CN112572826B - Positioning structure and positioning method for aircraft fuel system guide pipe - Google Patents
Positioning structure and positioning method for aircraft fuel system guide pipe Download PDFInfo
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- CN112572826B CN112572826B CN202011473169.0A CN202011473169A CN112572826B CN 112572826 B CN112572826 B CN 112572826B CN 202011473169 A CN202011473169 A CN 202011473169A CN 112572826 B CN112572826 B CN 112572826B
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- Prior art keywords
- ring body
- upper ring
- conduit
- positioning plate
- gap
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- 239000000446 fuel Substances 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 10
- 210000001503 joint Anatomy 0.000 claims abstract description 18
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 238000001179 sorption measurement Methods 0.000 claims description 2
- 238000002788 crimping Methods 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000007789 sealing Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Quick-Acting Or Multi-Walled Pipe Joints (AREA)
- Rigid Pipes And Flexible Pipes (AREA)
Abstract
The utility model provides an aircraft fuel system pipe location structure and location method, location structure contains the centre gripping clamp, end face locating plate and axial connector, can dismantle the connection between the last ring body of centre gripping clamp and the lower ring body, axial connector is used for connecting the location according to predetermined clearance between the last ring body of centre gripping clamp and the end face locating plate, the outside of end face locating plate is equipped with the annular positioning line that matches with butt joint pipe external diameter, it is spacing to the left side pipe to realize with the centre gripping clamp, the clearance between adjustment last ring body and the end face locating plate, it can to fix the mouth of pipe crimping of right side pipe on the annular positioning line in the end face locating plate outside.
Description
Technical Field
The application belongs to an assembly production technology of a guide pipe of an aircraft fuel system, and particularly relates to a guide pipe positioning structure and a positioning method of the aircraft fuel system.
Background
The aircraft fuel system pipeline connection is mainly realized by adopting flexible connection, namely, a guide pipe with a pipe joint, a pipe sleeve, a sealing piece and a clamp are assembled and then fixed by a support and a pipe clamp on a wall body in an engine room, the reserved gap of each pair of joint butt joints is required to be 3-6 mm in the pipeline assembly, and the axis deviation is not more than 3 degrees. In the aircraft assembly production process, the fuel system pipes are in butt joint in sections when being installed and connected in the aircraft cabin, the flexible joints and the sealing pieces of the pipes in each section are assembled firstly and then are clamped by the clamp, and airtight or pressure-resistant tests are carried out after all the system pipelines are connected, so that the sealing of each connecting part is ensured to be firm, the leakage of oil is prevented, and the flight safety is ensured.
At present, workers only manually assemble the pipeline according to the senses and experiences, then carry out pipeline airtightness tests, disassemble, adjust and reassemble the pipeline if air leakage is detected, and repeatedly install and debug the pipeline until the requirements are met. As the fuel oil system has a plurality of pipelines and different shapes, and the installation space in the engine room is limited, the assembly difficulty of the system conduit is high, the efficiency is low, and the production cycle of a large airplane is seriously influenced.
In order to meet the assembly requirement of the pipeline of the aircraft fuel system, a novel tool which is simple and practical, strong in operability, high in universality, low in manufacturing cost, capable of being quickly positioned and convenient for controlling the gap and the angle needs to be developed, and the assembly requirement of the pipeline of the aircraft fuel system is met.
Disclosure of Invention
An object of this application is to provide an aircraft fuel system pipe location structure and positioning method that can fix a position, control clearance and angle fast, this location structure can be reliably with aircraft pipe joint location connection to can adjust butt joint clearance and control axis deviation through the mechanism, and the commonality is strong, and occupation space is little, can realize quick assembly disassembly.
The utility model provides an aircraft fuel system pipe location structure, its characterized in that, location structure contains centre gripping clamp, end face locating plate and axial connector, the centre gripping clamp contain ring body and lower ring body, go up and to dismantle between ring body and the lower ring body and be connected, go up the connecting hole that is equipped with a plurality of axial connector on the ring body, the internal diameter and the pipe external diameter of centre gripping clamp match, the outside of end face locating plate be equipped with the annular positioning line that matches of butt joint pipe external diameter, be equipped with a plurality of axial connector's that correspond with last ring body connecting hole in the outside of end face locating plate annular positioning line, axial connector be used for with the last ring body of centre gripping clamp and the end face locating plate between according to predetermined gap connection location.
