CN109322994A - A kind of encapsulating method of aircraft trim panel - Google Patents
A kind of encapsulating method of aircraft trim panel Download PDFInfo
- Publication number
- CN109322994A CN109322994A CN201811305758.0A CN201811305758A CN109322994A CN 109322994 A CN109322994 A CN 109322994A CN 201811305758 A CN201811305758 A CN 201811305758A CN 109322994 A CN109322994 A CN 109322994A
- Authority
- CN
- China
- Prior art keywords
- trim panel
- rubber slab
- sealing
- rubber
- sealing edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000007789 sealing Methods 0.000 claims abstract description 44
- 238000003475 lamination Methods 0.000 claims abstract description 13
- 239000000565 sealant Substances 0.000 description 9
- 230000000694 effects Effects 0.000 description 3
- 238000003032 molecular docking Methods 0.000 description 2
- 208000013738 Sleep Initiation and Maintenance disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000007767 bonding agent Substances 0.000 description 1
- 201000010099 disease Diseases 0.000 description 1
- 208000037265 diseases, disorders, signs and symptoms Diseases 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 206010022437 insomnia Diseases 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
- F16J15/104—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing characterised by structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Gasket Seals (AREA)
Abstract
A kind of encapsulating method of aircraft trim panel, containing the first adjacent trim panel, the second trim panel and for the rubber slab of sealing, 1) the first rubber slab is tightly connected on the sealing edge of the first trim panel, it is tightly connected the second rubber slab on the sealing edge of the second trim panel, 2) again by the first rubber slab and the second rubber slab lamination adhering and sealing.
Description
Technical field
The invention belongs to aerospace designs technical fields, and in particular to a kind of encapsulating method of aircraft trim panel.
Background technique
In aviation field, aircraft noise is got more and more attention, and aircraft noise pollution effect is serious: can make pilot's energy
Dispersion is to influence flight safety；Noise can cause damages to the staff for a long time in aircraft noise, induction impaired hearing,
A variety of diseases such as insomnia, depression；The larger riding comfort that will affect passenger of aircraft noise, passenger are increasingly partial to take and fly
The small aircraft of machine noise, to influence the economic benefit of airline indirectly.Trim panel be fly Passenger On Board can directly contact with
Visual structure covers all areas that passenger can contact substantially, can there is the seam of certain interval between trim panel, these
Seam can seriously affect the sealing effect of aircraft noise.The sealing means of the seam on aircraft for trim panel are mainly at present
It is sealed using rubber profile.Such as p-type rubber profile, c-type rubber profile, E type rubber profile etc., p-type rubber profile is using
Trim panel is needed to realize the extruding of 15% to 20% deformation to it in the process, it can be because of vibration during aircraft flies for a long time
It generates and is displaced between trim panel, die down to influence the sealing of seam crossing so that squeezing sense, and very for relatively thin trim panel
Hardly possible realizes the extruding and fixation of p-type rubber profile；The application of E type rubber profile need to reserve molding mounting groove in trim panel end face,
Rubber strip is embedded in and is fixed, the form complex procedures, and trim panel is required to have certain thickness, it is mainly used in lap joint form
Trim panel.Rubber profile on the market is large number of, sealing effect also respectively have it is excellent lack, how to select suitable rubber profile,
It is the difficult point and pain spot of Seal Design to realize good leakproofness, economy and lightweight.
Goal of the invention
The object of the present invention is to provide a kind of encapsulating method of the seam of general aircraft trim panel, this method can expire
The double-layer seal of the parallel overlap joint of foot or parallel docking trim panel difference gap size, mounting means is simple and effective, and there is no harm in
Hinder the fast quick-detach of trim panel and can be realized fast assembling-disassembling and the maintenance of sealed rubber plate.
A kind of encapsulating method of aircraft trim panel, containing the first adjacent trim panel, the second trim panel and for sealing
Rubber slab, which is characterized in that 1) there are two corresponding rubber slabs, and the first rubber is tightly connected on the sealing edge of the first trim panel
Plate, is tightly connected the second rubber slab on the sealing edge of the second trim panel, and 2) again by the first rubber slab and the second rubber slab lamination
Adhering and sealing.
