Aircraft ignition cable assembling method

An assembly method and cable technology, applied to circuits, auxiliary devices, electrical components, etc., can solve problems such as reduced product reliability, failure to pass tests, time-consuming and laborious cleaning, etc., to achieve improved product reliability, good three-proof performance, and three-dimensional protection. Anti-performance high effect

Inactive Publication Date: 2021-02-23
四川泛华航空仪表电器有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the connection adopts the flame brazing method, and there are many processing procedures, serious oxidation after welding, and time-consuming and laborious cleaning.
The more important problem is that silver-copper solder is used in flame brazing, and the processed products are severely corroded in the three-proof test, failing to pass the test, and the product reliability is reduced

Method used

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  • Aircraft ignition cable assembling method
  • Aircraft ignition cable assembling method
  • Aircraft ignition cable assembling method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] A method for assembling an aircraft ignition cable mainly comprises the following steps:

[0026] Step S100: if figure 1 As shown, the first connection sleeve 3 is placed outside the end of the metal hose, and the end is welded for the first time to obtain a hose assembly;

[0027] Step S200: if figure 2 As shown, the copper braided sleeve 4 passes through the hose assembly and is turned outward at the end of the hose assembly; a second connecting sleeve 5 is sheathed outside the end of the hose assembly, and the first connecting sleeve 3 and the second Copper braided sleeves 4 are arranged between the connecting sleeves 5, and the connection between the three is welded for the second time.

[0028] The invention decomposes the original assembling and welding process into two parts, decomposes the original one metal part into two parts, and improves the original brazing process into two welding formings. The invention has strong practicability and solves the proble...

Embodiment 2

[0030] This embodiment is optimized on the basis of Embodiment 1. In the step S100, the first fusion welding is performed on the plane of the end of the metal hose sleeved with the first connecting sleeve 3 .

[0031] Further, as figure 1 , image 3 As shown, the metal hose includes a stainless steel bellows 2 and a stainless steel wire braided sleeve 1 that are sheathed in sequence from the inside to the outside; the outer end of the stainless steel wire braided sleeve 1 is covered with a first connecting sleeve 3 .

[0032] Further, the copper braided sheath 4 is snugly sleeved inside the hose assembly.

[0033] Other parts of this embodiment are the same as those of Embodiment 1, so details are not repeated here.

Embodiment 3

[0035] This embodiment is optimized on the basis of Embodiment 1 or 2. In the step S200, the first connection sleeve 3 is provided with a receiving limit platform, and the second connection sleeve 5 is correspondingly provided with an abutment surface, so One end of the braided braided sleeve 4 is turned outward and fitted along the length direction of the first connecting sleeve 3 , and the abutting surface is fixedly connected with the receiving limit platform.

[0036] Further, the second welding is performed on the receiving limit platform and the abutment surface.

[0037] The invention decomposes the original assembling and welding process into two parts, decomposes the original one metal part into two parts, and improves the original brazing process into two welding formings. The invention has strong practicability and solves the problem that the existing assembly structure cannot satisfy the three-proof performance of the product. At the same time, the structural stre...

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PUM

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Abstract

The invention discloses an aircraft ignition cable assembling method, and the method comprises the following steps: sleeving the outer side of the end part of a metal hose with a first connecting sleeve, and carrying out primary fusion welding on the end part to obtain a hose assembly; enabling the copper braided sleeve to penetrate through the hose assembly and to be turned outwards at the end ofthe hose assembly; sleeving the outer side of the end of the hose assembly with a second connecting sleeve, arranging a copper braided sleeve between the first connecting sleeve and the second connecting sleeve, and performing secondary fusion welding on the joint of the first connecting sleeve, the second connecting sleeve and the copper braided sleeve. According to the method, the original assembling and welding process is divided into two times, one original metal part is divided into two parts, and meanwhile original brazing machining is improved into two times of fusion welding forming.The assembly structure is high in practicability, and the problem that an existing assembly structure cannot meet the three-proofing performance of a product is solved. Meanwhile, the structural strength is improved, the appearance is attractive, the manufacturability is good, and the universal applicability is achieved.

Description

technical field [0001] The invention belongs to the technical field of aircraft ignition cable assembly, and in particular relates to an aircraft ignition cable assembly method. Background technique [0002] With the increase of ignition cable models, there are dozens of models using high magnetic permeability metal composite hose (abbreviation: metal hose) as the main body of the cable, such as: ignition cable DDL-63, DDL-65, Q / DDL- 72.73 series etc. Such as image 3 As shown, the metal hose is composed of a stainless steel wire braided sleeve and a stainless steel bellows. [0003] When processing the cable, a layer of copper braiding sleeve is installed in the hole of the metal hose, and then the two ends are connected with the metal parts. At present, flame brazing is used for connection, and there are many processing procedures, serious oxidation after welding, and time-consuming and laborious cleaning. The more important problem is that silver-copper solder is used ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01R43/02B23K37/00
CPCB23K37/00H01R43/02
Inventor 陈效
Owner 四川泛华航空仪表电器有限公司
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