CN110254743B - Cabin side windshield assembly method and assembly framework - Google Patents
Cabin side windshield assembly method and assembly framework Download PDFInfo
- Publication number
- CN110254743B CN110254743B CN201910414593.9A CN201910414593A CN110254743B CN 110254743 B CN110254743 B CN 110254743B CN 201910414593 A CN201910414593 A CN 201910414593A CN 110254743 B CN110254743 B CN 110254743B
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- putty
- assembly
- side windshield
- windshield
- conductive
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- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000013461 design Methods 0.000 claims abstract description 4
- 238000005498 polishing Methods 0.000 claims abstract description 4
- 239000011521 glass Substances 0.000 claims description 46
- 125000000449 nitro group Chemical group [O-][N+](*)=O 0.000 claims description 14
- 239000000853 adhesive Substances 0.000 claims description 12
- 230000001070 adhesive effect Effects 0.000 claims description 12
- 239000004020 conductor Substances 0.000 claims description 4
- 244000137852 Petrea volubilis Species 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 239000000741 silica gel Substances 0.000 claims description 3
- 229910002027 silica gel Inorganic materials 0.000 claims description 3
- 238000009499 grossing Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 description 7
- 238000003825 pressing Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000007790 scraping Methods 0.000 description 4
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 239000003292 glue Substances 0.000 description 3
- 238000009966 trimming Methods 0.000 description 3
- 239000002699 waste material Substances 0.000 description 3
- 230000001680 brushing effect Effects 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- 239000007799 cork Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 239000005357 flat glass Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
- B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
-
- 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
-
- 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
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B80/00—Architectural or constructional elements improving the thermal performance of buildings
- Y02B80/22—Glazing, e.g. vaccum glazing
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Automobile Manufacture Line, Endless Track Vehicle, Trailer (AREA)
Abstract
The application provides a method for assembling a side windshield of a cockpit, which comprises the following steps: the assembly surface and the conduction area are respectively arranged at two sides of the side windshield, the assembly surface is the outer side of the side windshield, and the conduction area is the inner side of the side windshield; leveling the assembly surface with putty, and polishing the putty to enable the gap between the assembly surface and the side windshield to meet the design requirement; and taking the assembly surface as a reference surface, so as to accurately position the assembly hole of the bolt fastener.
Description
Technical Field
The application relates to the technical field of aviation manufacturing, in particular to a cockpit side windshield assembly method and an assembly framework.
Background
The first ventilation window glass of the original cockpit is divided into two parts after the class III platform, and the new ventilation window and the side windshield are separated, and the assembly surface of the glass is also an electromagnetic shielding electric conduction area (see figure 1). The glass edge electromagnetic shielding net is turned outwards to the subsidence of the inner side of the glass, the original outer conductive area is changed into the inner side, the assembling surface can be repaired by scraping nitro putty Q07-5, (in actual production, the glass of the cockpit mostly needs to be repaired on the assembling surface to meet the requirement of the assembling gap). The conducting area and the assembling surface are arranged on the same side of the glass (the assembling surface and the conducting area of other types of glass of the cockpit are respectively arranged on two sides of the glass) during design, and the assembling surface is flattened by using nitro putty Q07-5, so that insulation is caused, which contradicts the electromagnetic shielding requirement, but in production, the assembling surface can only be flattened by scraping 72-00151 conductive putty, but the conductive putty can be polished after being solidified unlike Q07-5, and the price of the conductive putty is very high, so that the conductive putty is used for repairing in a large range and has high cost.
Content of the application
The electromagnetic shielding method overcomes the problem of contradiction of electromagnetic shielding requirements after the aircraft cockpit side windshield is assembled, and provides an assembling method and an assembling framework of the cockpit side windshield.
In a first aspect, the present application provides a method of cabin-side windshield assembly, the method comprising:
the assembly surface and the conduction area are respectively arranged at two sides of the side windshield, the assembly surface is the outer side of the side windshield, and the conduction area is the inner side of the side windshield;
leveling the assembly surface with putty, and polishing the putty to enable the gap between the assembly surface and the side windshield to meet the design requirement;
and taking the assembly surface as a reference surface, so as to accurately position the assembly hole of the bolt fastener.
Optionally, the leveling the assembly surface with the nitro putty specifically includes:
and (3) flattening the putty for the assembly surface by using sand paper.
Optionally, the conduction region comprises an electromagnetic shielding net, conductive adhesive, a conductive adhesive plate and conductive putty, and the electromagnetic shielding net, the conductive adhesive plate and the conductive putty are all arranged on the inner side of the side windshield.
Optionally, the method further comprises:
and the gap between the side windshield skeleton and the side windshield is sealed by silica gel.