If having butt-joint clearance between the first trim panel and the second trim panel, the side lower surface of the first rubber slab is sealed
It is connected to the upper surface of the first trim panel sealing edge, the other side of the first rubber slab is greater than the width of butt-joint clearance, by the second rubber
The side lower surface of offset plate is sealedly connected on the upper surface of the second trim panel sealing edge, the other side of the second rubber slab also greater than
Adhering and sealing at first rubber slab and the second rubber slab lamination is made the first trim panel and the second interior trim by the width of butt-joint clearance
Butt-joint clearance sealing between plate.
If the sealing edge of the first trim panel is stacked on the sealing edge of the second trim panel, the first trim panel and the second interior trim
Plate has lamination gap, and the lower surface of first rubber slab is sealedly connected on the upper surface of the first trim panel sealing edge, the second rubber
The upper surface of offset plate is sealedly connected on the lower surface of the second trim panel sealing edge, then by the upper surface of the first rubber slab and the second rubber
The lower surface bonds of offset plate seal, and make the lamination clearance seal between the first trim panel and the second trim panel.
The beneficial effects of the present invention are: the interior of parallel overlap joint or parallel docking is realized using two corresponding rubber slabs
The double-layer seal of different seam sizes between plaque, the installation of which is simple and effective to have versatility, and only need to be according to reality
Border situation selects the thickness and width of rubber slab, reduces the process of rubber profile selection, simplifies the technique stream of seal process
Journey improves design efficiency.
Attached drawing is described in further detail the application with reference to embodiments.
Detailed description of the invention
Fig. 1 docks trim panel joint seal mode
Fig. 2 overlaps trim panel joint seal mode
Explanation: 1 first rubber slab, 2 second rubber slabs, 3 screws, 4 bonding agents, 5 first trim panels, 6 second is numbered in figure
Trim panel
Specific embodiment
Referring to attached drawing, a kind of encapsulating method of aircraft trim panel contains the first adjacent trim panel 5,6 and of the second trim panel
Rubber slab for sealing, which is characterized in that 1) there are two corresponding rubber slabs, pass through on the sealing edge of the first trim panel 5
Screw 3 and sealant 4 are tightly connected the first rubber slab 1, close by screw 3 and sealant 4 on the sealing edge of the second trim panel 6
The second rubber slab 2,2 of envelope connection) the first rubber slab 1 and 2 lamination of the second rubber slab are passed through into 4 adhering and sealing of sealant again.
If having butt-joint clearance between the first trim panel 5 and the second trim panel 6, as shown in Figure 1, by the first rubber slab 1
Side lower surface is sealedly connected on the upper surface of 5 sealing edge of the first trim panel by screw 3 and sealant 4, the first rubber slab 1
The other side is greater than the width of butt-joint clearance, and the side lower surface of the second rubber slab 2 is tightly connected by screw 3 and sealant 4
In the upper surface of 6 sealing edge of the second trim panel, the other side of the second rubber slab 2 also greater than butt-joint clearance width, by first
By 4 adhering and sealing of sealant at 2 lamination of rubber slab 1 and the second rubber slab, make between the first trim panel 5 and the second trim panel 6
Butt-joint clearance sealing.
If the sealing edge of the first trim panel 5 is stacked on the sealing edge of the second trim panel 6, as shown in Fig. 2, the first interior trim
Plate 5 and the second trim panel 6 have lamination gap, and the lower surface of first rubber slab 1 is sealed entirely through screw 3 and sealant 4
It is connected to the upper surface of 5 sealing edge of the first trim panel, the upper surface of the second rubber slab 2 is sealed entirely through screw 3 and sealant 4
It is connected to the lower surface of 6 sealing edge of the second trim panel, then by the lower surface of the upper surface of the first rubber slab 1 and the second rubber slab 2
Entirely through 4 adhering and sealing of sealant, make the lamination clearance seal between the first trim panel 5 and the second trim panel 6.
Claims (3)
1. a kind of encapsulating method of aircraft trim panel, containing the first adjacent trim panel, the second trim panel and for the rubber of sealing
Offset plate, which is characterized in that 1) the first rubber slab is tightly connected on the sealing edge of the first trim panel, in the sealing of the second trim panel
It is tightly connected the second rubber slab on side, 2) again by the first rubber slab and the second rubber slab lamination adhering and sealing.
2. the encapsulating method of aircraft trim panel as described in claim 1, which is characterized in that the first trim panel and the second trim panel
Between have butt-joint clearance, the side lower surface of first rubber slab is sealedly connected on the upper surface of the first trim panel sealing edge,
The other side of first rubber slab is greater than the width of butt-joint clearance, and the side lower surface of second rubber slab is sealedly connected on second
The upper surface of trim panel sealing edge, the other side of the second rubber slab also greater than butt-joint clearance width, by the first rubber slab with
Adhering and sealing at second rubber slab lamination seals the butt-joint clearance between the first trim panel and the second trim panel.
