CN212448030U - Inside secondary seal structure in general aircraft cabin - Google Patents
Inside secondary seal structure in general aircraft cabin Download PDFInfo
- Publication number
- CN212448030U CN212448030U CN202020591791.0U CN202020591791U CN212448030U CN 212448030 U CN212448030 U CN 212448030U CN 202020591791 U CN202020591791 U CN 202020591791U CN 212448030 U CN212448030 U CN 212448030U
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- Prior art keywords
- frame
- sealing
- interior
- lug
- aircraft cabin
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Links
- 238000007789 sealing Methods 0.000 claims abstract description 80
- 230000007246 mechanism Effects 0.000 claims abstract description 23
- 239000011521 glass Substances 0.000 claims abstract description 17
- 238000009413 insulation Methods 0.000 claims abstract description 11
- 230000035939 shock Effects 0.000 claims abstract description 11
- 239000003292 glue Substances 0.000 claims abstract description 8
- 239000000945 filler Substances 0.000 claims description 10
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 18
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000006872 improvement Effects 0.000 abstract description 3
- 230000008595 infiltration Effects 0.000 abstract description 3
- 238000001764 infiltration Methods 0.000 abstract description 3
- 239000005394 sealing glass Substances 0.000 description 14
- 230000001681 protective effect Effects 0.000 description 6
- 230000008859 change Effects 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- Securing Of Glass Panes Or The Like (AREA)
Abstract
The utility model discloses an inside secondary seal structure in general aircraft cabin, including interior frame, interior frame and outer frame, be equipped with sealed glass between interior frame and the outer frame, be equipped with sealing mechanism between interior frame and the outer frame and the sealed glass, sealing mechanism is including arc protecting sheathing, arc filling glue, seal groove, sealed piece, first lug and second lug, be equipped with latch mechanism between interior frame and the outer frame, latch mechanism moulds system fixture block and shock insulation pad including draw-in groove, spliced pole, elasticity, the arc protecting sheathing passes through the arc filling glue veneer and connects between interior frame and outer frame and the sealed glass, the surface at sealed glass is seted up to the seal groove. A inside secondary seal structure in general aircraft cabin, the sealed effect of improvement that can be great avoids appearing the phenomenon of leaking out, infiltration, secondly can make things convenient for the dismouting to enclose the frame in, improves the convenience of later maintenance.
Description
Technical Field
The utility model relates to a seal structure field, in particular to inside secondary seal structure in general aircraft cabin.
Background
The sealing structure in the cabin of the general airplane is a sealing structure used between cabin glass and the cabin of the general airplane, the general airplane is generally an airplane in a non-passenger airplane form such as a private airplane, an emergency airplane or a coach airplane, a plurality of windows are reserved in the cabin of the airplane, the windows are made of glass and cannot be lifted or opened, a user can conveniently observe the landscape outside the airplane, and the glass and the cabin belong to two different objects, so the glass and the cabin need to be sealed by the sealing structure after being installed; but the inside seal structure in current general aircraft cabin is sealed the effect poor, only seals through outside glass is glued, appears leaking out easily when general aircraft flies at a high speed, the phenomenon of infiltration, has reduced the sealed effect in aircraft cabin, secondly inconvenient dismouting to glass, maintenance and change are not convenient for, and it is relatively poor to use the convenience.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a main aim at provides an inside secondary seal structure in general aircraft cabin can effectively solve the problem among the background art.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides an inside secondary seal structure in general aircraft cabin, includes interior frame, interior frame and outer frame, be equipped with sealing glass between interior frame and the outer frame, be equipped with sealing mechanism between interior frame and the outer frame and sealing glass, sealing mechanism is including arc protecting sheathing, arc filling glue, seal groove, sealed piece, first lug and second lug, be equipped with clamping mechanism between interior frame and the outer frame, clamping mechanism moulds system fixture block and shock insulation pad including draw-in groove, spliced pole, elasticity.
Preferably, the arc protective housing passes through the arc filling glue veneer and connects including sealing between frame and the outer frame and the sealing glass, the surface at sealing glass is seted up to the seal groove, inside top position at sealing frame and outer frame is sealed including sealed piece fixed mounting, sealed piece block is in the inside of seal groove, the equal fixed mounting of first lug and second lug is in the bottom outside of sealing glass.
Preferably, a first cavity and a second cavity are arranged between the first bump and the inner sealing frame and between the first bump and the second bump and the outer sealing frame respectively, and a first sealing filler and a second sealing filler are filled in the first cavity and the second cavity respectively.