Optionally, the leveling the putty for the assembly surface specifically includes:
and (3) flattening the assembly surface by using nitro putty.
In a second aspect, the present application provides a cockpit-side windshield assembly frame including a side windshield, a side windshield frame, a conductive material, wherein:
the two sides of the side windshield are respectively provided with an assembling surface and a conducting area, the assembling surface is the outer side of the side windshield, and the conducting area is the inner side of the side windshield;
the gap between the assembly surface and the side windshield is repaired by using putty.
Optionally, the putty is nitro putty.
Optionally, the conductive material includes electromagnetic shielding net, conductive adhesive plate and conductive putty, and the electromagnetic shielding net, conductive adhesive plate and conductive putty are all arranged on the inner side of the side windshield.
In summary, compared with the prior art, the method has the advantages that:
1) The electromagnetic shielding net at the edge of the glass is turned to the subsidence position of the inner side of the glass, and the electromagnetic shielding requirement of the wind shield glass at the side of the cockpit of the aircraft is ensured by changing the conductive area from the outer side to the inner side.
2) The nitro putty Q07-5 is adopted for flattening, so that the waste of conductive putty 72-00151 can be reduced, and the cost is saved to a great extent.
3) The assembly hole site is determined by repairing with puttying and taking the repaired assembly surface as a reference process cushion block (see figure 3), so that the assembly precision can be ensured.
Drawings
FIG. 1 is a schematic view of a prior art side windshield;
FIG. 2 is a theoretical diagram provided herein;
fig. 3 is a positioning chart of an assembly hole provided in the present application.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
Example 1
The method solves the problem of contradiction of electromagnetic shielding requirements after the side windshield of the cockpit of the aircraft is assembled, the assembly surface can only be flattened by scraping 72-00151 conductive putty in the assembly process, but the conductive putty can be polished after being solidified unlike the nitro putty Q07-5, and the price of 72-00151 is very high, so that the method is used for repairing in a large range and has high cost. The process cushion block takes the assembly surface before repair as a reference surface to determine the assembly hole, and the process cushion block is of a theoretical size and does not consider the repair amount (putty thickness). In order to ensure sufficient strength, the amount of putty modification generally does not allow more than 1.5mm, but the thickness of the putty is practically uncontrolled according to the existing conditions. It must be ensured that the assembly is in place once, and when partial thick putty appears, the hole site is already perforated in advance, and the stress is overlarge after the assembly is carried out barely.
In order to solve the technical problems, the application is realized through the following technical scheme.
The assembly surface and the conducting area are respectively arranged on two sides of the glass, the electromagnetic shielding of the glass edge is turned over from the outer net of the glass to the inner sunken position of the glass, and the conducting area is changed from the outer side to the inner side (see figure 2). Thus, the assembly surface can be flattened by using the nitro putty Q07-5 like other cockpit glass, and the trimming thickness can be polished and measured (the technical condition requires that the thickness of the putty is not more than 1.5mm when the trimming is performed, and the trimming amount of the metal frame is not more than 0.5 mm). The assembly accuracy can be ensured by using the flattened assembly surface as a reference surface to determine the assembly hole, and meanwhile, the waste of conductive putty can be reduced, and the cost is saved to a great extent.
In summary, the present application can achieve: 1) The electromagnetic shielding net at the edge of the glass is turned to the subsidence position of the inner side of the glass, and the electromagnetic shielding requirement of the wind shield glass at the side of the cockpit of the aircraft is ensured by changing the conductive area from the outer side to the inner side.
2) The nitro putty Q07-5 is adopted for flattening, so that the waste of conductive putty 72-00151 can be reduced, and the cost is saved to a great extent.
3) The assembly hole site is determined by repairing with puttying and taking the repaired assembly surface as a reference process cushion block (see figure 3), so that the assembly precision can be ensured.
Example two
The method for assembling the side windshield of the cockpit of the aircraft is implemented according to the following specific method:
1) And (5) checking the window frame. And (3) placing the glass installation model into an installation mouth frame, adjusting the gap between the glass installation model and the mouth frame to be uniform, checking the gap without attaching, and if the gap between the glass installation model and the mouth frame is not more than 2.3mm, adopting scraping and coating of nitro putty Q07-5 containing 5% cork powder to compensate.
2) And (5) testing the glass. And (3) putting the side windshield glass into the corresponding window frame, adjusting the glass to ensure that the gaps between the side windshield glass and the periphery of the window frame are uniform, measuring the gap between the glass sinking area and the window frame framework, and ensuring that the gap on the straight line section is 2-2.5mm and the gap at the corner is 2-4mm. The clearance between the glass outline and the installation framework is not less than 2mm.