The axial connector comprises a step shaft and a gap measurer, the left end of the step shaft passes through the connecting hole on the upper ring body, the end of the screw is matched with a first nut, a spiral pressure spring is respectively sleeved on the step shafts on the two sides of the upper ring body, the right end of the step shaft passes through the connecting hole on the end face positioning plate, the end of the gap measurer is matched with the second nut, the gap measurer comprises a vernier pointer and a gap indicating scale, the gap indicating scale is connected with one side of the upper ring body close to the end surface positioning plate through a connecting body, the vernier pointer is fixed on the step shaft, the axial position of the step shaft can be adjusted through the first nut or the second nut, the axial position of the step shaft determines the gap between the upper ring body and the end face positioning plate, the vernier pointer follows the axial position of the step shaft, and the indication position of the vernier pointer on the gap indication scale displays the gap between the upper ring body and the end face positioning plate.
The application also provides a positioning method using the positioning structure for the guide pipe of the aircraft fuel system, wherein a left guide pipe and a right guide pipe of the aircraft fuel system need to be positioned and butted, and the positioning method is characterized in that 1) a pipe body of the left guide pipe is fixed with an aircraft body; 2) clamping an upper ring body of a clamping hoop on a conduit joint of a left conduit, butting a lower ring body and the upper ring body into a whole, and limiting the conduit joint of the left conduit by using the clamping hoop; 3) connecting the end face positioning plate with the upper ring body through the axial connector, and adjusting the gap between the upper ring body and the end face positioning plate to enable the gap to be in accordance with the preset value range of the butt joint of the aircraft fuel system guide pipes, 3) pressing the pipe orifice of the right side guide pipe on an annular positioning line on the outer side of the end face positioning plate; 4) keeping the state that the pipe orifice of the right side conduit is in compression joint with the annular positioning line, and fixing the pipe body of the right side conduit on the airplane body; 5) separating an upper ring body and a lower ring body of the clamping hoop to enable the lower ring body to be separated from a limiting state of the left side conduit, and then separating the upper ring body and the end face positioning plate from the left side conduit and the right side conduit to enable a pipe joint of the left side conduit to be in a butt joint state with a pipe orifice of the right side conduit; 6) and finally, connecting the left side conduit with the right side conduit by using a pipe joint hoop.
The beneficial effect of this application lies in: when the aircraft fuel system conduit is flexibly assembled, the conduit positioning structure capable of being quickly positioned and conveniently controlling the gap and the coaxiality is provided. This pipe location structure can be reliably with aircraft pipe joint location connection, can also adjust butt joint clearance and control axis deviation through the mechanism to the commonality is strong, and occupation space is little, can realize quick assembly disassembly, effectively improves production efficiency, guarantees product quality.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of a positioning structure of a guide pipe of an aircraft fuel system.
Fig. 2 is a schematic view of a clamp structure.
FIG. 3 is a schematic view of the connection of the axial connector with the clamp and the end positioning plate.
FIG. 4 is a schematic diagram of a method for locating conduits in an aircraft fuel system.
The numbering in the figures illustrates: the device comprises a clamp 1, an end face positioning plate 2, an axial connector 3, a gap measurer 4, an annular positioning line 5, an upper annular body 6, a lower annular body 7, an iron joint 8, a magnet 9, a gap indication scale 10, a vernier pointer 11, a step shaft 12, a first nut 13, a second nut 14, a spiral pressure spring 15, a left side guide pipe 16 and a right side guide pipe 17.