Preferably, the clamping groove is formed in the front surface of the outer sealing frame, the connecting column is fixedly installed at the rear portion of the inner sealing frame, the elastic plastic clamping block is fixedly connected to one end of the connecting column, and the shock insulation cushion is sleeved outside the connecting column.
Preferably, the four corners of the outer part and the four corners of the inner sealing frame and the outer sealing frame are provided with chamfers.
Compared with the prior art, the utility model discloses following beneficial effect has: the utility model discloses in, through the sealing mechanism who sets up, the efficiency of multistage seal has been realized, excellent sealed effect has been played, great improvement the leakproofness between aircraft cabin and the glass, avoid appearing leaking, the phenomenon of infiltration, the result of use is better, through the latch mechanism who sets up, can conveniently demolish interior frame, then change, maintain sealed glass, easy dismounting's effect has been played, great improvement later maintenance's convenience, the result of use is better.
Drawings
Fig. 1 is a schematic view of the overall structure of a general aircraft cabin interior secondary sealing structure of the present invention;
FIG. 2 is a cross-sectional side view of the utility model of a general aircraft cabin interior secondary seal structure;
fig. 3 is an enlarged view of a in fig. 2 of the internal secondary sealing structure of the general aircraft cabin of the present invention.
In the figure: 1. an inner sealing frame; 2. sealing glass; 3. an outer sealing frame; 4. a sealing mechanism; 5. an arc-shaped protective shell; 6. arc filling glue; 7. a sealing groove; 8. a sealing block; 9. a first bump; 10. a second bump; 11. a first cavity; 12. a second cavity; 13. a first seal packing; 14. a second seal packing; 15. a clamping mechanism; 16. a card slot; 17. connecting columns; 18. elastic plastic fixture blocks; 19. provided is a shock insulation pad.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1-3, a general aircraft cabin interior secondary sealing structure comprises an inner sealing frame 1, an inner sealing frame 1 and an outer sealing frame 3, sealing glass 2 is arranged between the inner sealing frame 1 and the outer sealing frame 3, a sealing mechanism 4 is arranged between the inner sealing frame 1 and the outer sealing frame 3 and between the sealing glass 2, the sealing mechanism 4 comprises an arc-shaped protective shell 5, an arc-shaped filling adhesive 6, a sealing groove 7, a sealing block 8, a first bump 9 and a second bump 10, a clamping mechanism 15 is arranged between the inner sealing frame 1 and the outer sealing frame 3, and the clamping mechanism 15 comprises a clamping groove 16, a connecting column 17, an elastic plastic clamping block 18 and a shock insulation pad 19;
the arc-shaped protective shell 5 is connected between the inner sealing frame 1 and the outer sealing frame 3 and the sealing glass 2 through the arc-shaped filling adhesive 6 in a gluing mode, the sealing groove 7 is formed in the outer surface of the sealing glass 2, the sealing block 8 is fixedly installed at the top positions of the inner sealing frame 1 and the outer sealing frame 3, the sealing block 8 is clamped inside the sealing groove 7, the first bump 9 and the second bump 10 are both fixedly installed on the outer side of the bottom of the sealing glass 2, the multi-stage sealing effect is achieved through the arrangement of the sealing mechanism 4, the excellent sealing effect is achieved, the sealing performance between the aircraft cabin and the sealing glass 2 is greatly improved, the phenomena of air leakage and water seepage are avoided, and the using effect is better; a first cavity 11 and a second cavity 12 are respectively arranged between the first bump 9 and the second bump 10 and the inner sealing frame 1 and the outer sealing frame 3, a first sealing filler 13 and a second sealing filler 14 are respectively filled in the first cavity 11 and the second cavity 12, a four-sealing effect is formed between the first bump 9 and the second bump 10 and between the first sealing filler 13 and the second sealing filler 14, and the sealing property is further improved; the clamping groove 16 is formed in the front surface of the outer sealing frame 3, the connecting column 17 is fixedly installed at the rear part of the inner sealing frame 1, the elastic plastic clamping block 18 is fixedly connected to one end of the connecting column 17, the shock insulation pad 19 is sleeved outside the connecting column 17, the inner sealing frame 1 can be conveniently detached through the arrangement of the clamping mechanism 15, then the sealing glass 2 is replaced and maintained, the effect of convenience in disassembly and assembly is achieved, convenience in later maintenance is greatly improved, and the using effect is better; the chamfer angle has been all seted up to the outside and the inside four corners position of interior frame 1 and outer frame 3.