3) And drilling a side windshield mounting hole. The positioning blocks are placed at the corresponding positions of the glass installation framework, the pressing blocks are placed on the positioning blocks at the corresponding positions, and then the positioning blocks are clamped by using bow-shaped clamps or locking pliers, so that the distance between the pressing blocks and the mouth frame is ensured. Arranging bolt holes according to the drawing requirement, drilling guide holes through the center lines of the arranged bolt holes on the pressing blocks and the framework, and reaming.
4) Cutting and sticking the rubber piece. And adhering 1154 rubber pads to a pressing plate by using XY401 glue solution, polishing the surfaces to be adhered of the rubber pads by using 240# sand paper before adhering, wiping the surfaces to be adhered by using absorbent cotton or gauze dipped with aviation washing gasoline, naturally airing (about 10-15 min) under the environmental condition until the surfaces to be adhered are dried, uniformly brushing a layer of XY401 glue on the surfaces to be adhered of the pressing plate, airing at room temperature for 3-10 min, respectively brushing a layer of glue solution on the surfaces to be adhered of the pressing plate and the rubber pads, airing for 5-6 min until the surfaces to be adhered are similar to hands, and adhering the surfaces to be adhered under the environmental condition for 24-48 h, so that the adhesion is smooth and no wrinkling phenomenon is ensured. Turning the electromagnetic shielding net at the edge of the glass to the subsidence position at the inner side of the glass, then dipping alcohol into gauze to wipe the cut conductive rubber plate, drying at room temperature, coating 72-00002 conductive adhesive on the subsidence surface of the glass, and then pasting the conductive rubber plate on the subsidence area of the glass.
5) And installing side windshield. And (3) putting the side windshield into a corresponding mouth frame, adjusting the gaps between the sunk outer edge of the glass and the periphery of the mouth frame uniformly, measuring the gaps, ensuring the straight-edge gaps to be 2-2.5mm, enabling the corners to reach 4mm, and making mounting marks. And after the glass is taken down, two pieces of RTV732 silica gel with the diameter of about 3-5 are extruded on the framework, and finally the glass is placed on the framework according to the installation mark to extrude the RTV732, so that the framework is ensured to be smooth. RTV732 is extruded and placed at the gap between the glass sinking and the framework, the height of the RTV is flush with the glass, no gap is reserved between the periphery of the glass sinking and the framework, and the packing is compact. RTV732 is also squeezed and put in the clearance department between glass outer fringe and skeleton after placing, guarantees to pack closely knit, does not have the cavity phenomenon. And coating a layer of conductive putty 72-00151 on the wrapping edge of the inner surface of the glass.
In summary, the application belongs to the technical field of aviation manufacturing, and relates to a convenient and repairable aircraft cockpit side windshield assembly method, wherein an electromagnetic shielding net at the edge of glass is turned over from outside to a sunken position at the inner side of glass, a conductive area is changed from outside to inside, electromagnetic shielding requirements of glass assembly are met, and the assembly holes can be determined by repairing with nitro putty Q07-5 by taking a flattened assembly surface as a reference surface, so that the assembly precision is ensured.
Claims (5)
1. A method of cabin side windshield assembly, the method comprising:
the assembly surface and the conduction area are respectively arranged at two sides of the side windshield, the assembly surface is the outer side of the side windshield, and the conduction area is the inner side of the side windshield; the conducting area comprises an electromagnetic shielding net, conductive adhesive, a conductive adhesive plate and conductive putty, and the electromagnetic shielding net, the conductive adhesive plate and the conductive putty are all arranged on the inner side of the side windshield; the electromagnetic shielding net at the edge of the glass is turned over from the outside of the glass to the subsidence position at the inner side of the glass;
leveling the assembly surface with putty, and polishing the putty to enable the gap between the assembly surface and the side windshield to meet the design requirement;
the assembly surface is used as a reference surface, so that the assembly hole of the bolt fastener is accurately positioned;
the method for leveling the assembly surface with the nitro putty specifically comprises the following steps:
and (3) flattening the putty for the assembly surface by using sand paper.
2. The method according to claim 1, wherein the method further comprises:
and the gap between the side windshield skeleton and the side windshield is sealed by silica gel.
3. The method according to claim 1, characterized in that said smoothing of the assembly surface with putty, in particular comprises:
and (3) flattening the assembly surface by using nitro putty.