Detailed Description
Referring to the drawings, the aircraft fuel system conduit positioning structure comprises a clamping hoop 1, an end face positioning plate 2 and an axial connector 3, wherein the clamping hoop 1 comprises an upper ring body 6 and a lower ring body 7, the upper ring body 6 is detachably connected with the lower ring body 7, a handle is arranged on the lower ring body, the butt joint surface of the upper ring body 6 and the lower ring body 7 is of a magnetic adsorption structure, the butt joint surface of the lower ring body comprises a magnet 9, and the butt joint surface of the upper ring body 7 comprises an iron joint 8, and vice versa. In order to be connected with the end face positioning plate 2, the upper ring body 6 is provided with connecting holes of three axial connectors 3, the inner diameter of the clamping hoop 1 is matched with the outer diameter of a guide pipe of an aircraft fuel system, the end face positioning plate 2 can be a circular flat plate or an annular flat plate, the outer side center of the end face positioning plate 2 is provided with an annular positioning line 5 matched with the outer diameter of a butt joint guide pipe, the outer side of the annular positioning line 5 of the end face positioning plate is also provided with three connecting holes of the axial connectors corresponding to the upper ring body, and the axial connectors 3 are used for connecting and positioning the upper ring body 6 of the clamping hoop 1 and the end face positioning plate 2 according to a preset gap. In operation, the axial connector 3 comprises a step shaft 12 and a gap measurer 4. When assembled, there are three axial connectors 3, each axial connector 3 being fitted with a gap measuring device 4. The left end of each step shaft 12 penetrates through a connecting hole in the upper ring body 6, the end of each step shaft is matched with a first nut 13, as shown in fig. 3, a spiral pressure spring 15 is sleeved on each step shaft on two sides of the upper ring body 6, the right end of each step shaft 12 penetrates through a connecting hole in the end face positioning plate 2, the end of each step shaft is matched with a second nut 14, the gap measurer 4 comprises a cursor pointer 11 and a gap indication scale 10, the gap indication scale 10 is connected to one side, close to the end face positioning plate, of the upper ring body 6 through a connecting body, as shown in fig. 2, the cursor pointer 11 is fixed on the step shaft 12, the axial position of the step shaft 12 can be adjusted through the first nut 13 or the second nut 14, the axial position of the step shaft 12 determines the gap between the upper ring body 6 and the end face positioning plate 2, the cursor pointer 11 follows the axial position of the step shaft 12, and the indication position of the pointer 11 on the gap indication scale 10 shows the gap between the upper ring body 6 and the end face positioning plate 2.
As shown in fig. 4, a left side conduit 16 and a right side conduit 17 of an aircraft fuel system need to be positioned and butted, and the left side conduit 16 and the right side conduit 17 are positioned by using the positioning structure of the aircraft fuel system conduit provided by the present application, wherein the positioning method comprises the steps of fixing a pipe body of the left side conduit 16 with an aircraft body, clamping an upper ring body 6 of a clamping hoop 1 on a conduit joint of the left side conduit 16, butting a lower ring body 7 with the upper ring body 6 into a whole, and limiting the conduit joint of the left side conduit 16 by using the clamping hoop 1; connecting the end face positioning plate 2 with the upper ring body 6 through the axial connector 3, adjusting the gap between the upper ring body 6 and the end face positioning plate 2 to enable the gap to accord with the preset value range of the butt joint of the aircraft fuel system guide pipes, keeping the positioning structure still, and pressing the pipe orifice of the right side guide pipe 17 on an annular positioning line 5 on the outer side of the end face positioning plate 2; fixing the pipe body of the right side guide pipe 17 on the airplane body under the condition that the pipe orifice of the right side guide pipe 17 is in pressure joint with the annular positioning line 5; after the right side guide pipe 17 is fixed with the airplane body, the upper ring body 6 and the lower ring body 7 of the clamping hoop 1 are separated, so that the lower ring body 7 is separated from a limiting state of the left side guide pipe 16, the upper ring body 6 and the end face positioning plate 2 are separated from the left side guide pipe 16 and the right side guide pipe 17, and a pipe joint of the left side guide pipe 16 and a pipe orifice of the right side guide pipe 17 are kept in a butt joint state; and finally, connecting the left guide pipe 16 with the right guide pipe 17 by using a pipe joint hoop.
Claims (4)
1. A guide pipe positioning structure of an aircraft fuel system is characterized in that the positioning structure comprises a clamping hoop, an end face positioning plate and an axial connector, the clamping hoop comprises an upper ring body and a lower ring body, the upper ring body is detachably connected with the lower ring body, a plurality of connecting holes of the axial connector are formed in the upper ring body, the inner diameter of the clamping hoop is matched with the outer diameter of a guide pipe, an annular positioning line matched with the outer diameter of a butt joint guide pipe is arranged on the outer side of the end face positioning plate, a plurality of connecting holes of the axial connector corresponding to the upper ring body are formed in the outer side of the annular positioning line of the end face positioning plate, the axial connector is used for connecting and positioning the upper ring body and the end face positioning plate of the clamping hoop according to a preset gap, the axial connector comprises a step shaft and a gap measurer, the left end of the step shaft penetrates through the connecting holes in the upper ring body, and the end of the step shaft is matched with a first nut, the step shafts on the two sides of the upper ring body are respectively sleeved with a spiral pressure spring, the right ends of the step shafts penetrate through connecting holes in the end face positioning plate, the ends of the step shafts are matched with second nuts, the gap measurer comprises a vernier pointer and a gap indication scale, the gap indication scale is connected to one side, close to the end face positioning plate, of the upper ring body through a connecting body, the vernier pointer is fixed on the step shafts, the axial position of the step shafts can be adjusted through the first nuts or the second nuts, the axial position of the step shafts determines the gap between the upper ring body and the end face positioning plate, the vernier pointer follows the axial position of the step shafts, and the indication position of the vernier pointer on the gap indication scale displays the gap between the upper ring body and the end face positioning plate.
