieces with sufficiently complex shapes or panels of complex geometries with precision in terms of dimensional tolerances using this conventional technique, because during forming The appearance of folds and creases will inevitably arise from the twisting action of the plies of prepreg and fibers
These defects in dimensional tolerances can lead to other inducing defects that compromise the mechanical and structural integrity of the workpiece to be obtained, such as vulnerability to prepreg delamination due to increased probability of cavities and stress concentration points of

Method used

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  • Method for manufacturing panels of complex geometries in prepreg composites
  • Method for manufacturing panels of complex geometries in prepreg composites
  • Method for manufacturing panels of complex geometries in prepreg composites

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Embodiment Construction

[0091] Figure 1a , Figure 1b and Figure 1c A complex geometry panel 1 is shown, to which the present invention relates. The complex geometry panel 1 includes some undulations 3 such as grooves ( Figure 1b ) or funnel-shaped ( Figure 1c ), with or without flat region2. in the Figure 1a and Figure 1b Represented generally in is a contour 4 close enough to the undulating neighborhood of the panel 1 of complex geometry to be obtained, within which contour there may be stacked broken lines.

[0092] exist figure 2 , it can be seen how, in a preferred embodiment, during the stacking phase I, the unrolling of the prepreg on the mold 13 is carried out by means of fiber lay-up techniques. figure 2 The head 5 of the fiber placement machine is shown during unrolling of the prepreg. The head 5 comprises, in a simplified manner, a collimator 6, which brings together the prepreg fibers into a ribbon, some guide rollers 7, a cutter 8 and pinch rollers 9. Other auxiliary elem...

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Abstract

The method comprises: a first stage in which the layers of the prepreg are spread over a mold having cavities corresponding to reliefs (3) of the complex geometry panel (1) to be obtained, the layers of prepreg presenting lines of discontinuity (12) In the vecinity of the reliefs (3); a second stage in which the stack (11) is done by application of a cycle of pressure and temperature; and a third stage of finishing of the panel to be obtained, comprising the curing of the prepreg.

Description

technical field [0001] The general object to which the present invention relates is to provide a method of manufacturing structural panels with complex geometries and light weight, ensuring panels obtained with maximum mechanical and structural integrity and maximum precision in terms of dimensional tolerances. Background technique [0002] In the present invention, a "panel" is understood as a workpiece whose thickness is very small compared to the surface on which it extends or the surface of a feature, which can have an open or closed profile (for example, a cylinder or a cone is considered a closed contour surface). [0003] The attainment of the lightness of the panels and their required structural functions leads to the application of the invention to panels manufactured in pre-impregnated composite material, as stated in the title of this specification. [0004] Prepregs basically consist of a set of reinforcing fibers impregnated in a resin matrix and combined into ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/46B29C70/34B32B7/08
CPCB29D99/0014B32B3/10B29C70/46B32B5/26B32B3/30B32B7/08B32B7/12B32B2260/021B32B2260/046B32B2307/514B32B2607/00B32B7/03B29C70/304B29C70/461B29C70/345
Inventor D.桑切斯-布鲁内特阿尔瓦雷斯
Owner AIRBUS OPERATIONS SL
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