4. The utility model provides a cockpit side windshield assembly skeleton, its characterized in that, cockpit side windshield assembly skeleton includes side windshield, side windshield skeleton, electrically conductive material, wherein:
the two sides of the side windshield are respectively provided with an assembling surface and a conducting area, the assembling surface is the outer side of the side windshield, and the conducting area is the inner side of the side windshield;
the gap between the assembly surface and the side windshield is repaired by using putty;
the conductive material comprises an electromagnetic shielding net, conductive adhesive, a conductive adhesive plate and conductive putty, and the electromagnetic shielding net, the conductive adhesive plate and the conductive putty are all arranged on the inner side of the side windshield.
5. The cockpit-side windshield assembly skeleton of claim 4, wherein said putty is a nitro putty.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910414593.9A CN110254743B (en) | 2019-05-17 | 2019-05-17 | Cabin side windshield assembly method and assembly framework |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910414593.9A CN110254743B (en) | 2019-05-17 | 2019-05-17 | Cabin side windshield assembly method and assembly framework |
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| Publication Number | Publication Date |
|---|---|
| CN110254743A CN110254743A (en) | 2019-09-20 |
| CN110254743B true CN110254743B (en) | 2023-06-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910414593.9A Active CN110254743B (en) | 2019-05-17 | 2019-05-17 | Cabin side windshield assembly method and assembly framework |
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| CN111731504A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Positioning method of cockpit glass framework |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2118948A1 (en) * | 1994-03-14 | 1995-09-15 | Victor J. Garcia | Magnetic window insulating and fly screen system |
| JP2012164773A (en) * | 2011-02-04 | 2012-08-30 | Ohbayashi Corp | Electromagnetically shielded room and method of constructing the same |
| CN202686752U (en) * | 2012-03-09 | 2013-01-23 | 陕西飞机工业（集团）有限公司 | Web-shaped airplane skylight framework |
| CN104457432A (en) * | 2014-12-10 | 2015-03-25 | 衡阳泰豪通信车辆有限公司 | Special-shaped square cabin |
| CN206472447U (en) * | 2017-02-21 | 2017-09-05 | 北京兴天通电讯科技有限公司 | A kind of electromagnetic shielding glass frame |
| CN207482177U (en) * | 2017-11-06 | 2018-06-12 | 江苏铁锚玻璃股份有限公司 | A kind of Multifunctional navigation aircraft windshield |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5902536A (en) * | 1996-09-13 | 1999-05-11 | Ppg Industries Ohio Inc. | Method for sealing an electrical connection to a laminated transparency |
| EP1608717B2 (en) * | 2003-04-01 | 2013-05-15 | De-Bonding Limited | Method and apparatus for bonding and debonding adhesive interface surfaces |
| US7344613B2 (en) * | 2004-03-17 | 2008-03-18 | Gyrotron Technology, Inc. | Method for laminating glass sheets using short wave radiation |
| CN202806307U (en) * | 2012-07-23 | 2013-03-20 | 长春光景科技有限公司 | Automotive front windshield with flexible display screens |
| CN204929541U (en) * | 2015-08-14 | 2015-12-30 | 江苏铁锚玻璃股份有限公司 | Electromagnetic shield glass and shielding cabin body thereof |
| CN205203356U (en) * | 2015-12-11 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Internal type windshield subassembly |
| CN106347582A (en) * | 2016-10-10 | 2017-01-25 | 江阴澳玛斯特游艇有限公司 | Fishing boat wind shield making process |
| CN109098479B (en) * | 2018-09-26 | 2020-07-03 | 吉林省泰华电子股份有限公司 | Construction process of light electromagnetic shielding chamber |
-
2019
- 2019-05-17 CN CN201910414593.9A patent/CN110254743B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2118948A1 (en) * | 1994-03-14 | 1995-09-15 | Victor J. Garcia | Magnetic window insulating and fly screen system |
| JP2012164773A (en) * | 2011-02-04 | 2012-08-30 | Ohbayashi Corp | Electromagnetically shielded room and method of constructing the same |
| CN202686752U (en) * | 2012-03-09 | 2013-01-23 | 陕西飞机工业（集团）有限公司 | Web-shaped airplane skylight framework |
| CN104457432A (en) * | 2014-12-10 | 2015-03-25 | 衡阳泰豪通信车辆有限公司 | Special-shaped square cabin |
| CN206472447U (en) * | 2017-02-21 | 2017-09-05 | 北京兴天通电讯科技有限公司 | A kind of electromagnetic shielding glass frame |
| CN207482177U (en) * | 2017-11-06 | 2018-06-12 | 江苏铁锚玻璃股份有限公司 | A kind of Multifunctional navigation aircraft windshield |
Non-Patent Citations (1)
| Title |
|---|
| 环氧导电防腐涂料的研究;倪楠楠;《优秀硕士论文全文数据库》;全文 * |
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