Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool

A composite material and integral component technology, applied in workpiece clamping devices, manufacturing tools, etc., to improve assembly quality and meet assembly coordination requirements

Active Publication Date: 2012-09-05
BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage of the above positioning method is: the position accuracy of the skeleton or reinforcement is poor, and it still cannot meet the assembly coordination requirements between the composite airfoil integral component and other components
The reason is that because the skeleton or reinforced curing mold is not constrained, and because the skeleton or reinforced blank is soft during the high-temperature curing process, there will be sliding displacement between the skeleton or reinforced curing mold and the skin when vacuuming or pressurizing , and the skeleton or reinforced curing mold will also produce deflection movement, and there is no mutual constraint between each skeleton or reinforced curing mold, and the displacement of each skeleton or reinforced curing mold with the thermal expansion of the skin is different, which will lead to the skeleton or The location accuracy of the reinforcement cannot be controlled

Method used

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  • Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool
  • Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool
  • Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] 1. A composite airfoil integral component with upper and lower skins. Between the upper and lower skins, there are 5 composite materials that are connected to the upper and lower skins. Type skeleton; positioning tooling for the composite wing surface integral component skeleton, including 1 skin mold made of steel and 5 skeleton curing molds. The shape of the skeleton curing mold is Shape, the skeleton curing mold is located Outside of the type frame, each The inner side of the mold skeleton is a [shaped soft mold, there are a total of 5 soft molds; on the skin mold there are skin profiles, on the skin profiles there are uncured skin blanks, on the uncured skin blanks There are 5 curing molds with skeleton blanks arranged; 5 wing root positioning devices and 5 wing tip positioning devices; the wing root positioning device is composed of 5 wing root positioning components and 1 wing root cross beam. The root positioning component consists of 1 wing root locator, 1 wing...

Embodiment 2

[0051] A composite wing surface integral wall panel with a lower skin. On the lower skin, there are 10 composite T-shaped reinforcements that only fit and connect with the lower skin; positioning tooling for the reinforcement of the composite wing surface integral component , Including 1 skin mold made of steel and 5 reinforced curing molds. The cross-sectional shape of the reinforced curing mold is rectangular. From the left, the reinforced curing mold I is located in the first T-shaped rib 9 and the second T Type II reinforcement curing mold is located between the third T type reinforcement 11 and the fourth T type reinforcement 12, and the No. III reinforcement curing mold is located between the fifth T type reinforcement 13 and Between the sixth T-shaped reinforcement 14, the IV reinforcement curing mold is located between the seventh T-shaped reinforcement 15 and the eighth T-shaped reinforcement 16, and the V reinforcement curing mold is located in the ninth T-shaped reinf...

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Abstract

The invention belongs to composite-material structure forming technologies, and relates to a locating tool for frameworks / reinforced ribs of an integrated composite-material wing structural member and an application method of the locating tool. The locating tool is characterized in that: at the two ends of longitudinal direction of skin-covering molds (1), framework / reinforced rib curing mold locating devices are respectively arranged on the skin-covering molds outside a skin-covering molded surface; and the application method is characterized by comprising the following steps of: installing a wing root locator (3) and a wing tip locator (6); assembling and connecting a wing root connecting segment (4), a wing tip connecting segment (7) and a framework / reinforced rib curing mold (2); locating the framework / reinforced rib curing mold (2); placing a soft mold; packaging in a vacuum bag; installing a wing root transverse beam (5) and a wing tip transverse beam (8); and disassembling pinsand fixing bolts of the locators. By the locating tool and the application method, the positional precision of the frameworks / reinforced ribs of an integrated composite-material wall panel is ensured, the requirement of assembly and coordination between the integrated composite-material wing structural member and other structural members is met, and the assembly quality is improved.

Description

technical field [0001] The invention belongs to composite material structure molding technology, and relates to a positioning tool for the skeleton or reinforcement of an integral component of a composite airfoil and a method for using the same. Background technique [0002] After years of development, composite materials have been gradually applied to large-scale main load-bearing structures. see figure 1 , figure 1 The upper picture in the figure is a composite material airfoil integral component with upper and lower skins, and there is a composite material skeleton connected to the upper and lower skins between the upper and lower skins. figure 1 The figure below is a composite material airfoil integral member with a lower skin, and there are composite material reinforcements that are only connected to the lower skin on the lower skin. The extension direction of the skeleton or reinforcement is the longitudinal direction of the composite airfoil, that is, the span ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B25B11/00
Inventor 梁宪珠常海峰薛向晨张西伟
Owner BEIJING AERONAUTICAL MFG TECH RES INST
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