Composite material pi-type lug interface and integral co-curing forming method

A composite material and lug-type technology, applied in high-efficiency propulsion technology, aircraft parts, climate sustainability, etc., can solve problems such as poor performance and large gaps, and achieve the effects of excellent performance, improved carrying capacity, and good integrity

Active Publication Date: 2014-01-29
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Due to the poor interlayer performance of composite materials, there is a large gap between them and traditional alumi

Method used

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  • Composite material pi-type lug interface and integral co-curing forming method
  • Composite material pi-type lug interface and integral co-curing forming method
  • Composite material pi-type lug interface and integral co-curing forming method

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Embodiment Construction

[0029] The present invention will be described in detail below through specific embodiments and accompanying drawings.

[0030] In this embodiment, a composite material π-type lug joint is made. figure 1 is the structural schematic diagram of the composite material π-type lug joint, figure 2 It is a schematic cross-sectional view of the joint, which includes the lug 1 and the bottom plate 3, and is composed of an embedded skeleton 8 and an outer skin 9, where 2 is the outer corner, 4 is the inner corner, 5 is the length direction, and 6 is the width 7 is the height direction, 10 is the extension direction of the skeleton laminated surface, that is, the direction of the load action surface, 11 is the extension direction of the skin laminate, that is, the direction of the vertical load, 12 is the direction of the bending load, and 13 is the direction of the shear load . The thickness of the lugs of the composite material π-shaped lug joint is 13mm, the thickness of the bottom...

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Abstract

The invention relates to a composite material pi-type lug interface and integral co-curing forming method. The pi-type lug interface comprises an embedded composite material framework and an outer-layer composite material skin coated on the framework. A lamination plane of the embedded composite material framework is parallel to a load direction, and is mainly used for bearing in-plane bending and shearing load. The lamination plant of the outer-layer composite material skin is along with a tangential direction of the outer surface of the embedded framework. The interface is formed with a prepreg-RTM co-curing process. The paving direction of the embedded framework is coplanar with bending and transverse shearing load, such that a characteristic of high composite material in-plane strength can be developed. With the outer-layer skin, the blocked embedded framework is coated into a whole, such that the interface structure is provided with better integrity, and defects of low transmission efficiency and easy stratification at corner joints when a traditional pi-typed interface bears outer-plane load are overcome.

Description

technical field [0001] The invention relates to the technical field of composite materials, and relates to a composite material π-shaped lug joint and an integral co-curing molding method thereof. Background technique [0002] The π-type lug joint is one of the main forms of connection between aircraft structures, and it is used for the transfer of concentrated loads between the airfoil structure and the cabin structure. The traditional π-shaped lug structure is made of forged aluminum alloy. The aluminum alloy is an isotropic material, which can effectively transfer the load from the lug of the π-shaped joint to the bottom plate. [0003] With the continuous improvement of users' requirements for structural lightweight, the use of composite materials to replace aluminum alloy materials has become an important development trend. The fiber orientation of the existing π-type lug joints of composite materials will change in the transition zone between the lugs and the bottom p...

Claims

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Application Information

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IPC IPC(8): B64C1/26B29C70/48
CPCY02T50/43Y02T50/433Y02T50/40
Inventor 张涛王国勇张东华程小全许亚洪柯红军李丽英
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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