2. An aircraft fuel system duct positioning structure as claimed in claim 1, wherein the abutting surfaces of the upper ring body and the lower ring body are of a magnetic adsorption structure, one abutting surface of the upper ring body and the lower ring body comprises a magnet, and the other abutting surface of the upper ring body and the lower ring body comprises an iron joint.
3. An aircraft fuel system conduit locating structure as claimed in claim 2, wherein said lower ring body is provided with a handle.
4. A positioning method using the positioning structure of the conduit of the aircraft fuel system as claimed in claim 1, 2 or 3, wherein the left conduit and the right conduit of the aircraft fuel system need to be positioned and butted, and is characterized by 1) fixing the pipe body of the left conduit with the aircraft body; 2) clamping an upper ring body of a clamping hoop on a conduit joint of a left conduit, butting a lower ring body and the upper ring body into a whole, and limiting the conduit joint of the left conduit by using the clamping hoop; 3) connecting the end face positioning plate with the upper ring body through the axial connector, and adjusting the gap between the upper ring body and the end face positioning plate to enable the gap to be in accordance with the preset value range of the butt joint of the aircraft fuel system guide pipes; 4) pressing the pipe orifice of the right guide pipe on an annular positioning line outside the end surface positioning plate; 5) keeping the state that the pipe orifice of the right side conduit is in compression joint with the annular positioning line, and fixing the pipe body of the right side conduit on the airplane body; 6) separating an upper ring body and a lower ring body of the clamping hoop to enable the lower ring body to be separated from a limiting state of the left side conduit, and then separating the upper ring body and the end face positioning plate from the left side conduit and the right side conduit to enable a pipe joint of the left side conduit to be in a butt joint state with a pipe orifice of the right side conduit; 7) and finally, connecting the left side conduit with the right side conduit by using a pipe joint hoop.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011473169.0A CN112572826B (en) | 2020-12-15 | 2020-12-15 | Positioning structure and positioning method for aircraft fuel system guide pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011473169.0A CN112572826B (en) | 2020-12-15 | 2020-12-15 | Positioning structure and positioning method for aircraft fuel system guide pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112572826A CN112572826A (en) | 2021-03-30 |
| CN112572826B true CN112572826B (en) | 2022-08-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011473169.0A Active CN112572826B (en) | 2020-12-15 | 2020-12-15 | Positioning structure and positioning method for aircraft fuel system guide pipe |
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| Country | Link |
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| CN (1) | CN112572826B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2991428B1 (en) * | 2012-06-01 | 2016-07-01 | Airbus Operations Sas | DEVICE AND METHOD FOR SUPPLYING TWO CONNECTIONS AT THE END OF TWO CONDUITS, IN PARTICULAR IN AN AIRCRAFT |
| WO2015179896A1 (en) * | 2014-05-29 | 2015-12-03 | Australasian Steel Products Pty Ltd | Anchoring arrangement for a protective sleeve |
| CN104175279B (en) * | 2014-07-31 | 2016-11-16 | 湖北三江航天红林探控有限公司 | The manual quick pipeline connection device of clamping hoop type |
| EP3287682A1 (en) * | 2016-08-23 | 2018-02-28 | Horst Streitmaier | Holding device for the detachable, coaxial joining of flexible tubing |
| CN207735855U (en) * | 2017-11-30 | 2018-08-17 | 成都飞机工业（集团）有限责任公司 | A kind of thin-wallconduit tack-weld anti-deformation device |
| CN111070152A (en) * | 2019-12-24 | 2020-04-28 | 宜宾三江机械有限责任公司 | Flexible clamp connector sleeve disassembling tool |
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2020
- 2020-12-15 CN CN202011473169.0A patent/CN112572826B/en active Active
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| Publication number | Publication date |
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| CN112572826A (en) | 2021-03-30 |
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