It should be noted that, the utility model relates to a general aircraft cabin interior secondary seal structure, when in use, when the aircraft flies, firstly the arc protective shell 5 and the arc filling glue 6 can play the primary seal effect, and simultaneously the arc protective shell 5 and the arc filling glue 6 are arc-shaped, and can play the effect of guiding rainwater and reducing wind resistance, secondly, because the first lug 9 and the second lug 10 are both clamped between the inner seal frame 1 and the outer seal frame 3, the first lug 9 and the second lug 10 can play the two sealing effect to form secondary seal, thereby greatly improving the sealing effect, reducing the phenomena of air leakage, rainwater leakage and the like, meanwhile, the first cavity 11 and the second cavity 12 are respectively formed between the inner seal frame 1 and the outer seal frame 3 by the first lug 9 and the second lug 10, and the first sealing filler 13 and the second sealing filler 14 are filled in the first cavity 11 and the second cavity 12, play the effect of two sealings again, thereby multistage sealed effect has been realized, the leakproofness has further been improved, when sealing glass 2 needs to be changed, can demolish interior frame 1 through latch mechanism 15, directly outwards pull out interior frame 1 during the operation, thereby drive spliced pole 17 and pull out elasticity plastic-molded fixture block 18, pressure leads to elasticity plastic-molded fixture block 18 to produce deformation, thereby break away from draw-in groove 16, finally demolish interior frame 1, direct card is gone into when reinstallating, can utilize elasticity plastic-molded fixture block 18's elasticity and draw-in groove 16 block to be connected, shock insulation pad 19 can play the effect of shock insulation.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. The utility model provides an inside secondary seal structure of general aircraft cabin which characterized in that: including interior frame (1), interior frame (1) and outer frame (3) of sealing, be equipped with between interior frame (1) and the outer frame (3) sealed glass (2), be equipped with between interior frame (1) and outer frame (3) and sealed glass (2) sealing mechanism (4), sealing mechanism (4) are including arc protecting crust (5), arc packing glue (6), seal groove (7), sealed piece (8), first lug (9) and second lug (10), be equipped with clamping mechanism (15) between interior frame (1) and the outer frame (3), clamping mechanism (15) are including draw-in groove (16), spliced pole (17), elasticity mould system fixture block (18) and shock insulation pad (19).
2. The general aircraft cabin interior secondary seal structure of claim 1, wherein: arc protecting sheathing (5) are connected including sealing between frame (1) and outer frame (3) and sealed glass (2) through arc filling adhesive (6) veneer, the surface at sealed glass (2) is seted up in seal groove (7), the inside top position of sealing frame (1) and outer frame (3) including sealed piece (8) fixed mounting, sealed piece (8) block is in the inside of seal groove (7), equal fixed mounting in the bottom outside of sealed glass (2) of first lug (9) and second lug (10).
3. The general aircraft cabin interior secondary seal structure of claim 1, wherein: a first cavity (11) and a second cavity (12) are arranged between the first lug (9) and the second lug (10) and the inner sealing frame (1) and the outer sealing frame (3) respectively, and a first sealing filler (13) and a second sealing filler (14) are filled in the first cavity (11) and the second cavity (12) respectively.
4. The general aircraft cabin interior secondary seal structure of claim 1, wherein: the shock insulation structure is characterized in that the clamping groove (16) is formed in the front surface of the outer sealing frame (3), the connecting column (17) is fixedly installed at the rear portion of the inner sealing frame (1), the elastic plastic clamping block (18) is fixedly connected to one end of the connecting column (17), and the shock insulation pad (19) is sleeved on the outer portion of the connecting column (17).
5. The general aircraft cabin interior secondary seal structure of claim 1, wherein: chamfers are arranged at four corners of the outer part and the inner part of the inner sealing frame (1) and the outer sealing frame (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020591791.0U CN212448030U (en) | 2020-04-20 | 2020-04-20 | Inside secondary seal structure in general aircraft cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020591791.0U CN212448030U (en) | 2020-04-20 | 2020-04-20 | Inside secondary seal structure in general aircraft cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212448030U true CN212448030U (en) | 2021-02-02 |
Family
ID=74468176
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020591791.0U Active CN212448030U (en) | 2020-04-20 | 2020-04-20 | Inside secondary seal structure in general aircraft cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212448030U (en) |
-
2020
- 2020-04-20 CN CN202020591791.0U patent/CN212448030U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20240624 Granted publication date: 20210202 |
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| PP01 | Preservation of patent right | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20240805 Granted publication date: 20210202 |
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| PD01 | Discharge of preservation of patent |