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Connecting structure of composite material joint

A composite material and connection structure technology, applied in the direction of connection components, threaded fasteners, nuts, etc., can solve the problems of thread damage, thread load, etc., to avoid wear resistance, strong bearing capacity, and avoid low thread strength Effect

Active Publication Date: 2020-12-01
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a connection structure of a composite material joint, in which a metal insert is pre-embedded in the composite material joint to solve the problem that the thread load of the composite material is large and repeated disassembly and assembly will cause thread damage

Method used

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  • Connecting structure of composite material joint

Examples

Experimental program
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Effect test

Embodiment 1

[0049] The metal insert 3 adopts a step-shaped metal insert, which is pre-embedded in the composite material joint with a flange thickness of 20mm. The metal insert 3 is made of high-strength alloy steel 30CrMnSi, and the metal insert 3 is processed with M18 threaded holes. The diameter is 28mm, the outer diameter of the limiting step is 35mm, the height of the cylinder 34 is 15mm, the height of the limiting step is 5mm, and the pull-out bearing capacity of the metal insert 3 is 17.2t.

Embodiment 2

[0051] The metal insert 3 adopts a tapered metal insert, which is pre-embedded in the composite material joint with a flange thickness of 20mm. The metal insert 3 is made of high-strength alloy steel 30CrMnSi. The height of the piece 3 is 20mm, wherein, the outer diameter of the small end is 28mm, the outer diameter of the big end is 35mm, and the drawing bearing capacity of the metal insert 3 is 20.0t.

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Abstract

The invention discloses a connecting structure of a composite material joint. The connecting structure comprises a composite material joint body and a metal insert, the end face of the composite material joint body is provided with an installation hole for an external connecting piece to penetrate through. The outer bottom face and the outer side face of the metal insert are completely wrapped inthe composite material joint body, and a threaded hole used for being connected with the external connecting piece is formed in the outer top face of the metal insert. According to the connecting structure, the metal insert with the threaded hole is embedded into the composite material joint body; and the external connecting piece is connected with the composite material joint through the threadedhole in the metal insert, the defects that the composite material joint body is low in threaded strength, not resistant to abrasion and the like can be overcome, the bearing capacity is higher, and it is guaranteed that the composite material joint body cannot be damaged in the repeated disassembling and assembling process of the composite material joint and the external connecting piece.

Description

technical field [0001] The invention relates to the field of connectors, in particular to a connection mechanism for composite material joints. Background technique [0002] Lightweight has always been an important indicator to reflect the advanced nature of solid rocket motors. With the increase in the mass ratio of solid rocket motors, the joints of composite material shells have also begun to be made of composite materials at this stage, that is, composite material joints are used to further reduce Negative mass of the engine. However, due to the low strength and wear resistance of composite threads, the connection structure of composite joints is a major problem that limits its application. The mechanical industry usually uses threaded sleeves such as self-tapping screw sleeves, pin screw sleeves or locking screw sleeves to strengthen or repair the threads. However, for composite shell joints, the thread load is large, the working conditions are complicated, and repeate...

Claims

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Application Information

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IPC IPC(8): F16B37/12F16B37/14
CPCF16B37/122F16B37/145
Inventor 赵飞周睿刘冬青司学龙余明敏钟志文武丹蒋磊
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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