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Aircraft fuel system duct positioning structure and positioning method

A technology of fuel system and positioning structure, which is applied in aircraft assembly, aircraft parts, aircraft power plant, etc. It can solve the problems that affect the production cycle of large aircraft, the difficulty of system conduit assembly, and the limited installation space of the cabin, so as to achieve easy control Clearance and coaxiality, small space occupation, and the effect of ensuring product quality

Active Publication Date: 2021-03-30
XIAN AIRCRAFT IND GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the large number of fuel system pipelines with different shapes and the limited installation space in the cabin, the assembly of system conduits is difficult and inefficient, which seriously affects the production cycle of large aircraft

Method used

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  • Aircraft fuel system duct positioning structure and positioning method
  • Aircraft fuel system duct positioning structure and positioning method
  • Aircraft fuel system duct positioning structure and positioning method

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Experimental program
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Effect test

Embodiment Construction

[0016] Referring to the accompanying drawings, the aircraft fuel system conduit positioning structure of the present application includes a clamping band 1, an end face positioning plate 2 and an axial connector 3, and the clamping band 1 includes an upper ring body 6 and a lower ring body 7 , the detachable connection between the upper ring body 6 and the lower ring body 7, in the embodiment, the lower ring body is provided with a handle, the butt surface of the upper ring body 6 and the lower ring body 7 is a magnetic adsorption structure, the lower ring body The docking surface contains a magnet 9, and the docking surface of the upper ring body 7 contains an iron joint 8, and vice versa. In order to connect with the end face positioning plate 2, three connecting holes of the axial connector 3 are provided on the upper ring body 6, and the inner diameter of the clamping clip 1 matches the outer diameter of the conduit of the aircraft fuel system. The end face positioning plat...

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PUM

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Abstract

The invention relates to an aircraft fuel system duct positioning structure and method, the positioning structure comprises a clamping hoop, an end face positioning plate and an axial connector, an upper ring body and a lower ring body of the clamping hoop are detachably connected, and the axial connector is used for connecting and positioning the upper ring body of the clamping hoop and the end face positioning plate according to a preset gap, an annular positioning line matched with the outer diameter of a butt joint duct is arranged on the outer side of the end face positioning plate, a left side duct is limited through the clamping hoop, the gap between the upper ring body and the end face positioning plate is adjusted, and a pipe opening of a right side duct is connected to an annularpositioning line on the outer side of the end face positioning plate in a pressed mode to be fixed.

Description

technical field [0001] This application belongs to the assembly and production technology of the conduit of the aircraft fuel system, in particular to the positioning structure and the positioning method of the conduit of the aircraft fuel system. Background technique [0002] Most of the pipeline connections of aircraft fuel systems use flexible connections, that is, pipes with pipe joints, sleeves, seals and clamps are combined and assembled, and then fixed with brackets and pipe clamps on the walls of the cabin. The gap reserved for butt joints is 3-6mm, and the axis deviation is not greater than 3^. During the aircraft assembly and production process, the fuel system conduits are installed and connected in the cabin in sections, and the flexible joints and seals of each section of the conduits are assembled first, and then tightened with clamps. After all the system pipelines are connected, airtight or For the pressure test, it is necessary to ensure that the joints are...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/10B64D37/00
CPCB64F5/10B64D37/005Y02T50/40
Inventor 范艳玲张可心张莹莹乔顺成王守川高建武
Owner XIAN AIRCRAFT IND GROUP
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