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Method for connecting composite material structural body without using fastening piece of passing through composite material structural body and aircraft

A technology of composite materials and structures, applied in the field of aircraft, can solve problems such as structural damage, stress concentration of fasteners, and layered damage of multi-layer structures

Active Publication Date: 2013-11-13
ZHUHAI TRITON TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Perforation may cause damage to the delamination of the multilayer structure of the composite structure
[0004] Trimming must be done for composite structures, which weakens the structure, so additional material must be used for reinforcement, resulting in an increase in the weight of the aircraft
[0005] Fasteners will cause local stress concentration, and the location of stress concentration is prone to structural damage

Method used

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  • Method for connecting composite material structural body without using fastening piece of passing through composite material structural body and aircraft
  • Method for connecting composite material structural body without using fastening piece of passing through composite material structural body and aircraft
  • Method for connecting composite material structural body without using fastening piece of passing through composite material structural body and aircraft

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Embodiment Construction

[0026] See figure 1 , the aircraft in this embodiment is an airplane, which has a fuselage 1 and wings 2 , and the fuselage 1 is located above the wings 2 . A spacer 3 is placed between the fuselage 1 and the wing 2, the shape of the lower surface of the spacer 3 matches the shape of the upper surface of the wing 2, and the shape of the upper surface of the spacer 3 matches the shape of the lower surface of the fuselage 1 The shape matches. In addition, a thin plate made of polymer or other materials can be embedded between the fuselage 1 and the filler 3 . Sheets can also be embedded between the caulk 3 and the wing 2 . see figure 2 , in this embodiment, the aircraft is provided with eight straps 4, and the straps 4 pass through four longitudinal beams 6 in the floor of the cabin and surround the wing box 5, so as to bind the wing 2, the filler 3 and the fuselage 1 together. purpose (such as Figure 2 to Figure 4 shown). The number of straps 4 and stringers 6 may vary ...

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PUM

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Abstract

The invention provides a method for connecting a composite material structural body using a belt and an aircraft manufactured by the method, in particular using the belt to bind the body of the aircraft and airfoils, so that defects in the traditional method that a lot of fastening pieces are consumed and holes are punched in the surface of a composite material are prevented. The method can be used in the connection of any composite material structural body and has particular application values in the connection between wings and a fuselage made of composite materials.

Description

technical field [0001] The present invention relates to the field of aircraft, in particular to an aircraft, and to a method of enabling the joining of composite structures without the use of fasteners passing through the composite structures. This application is based on US Provisional Application Serial No. 61 / 742,597 filed August 15, 2012, the contents of which are incorporated herein by reference. Background technique [0002] Many existing aircraft, such as airplanes, have a fuselage and wings. The traditional method of connecting the wings and the fuselage is to use fasteners to join the two together. More and more aircraft are made of composite materials. The fuselage and wings are usually composite structures. These composite structures usually include multi-layer structures. Using traditional methods to connect the fuselage and wings must be done in composite materials. Drill holes in the structure and pass bolts, rivets and other fasteners through the holes. This...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/00
CPCB64C1/26Y10T29/49622
Inventor 薛国航
Owner ZHUHAI TRITON TECH CO LTD