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CN-117508619-B - Air supplementing overflow pipeline in aircraft and installation method

CN117508619BCN 117508619 BCN117508619 BCN 117508619BCN-117508619-B

Abstract

The invention discloses an air supplementing overflow pipeline in an aircraft and an installation method, wherein the air supplementing overflow pipeline comprises a bottom support assembly, a pipe folding assembly, a curved pipe assembly and a top support assembly which are sequentially connected and internally communicated, the bottom end of the bottom support assembly is used for being connected with a water tank, the bottom support assembly is vertically arranged towards the bottom end, the bottom end of the pipe folding assembly is connected with the bottom support assembly, the top end of the pipe folding assembly is bent to be horizontally downward and connected with the curved pipe assembly, the height difference exists between the axes of the curved pipe assembly, one end connected with the pipe folding assembly is higher than the other end, the end part of the top support assembly is used for being connected with the inner wall of the aircraft, and the top support assembly is communicated to the outside of the aircraft after the connection. The air supplementing device can supplement air for the water tank, prevent the water tank from overflowing, and realize the discharge and acceleration of medium in the water tank.

Inventors

  • LIU RUI
  • JIA WEI
  • ZHOU XUAN
  • XIA WEIWEI
  • HU BIYANG

Assignees

  • 中航西飞民用飞机有限责任公司

Dates

Publication Date
20260512
Application Date
20231103

Claims (9)

