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A method for forming an integral skeleton of a variable-thickness composite material and a forming mold thereof

A technology of composite materials and molding methods, which is applied in the field of integral molding of resin-based structural composite materials, can solve problems such as the inability to realize the integrated molding of variable-thickness skeletons, large spans, etc., to ensure product structure quality, ensure bonding strength, and optimize layering process The effect of the design

Active Publication Date: 2021-02-09
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The overall skeleton thickness of the above-mentioned structure (determined by the height of the vertical plate) has a large span and has a closed back-shaped lattice. The existing molding process cannot realize the integrated molding of the variable-thickness skeleton

Method used

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  • A method for forming an integral skeleton of a variable-thickness composite material and a forming mold thereof
  • A method for forming an integral skeleton of a variable-thickness composite material and a forming mold thereof
  • A method for forming an integral skeleton of a variable-thickness composite material and a forming mold thereof

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Embodiment 1

[0059] Such as figure 1As shown, the present embodiment provides a kind of overall skeleton structure that is used for aircraft wing, and this overall skeleton structure is made of upper frame 1, lower frame 2 and multiple sets of vertical plates 3 with different heights, wherein upper frame 1 is made of many The first frame bars 11 form a multi-grid structure, and the lower frame 2 is surrounded by a plurality of second frame bars 21 to form a multi-grid structure. The first frame bars 11 and the second frame bars 21 correspond one-to-one, and the corresponding first frame bars A vertical plate 3 is arranged between the frame bar 11 and the second frame bar 21, and forms a vertical cross-section as an I-shaped structure. The upper surface of the upper frame 1 and the lower surface of the lower frame 2 are double-curvature surfaces; the overall skeleton The structure adopts carbon fiber reinforced Shuangma resin-based composite material. The maximum length of the skeleton is 2...

Embodiment 2

[0073] Such as Figure 5 As shown, this embodiment provides a kind of overall skeleton structure that is used for aircraft empennage, and this overall skeleton structure is made up of upper frame 1, lower frame 2 and multiple sets of vertical plates 3 with different heights, wherein upper frame 1 is made of a plurality of the first A frame bar 11 forms a multi-grid structure, and the lower frame 2 is surrounded by a plurality of second frame bars 21 to form a multi-grid structure. The first frame bar 11 and the second frame bar 21 correspond one-to-one, and the corresponding first frame bar A vertical plate 3 is provided between the bar 11 and the second frame bar 21, and forms a vertical cross-section as an I-shaped structure. The upper surface of the upper frame 1 and the lower surface of the lower frame 2 are double-curvature surfaces; the overall skeleton structure Using carbon fiber reinforced high temperature resistant epoxy resin-based composite material, the maximum le...

Embodiment 3

[0087] Such as Figure 6 As shown, the present embodiment provides a kind of integral skeleton structure that is used for aircraft wing test piece, and this integral skeleton structure is made of upper frame 1, lower frame 2 and the riser plate 3 of multiple groups of different heights, wherein upper frame 1 is made of A plurality of first frame bars 11 form a multi-grid structure, and the lower frame 2 is surrounded by a plurality of second frame bars 21 to form a multi-grid structure. The first frame bars 11 and the second frame bars 21 correspond one-to-one, and the corresponding A vertical plate 3 is arranged between the first frame bar 11 and the second frame bar 21, and forms a vertical cross-section as an I-shaped structure, and the upper surface of the upper frame 1 and the lower surface of the lower frame 2 are double-curvature surfaces; The overall skeleton structure adopts carbon fiber reinforced Shuangma resin-based composite material. The maximum length of the ske...

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Abstract

The invention discloses a method for forming an integral skeleton of a variable-thickness composite material and a forming mold thereof, and belongs to the technical field of integral forming of a resin-based structural composite material. The method includes: preparing a forming mold, the silicone rubber mold in the forming mold corresponds to the vertical plate one by one, the positioning core is used to fill the gap between two adjacent silicone rubber molds, the upper end of the side baffle is fixed to the upper cover plate, and the lower end Fix with the lower cover plate to form a skeleton cavity; use hot-melt prepreg layup to form multiple first prefabricated bodies corresponding to multiple vertical plates on the silicone rubber mold, and form multiple first prefabricated bodies on the upper cover plate corresponding to the upper frame A second prefabricated body, a third prefabricated body corresponding to the lower frame is formed on the lower cover plate; assembled and fixed, solidified, and the mold is removed to obtain the overall skeleton of the variable thickness composite material. The present invention can realize the integrated overall molding of the whole skeleton of the composite material with variable thickness, and the quality and dimensional accuracy of the formed whole skeleton meet the use requirements.

Description

technical field [0001] The invention belongs to the overall molding technology of resin-based structural composite materials, and in particular relates to a method for molding the overall skeleton of variable-thickness composite materials and a molding mold thereof. Background technique [0002] With the rapid development of aerospace structural composite materials and the further requirements of new models for structural weight reduction, high efficiency and integration, the forming technology of structural composite materials has become the focus. An important factor in product performance, quality and reliability, it is crucial to the improvement and development of aerospace technology. [0003] Composite materials are developing rapidly in foreign countries, and the overall structural design and manufacturing technology are mature. The aircraft uses a large number of composite materials and has an integrated design. For example, the structural system of the US X-37B airc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/342B29C70/54
Inventor 赵锐霞何析峻张大海孙宏杰蒋文革
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH