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Positioning and assembling method and device of part and composite material skeleton skin structure

A composite material and assembly method technology, which is applied in the field of resin-based structural composite material molding, can solve problems such as the inability to determine the installation reference and the inability to guarantee the accuracy of the shape and surface, so as to ensure the requirements of the aerodynamic shape, improve the quality of interface bonding and the accuracy of the shape and size , The effect of accurate positioning position

Active Publication Date: 2019-03-08
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to provide a method and device for positioning and assembling parts and composite skeleton skin structures, which can quickly find the precise installation position of parts and skeletons, and avoid problems due to inability to The problem that the installation datum cannot be determined due to the guarantee of shape and surface accuracy

Method used

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  • Positioning and assembling method and device of part and composite material skeleton skin structure
  • Positioning and assembling method and device of part and composite material skeleton skin structure
  • Positioning and assembling method and device of part and composite material skeleton skin structure

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Embodiment 1

[0065] like figure 1 As shown, the present embodiment provides a composite skeleton skin structure for aircraft empennage, comprising an integral skeleton, a metal rudder shaft and a lower skin 200, and the skeleton structure consists of an upper frame, a lower frame, and a plurality of groups of different heights. Board 3, wherein the upper frame is surrounded by a plurality of first frame bars 1 to form a multi-grid structure, the lower frame is surrounded by a plurality of second frame bars 2 to form a multi-grid structure, the first frame bars 1 and the second frame bars 2 One-to-one correspondence, a vertical plate 3 is provided between the corresponding first frame bar 1 and the second frame bar 2, and forms a structure with an I-shaped vertical section. The upper surface of the upper frame and the lower surface of the lower frame are both A double-curvature surface, correspondingly, the lower skin 200 is also a double-curvature surface. The skeleton skin structure is ma...

Embodiment 2

[0083] like Figure 6 As shown, the present embodiment provides a composite skeleton skin structure for aircraft wings, including an integral skeleton and a lower skin 200, and the skeleton structure is composed of an upper frame, a lower frame and multiple sets of vertical plates 3 with different heights , wherein the upper frame is surrounded by a plurality of first frame bars 1 to form a multi-grid structure, and the lower frame is surrounded by a plurality of second frame bars 2 to form a multi-grid structure. The first frame bars 1 and the second frame bars 2 correspond one-to-one , a vertical plate 3 is arranged between the corresponding first frame bar 1 and the second frame bar 2, and forms a structure with an I-shaped vertical section, and the upper surface of the upper frame and the lower surface of the lower frame are double-curvature surfaces Correspondingly, the lower skin 200 is also a double-curvature surface, and the skeleton skin structure is made of carbon fi...

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Abstract

The invention discloses a positioning and assembling method and device of a part and a composite material skeleton skin structure, and belongs to a resin-based structural composite material forming technology. The method comprises the following steps that a skin and a skeleton are sequentially stacked on a working surface of an appearance mold firstly and then pressed and fixed; a fixing base of apart positioner is fixed on a positioning surface, and the part to be fixed is fixed through a positioning part; and a relative position of the fixing base and the positioning surface is adjusted until the part to be fixed is matched with the skeleton; and then the part to be fixed is installed on the skeleton, the part positioner and the appearance mold are disassembled, and the positioning andassembling of the part and the skeleton are completed. According to the method and the device, the precise installation position of the part and the skeleton can be rapidly found, and the problem thatwhen the skin is a complex shape surface with double curvature and the like, the installation reference cannot be determined due to the fact that the surface accuracy cannot be guaranteed can be solved.

Description

technical field [0001] The invention belongs to the molding technology of resin-based structural composite materials, and in particular relates to a method for assembling and positioning a part and a double-curvature frame skin structure of a high-temperature-resistant resin-based composite material. Background technique [0002] With the rapid development of aerospace structural composite materials and the further requirements of new models for structural weight reduction and high efficiency, the overall molding technology of structural composite materials has become the focus, and the resulting assembly technology of the overall skeleton and skin has become the focus. As the key supporting technology of my country's transportation system, material technology is an important factor determining the performance, quality and reliability of aerospace products. Its performance and level have a very important impact on the development of aerospace technology and the development pro...

Claims

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Application Information

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IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/342B29C70/54
Inventor 赵锐霞王新张大海何析峻张毅
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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