  1. 1. The air supplementing overflow pipeline in the aircraft is characterized by comprising a bottom support assembly, a folding pipe assembly, a curved pipe assembly and a top support assembly which are sequentially connected and internally communicated; The bottom end of the bottom support component is used for being connected with the water tank, the bottom support component is vertically arranged towards the bottom end, the bottom end of the folding pipe component is connected with the bottom support component, the top end of the folding pipe component is bent to be horizontally downward and is connected with the curved pipe component, the axis of the curved pipe component has a height difference, one end connected with the folding pipe component is higher than the other end, the end part of the top support component is used for being connected with the inner wall of the airplane, and the top support component is communicated to the outside of the airplane after being connected; The bottom supporting assembly comprises a first supporting piece (2) and a first annular piece (3), the first supporting piece (2) is of a cylindrical structure, the bottom is used for being connected with the water tank, external threads are arranged outside the bottom, an axial boss is arranged on the inner wall of the bottom, the outer diameter of the first annular piece (3) is equal to the inner diameter of the first supporting piece (2), a plurality of axial bosses are arranged on the bottom, the first annular piece (3) is located in the first supporting piece (2), and the bosses of the first annular piece (3) are propped against the bosses of the first supporting piece (2); The folding pipe assembly comprises a folding pipe (8), a first outer sleeve nut (5) and a first flat pipe nozzle (6) are nested at the bottom of the folding pipe (8), the first outer sleeve nut (5) and the folding pipe (8) are axially and slidably arranged, a radial inward annular boss is arranged at the top of the first outer sleeve nut (5), a radial outward annular boss is arranged at the bottom of the first flat pipe nozzle (6), the two annular bosses are propped against each other, the bottom of the first outer sleeve nut (5) is in threaded connection with the first supporting piece (2), and the bottom end of the folding pipe (8) is in interference fit with the top end of the first annular piece (3); The bent pipe assembly comprises a bent pipe (9), one end of the bent pipe (9) is fixedly connected with the bent pipe (8), a second flat pipe nozzle (10) and a second outer sleeve nut (12) are nested at the other end of the bent pipe, the second outer sleeve nut (12) and the bent pipe (9) are arranged in a sliding mode, and the structures and the connection modes of the second outer sleeve nut (12) and the second flat pipe nozzle (10) and the first outer sleeve nut (5) and the first flat pipe nozzle (6) are the same; The top supporting component comprises a second annular piece (13), a second supporting piece (15) and a flange joint (16), wherein the flange joint (16) is fixedly connected with the inner wall of the machine body, one end of the second supporting piece (15) is fixedly connected with the flange joint (16), an axial boss is arranged inside the other end of the second supporting piece (15), external threads are arranged outside the boss, the second annular piece (13) is identical to the first annular piece (3) in structure, the outer diameter of the second annular piece (13) is equal to the inner diameter of the second supporting piece (15), the second annular piece (13) is located in the second supporting piece (15), the boss abuts against the second supporting piece (15), the end of the curved pipe (9) is in interference fit with the second annular piece (13).
  2. 2. An aircraft interior air make-up overflow duct according to claim 1, characterised in that the first annular member (3) and the second annular member (13) are evenly distributed with lugs around the top.
  3. 3. The aircraft interior make-up overflow duct of claim 1, wherein the curved tube assembly is riveted with the bellows assembly.
  4. 4. Aircraft interior make-up overflow duct according to claim 1, characterized in that the curvature of the flange joint (16) corresponds to the curvature of the fuselage.
  5. 5. The aircraft interior air supply overflow pipeline according to claim 1, wherein flares are arranged at the connection positions of the bottom of the folding pipe (8) and the outer edge of the curved pipe (9) with the second annular piece (13), and chamfers are arranged at the tops of the first annular piece (3) and the second annular piece (13).
  6. 6. Aircraft interior air make-up overflow duct according to claim 1, characterized in that the bottom of the first support (2) extends radially outwards as a flat ring.
  7. 7. A method of installing an aircraft interior air make-up overflow duct according to any of claims 1 to 6, wherein the bottom of the bottom support assembly is connected to the tank opening and the other end is connected to the bellows assembly by means of a threaded connection, the other end of the bellows assembly is connected to the curved tube assembly, the tail of the curved tube assembly is connected to the top support assembly, and the top support assembly is connected to the inner wall of the fuselage.
  8. 8. The method for installing the air supplementing and overflow pipeline in the aircraft according to claim 7, wherein one end of the curved pipe (9) with higher height is fixedly connected with the folding pipe (8), the flat circular ring of the first supporting piece (2) is fixed with the top of the water tank through bolts, and the flange joint (16) is fixedly connected with the aircraft body; The first outer sleeve nut (5) and the first flat nozzle (6) are sleeved at the bottom of the folding pipe (8), the bottom of the first outer sleeve nut (5) is in threaded connection with the first support (2), the annular boss at the top of the first outer sleeve nut (5) is propped against the annular boss at the bottom of the first flat nozzle (6), and the bottom of the folding pipe (8) is in interference fit with the top of the first annular member (3); The second annular piece (13) is arranged in the second supporting piece (15), a boss of the second annular piece (13) is propped against the boss of the second supporting piece (15), the second flat nozzle (10) and the second outer nut (12) are sleeved at one end of the curved pipe (9) with lower height, the second outer nut (12) is in threaded connection with the second supporting piece (15), the annular boss of the second outer nut (12) is propped against the annular boss of the second flat nozzle (10) and sealed, and the curved pipe (9) is in interference fit with the second annular piece (13); Finally, according to the horizontal direction position of the integral pipeline, the flange joint (16) is connected with the second support piece (15) through rivets.
  9. 9. The method for installing an aircraft interior air-make-up overflow pipeline according to claim 8, wherein grooves are formed between adjacent bosses of the first supporting member (2), when the pipeline is required to be disassembled, the first jacknut (5) is rotated to be separated from the first supporting member (2), the first annular member (3) is rotated until the bosses of the first annular member (3) correspond to the grooves of the first supporting member (2), the bosses of the first annular member (3) are inserted into the grooves of the first supporting member (2), so that the first annular member (3) is separated from the folding pipe (8), and the curved pipe (9) and the folding pipe (8) are horizontally pulled out from the second supporting member (15) with the second annular member (13), and the disassembly is completed; Or the curved tube (9) and the second annular piece (13) are separated in the same way, and then the curved tube (9) and the folded tube (8) are vertically pulled out from the first support piece (2) with the first annular piece (3), so that the disassembly is completed.

