Rotor blade integrally formed by three-dimensional woven composite material and manufacturing method

A composite material, integral molding technology, applied in the direction of rotorcraft, motor vehicles, aircraft assembly, etc., can solve the problems of low interlayer strength, difficulty in ensuring the uniformity of different blades, layer damage, etc., and achieve high fatigue resistance. and damage tolerance, avoid sudden failure problems, avoid the effect of easy delamination

Active Publication Date: 2022-02-01
TSINGHUA UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Using this process to make blades is complicated, and the laying of carbon fiber cloth depends on manual experience, the production efficiency is low, and it is difficult to ensure the uniformity of different blades
Moreover, since the upper airfoil, lower airfoil and the girder of the blade are only bonded together by resin, the integrity is poor, and the interlayer strength is low. It is prone to delamination damage when subjected to a large load or external impact, and cannot Give full play to the performance advantages of carbon fiber materials

Method used

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  • Rotor blade integrally formed by three-dimensional woven composite material and manufacturing method
  • Rotor blade integrally formed by three-dimensional woven composite material and manufacturing method
  • Rotor blade integrally formed by three-dimensional woven composite material and manufacturing method

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Embodiment Construction

[0054] In order to more clearly illustrate the above purpose, features and advantages of the present application, specific implementation methods of the present application will be described in detail in this part with reference to the accompanying drawings. In addition to the various implementations described in this section, the present application can also be implemented in other different ways. Without departing from the spirit of the present application, those skilled in the art can make corresponding improvements, deformations and replacements. Therefore, the present application Do not be bound by the specific embodiments disclosed in this section. The scope of protection of this application should be based on the claims.

[0055] Such as Figure 1 to Figure 9 As shown, the present application proposes a three-dimensional woven composite material integrally formed rotor blade (hereinafter sometimes simply referred to as blade), which includes a root connector 1 and a bl...

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Abstract

The present application proposes a rotor blade integrally formed from a three-dimensional woven composite material and a manufacturing method thereof. The rotor blade integrally formed from a three-dimensional woven composite material includes: a root connector, and the root connector is provided with a tow connection hole and a paddle body, the paddle body comprising a three-dimensional woven composite material woven from tows, the paddle body being connected to the tow by passing at least part of the tows through the tow connecting holes The above-mentioned root connector.

Description

technical field [0001] The application relates to a rotor blade integrally formed by three-dimensional woven composite materials and a manufacturing method thereof. Background technique [0002] At present, the rotor blades used by unmanned helicopters include upper airfoil, lower airfoil and load-bearing girder. The upper airfoil, lower airfoil and load-bearing girder need to be preformed by laying carbon fiber unidirectional cloth or woven cloth with independent molds, and then Finally, it is formed by gluing or co-curing. Using this process to make blades is complicated, and the laying of carbon fiber cloth depends on manual experience, the production efficiency is low, and it is difficult to ensure the uniformity of different blades. Moreover, since the upper airfoil, lower airfoil and the girder of the blade are only bonded together by resin, the integrity is poor, and the interlayer strength is low. It is prone to delamination damage when subjected to a large load or ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/473B64C27/48B29D99/00B64F5/10
CPCB64C27/473B64C27/48B29D99/0025B64F5/10B64C2027/4736
Inventor 王财政苏丹丹谢之峰周明
Owner TSINGHUA UNIV
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