3. the encapsulating method of aircraft trim panel as described in claim 1, which is characterized in that the sealing edge lamination of the first trim panel
On the sealing edge of the second trim panel, the lower surface of first rubber slab is sealedly connected on the upper table of the first trim panel sealing edge
Face, the upper surface of the second rubber slab are sealedly connected on the lower surface of the second trim panel sealing edge, then by the upper table of the first rubber slab
The lower surface bonds of face and the second rubber slab seal, and make the lamination clearance seal between the first trim panel and the second trim panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811305758.0A CN109322994A (en) | 2018-11-02 | 2018-11-02 | A kind of encapsulating method of aircraft trim panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811305758.0A CN109322994A (en) | 2018-11-02 | 2018-11-02 | A kind of encapsulating method of aircraft trim panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109322994A true CN109322994A (en) | 2019-02-12 |
Family
ID=65260739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811305758.0A Pending CN109322994A (en) | 2018-11-02 | 2018-11-02 | A kind of encapsulating method of aircraft trim panel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109322994A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1503328A (en) * | 1975-11-21 | 1978-03-08 | Coal Ind | Split sleeve closures |
| CN1617990A (en) * | 2001-12-18 | 2005-05-18 | 日本利克雷斯工业株式会社 | Metal gasket material sheet |
| CN2895844Y (en) * | 2005-10-25 | 2007-05-02 | 中集车辆（集团）有限公司 | Sandwiched board connection structure |
| US20100084819A1 (en) * | 2006-01-24 | 2010-04-08 | Airbus Deutschland Gmbh | Surface seal as well as method for producing sealed joints with this surface seal |
| EP2385087A2 (en) * | 2010-04-14 | 2011-11-09 | Urs Gassmann | Sealing and mounting tape |
| CN101639155B (en) * | 2008-07-30 | 2012-09-05 | 森钜科技材料股份有限公司 | Composite plate assembly |
| CN203189436U (en) * | 2013-02-01 | 2013-09-11 | 中国航空工业集团公司西安飞机设计研究所 | Clamping device of plane interior trim panel |
| CN103328146A (en) * | 2012-01-16 | 2013-09-25 | 丰田自动车株式会社 | Panel joining structure |
| CN104454855A (en) * | 2014-12-04 | 2015-03-25 | 中国科学院工程热物理研究所 | Composite material/metal trapezoidal tooth mixing and connecting structure and preparation method thereof |
| CN204533841U (en) * | 2015-04-02 | 2015-08-05 | 广州金鹏环保工程有限公司 | Aerated grit chamber sliding sealing device |
-
2018
- 2018-11-02 CN CN201811305758.0A patent/CN109322994A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1503328A (en) * | 1975-11-21 | 1978-03-08 | Coal Ind | Split sleeve closures |
| CN1617990A (en) * | 2001-12-18 | 2005-05-18 | 日本利克雷斯工业株式会社 | Metal gasket material sheet |
| CN2895844Y (en) * | 2005-10-25 | 2007-05-02 | 中集车辆（集团）有限公司 | Sandwiched board connection structure |
| US20100084819A1 (en) * | 2006-01-24 | 2010-04-08 | Airbus Deutschland Gmbh | Surface seal as well as method for producing sealed joints with this surface seal |
| CN101639155B (en) * | 2008-07-30 | 2012-09-05 | 森钜科技材料股份有限公司 | Composite plate assembly |
| EP2385087A2 (en) * | 2010-04-14 | 2011-11-09 | Urs Gassmann | Sealing and mounting tape |
| CN103328146A (en) * | 2012-01-16 | 2013-09-25 | 丰田自动车株式会社 | Panel joining structure |
| CN203189436U (en) * | 2013-02-01 | 2013-09-11 | 中国航空工业集团公司西安飞机设计研究所 | Clamping device of plane interior trim panel |
| CN104454855A (en) * | 2014-12-04 | 2015-03-25 | 中国科学院工程热物理研究所 | Composite material/metal trapezoidal tooth mixing and connecting structure and preparation method thereof |
| CN204533841U (en) * | 2015-04-02 | 2015-08-05 | 广州金鹏环保工程有限公司 | Aerated grit chamber sliding sealing device |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
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Application publication date: 20190212 |