Description

Air supplementing overflow pipeline in aircraft and installation method Technical Field The invention belongs to the field of aircraft structures, and relates to an aircraft interior air supplementing overflow pipeline and an installation method. Background The fire-extinguishing type aircraft relies on water tank and pipeline structure to store release medium and realizes the operation of putting out a fire, because the process that the type aircraft of putting out a fire reaches the task of putting out a fire often needs to bear the fire extinguishing medium in the water tank, but at present the water tank only is provided with the water level measuring hole at the top, when filling water in the water tank, produce the overflow easily, overflow from the water level measuring hole, influence the aircraft inside to the air originally in the water tank can't discharge, the water tank only delivery port and the outside intercommunication of aircraft can't air supply when the drainage, the drainage speed is slow, be unfavorable for the operation of putting out a fire, and lack of air in the water tank leads to pressure deformation easily. Disclosure of Invention The invention aims to overcome the defects of the prior art, and provides an air supplementing overflow pipeline in an aircraft and an installation method thereof, which can supplement air and exhaust air for a water tank, prevent the water tank from overflowing and realize medium discharge acceleration in the water tank. In order to achieve the purpose, the invention is realized by adopting the following technical scheme: An air supplementing overflow pipeline in an aircraft comprises a bottom support assembly, a folding pipe assembly, a curved pipe assembly and a top support assembly which are sequentially connected and communicated with each other; The bottom support assembly bottom is used for connecting the water tank, and the bottom support assembly is vertically oriented to setting, rolls over the bottom support assembly bottom and connects the curved pipe assembly, and the top is buckled to the level and is off-set and connect the curved pipe assembly, and curved pipe assembly axis exists the difference in height, highly is higher than the other end with the one end that rolls over the pipe assembly and is connected, and top support assembly tip is used for connecting the fuselage inner wall, and connects back top support assembly intercommunication to the aircraft outside. Preferably, the bottom supporting component comprises a first supporting piece and a first annular piece, the first supporting piece is of a cylindrical structure, the bottom is used for being connected with the water tank, external threads are arranged outside the bottom, an axial boss is arranged on the inner wall of the bottom, the outer diameter of the first annular piece is equal to the inner diameter of the first supporting piece, a plurality of axial bosses are arranged on the bottom, the first annular piece is located in the first supporting piece, and the first annular piece abuts against the boss of the first supporting piece; The folding pipe assembly comprises a folding pipe, a first sleeve nut and a first flat pipe nozzle are nested at the bottom of the folding pipe, the first sleeve nut and the folding pipe are axially and slidably arranged, a radial inward annular boss is arranged at the top of the first sleeve nut, a radial outward annular boss is arranged at the bottom of the first flat pipe nozzle, the two annular bosses are propped against each other, the bottom of the first sleeve nut is in threaded connection with a first supporting piece, and the bottom end of the folding pipe is in interference fit with the top end of the first annular piece; The bent pipe assembly comprises a bent pipe, one end of the bent pipe is fixedly connected with the bent pipe, a second flat pipe nozzle and a second outer nut are nested at the other end of the bent pipe, the second outer nut and the bent pipe are arranged in a sliding manner, and the structures and the connection modes of the second outer nut and the second flat pipe nozzle and the first outer nut and the first flat pipe nozzle are the same; The top supporting component comprises a second annular piece, a second supporting piece and a flange joint, wherein the flange joint is fixedly connected with the inner wall of the machine body, one end of the second supporting piece is fixedly connected with the flange joint, an axial boss is arranged inside the other end of the second supporting piece, external threads are arranged outside the second supporting piece, the second annular piece is identical to the first annular piece in structure, the outer diameter of the second annular piece is equal to the inner diameter of the second supporting piece, the second annular piece is located in the second supporting piece, the boss abuts against the second supporting piece, a second outer nut is in threaded connection with