CN209870717U - Installation assembly for installing transparent part of aircraft observation window - Google Patents
Installation assembly for installing transparent part of aircraft observation window Download PDFInfo
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- CN209870717U CN209870717U CN201920619264.3U CN201920619264U CN209870717U CN 209870717 U CN209870717 U CN 209870717U CN 201920619264 U CN201920619264 U CN 201920619264U CN 209870717 U CN209870717 U CN 209870717U
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- window frame
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- 238000009434 installation Methods 0.000 title claims abstract description 42
- 238000003825 pressing Methods 0.000 claims abstract description 25
- 230000006835 compression Effects 0.000 claims abstract description 20
- 238000007906 compression Methods 0.000 claims abstract description 20
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000002360 preparation method Methods 0.000 claims description 2
- 239000002184 metal Substances 0.000 description 11
- 229910052751 metal Inorganic materials 0.000 description 11
- 239000000463 material Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000005394 sealing glass Substances 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 239000011521 glass Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Securing Of Glass Panes Or The Like (AREA)
Abstract
The mounting assembly (100) for mounting the aircraft observation window transparent piece (200) comprises a window frame (110) and a pressing ring (120), wherein the window frame (110) comprises a window frame outer ring (111) and a window frame inner ring (112) extending inwards from the window frame outer ring (111) in the radial direction; the compression ring (120) comprises a compression ring outer ring (121) and a compression ring inner ring (122) which extends radially inwards from the compression ring outer ring (121); the window frame outer ring (111) is connected with the pressing ring outer ring (121) to clamp and press the transparent part (200) of the aircraft observation window between the window frame inner ring (112) and the pressing ring inner ring (122), the window frame outer ring (111) is provided with a pressing ring installation part protruding towards the pressing ring outer ring (121), and the window frame outer ring (111) is connected with the pressing ring outer ring (121) through the pressing ring installation part. The utility model discloses the strong weight of just clamping ring installation department of simple to operate swift stability is lighter.
Description
Technical Field
The utility model relates to an aircraft structural design field, concretely relates to an installation component for installing aircraft observation window transparency.
Background
The installation assembly for installing the transparent part of the aircraft observation window is used for installing and fixing the transparent part of the aircraft observation window on the window frame and can meet the related airtight requirement and the negative pressure problem in the flight process. The aircraft window transparency is, for example, a passenger window transparency assembly, which may comprise one or more layers of glass or other light transmissive material, or may comprise a combination of multiple layers of different materials.
The installation of the transparent part of the currently common aircraft observation window mainly comprises two types, one type is a spring clip installation mode similar to Boeing company, and the other type is a pressing plate installation mode similar to airbus company. The spring clip mounting method of Boeing company is used by both domestic C919 and ARJ21-700 airplanes.
The boeing company spring clip mounting is shown in figures 1 and 2. The figure shows the installation of the passenger viewing window of B-737. As can be seen, the passenger viewing window is secured to the window frame structure by means of 10 spring clips. The 10 spring clamps are specifically distributed in such a way that the upper side and the lower side of each spring clamp are fixed by 2 spring clamps, and the left side and the right side of each spring clamp are fixed by 3 spring clamps. Wherein, every spring clamp all only has two stabilizer blades to compress tightly sealing glass, and every spring clamp links to each other with the help of bolt fillet and window frame structure respectively.
A METHOD of mounting a WINDOW with a spring clip is also provided in patent US 8,087,615B2, entitled WINDOW mounting METHOD, assigned to boeing corporation. The structure of spring clamp installation is adopted, and the key of the structure lies in the spring clamp and the meshing teeth on the window frame, and the spring clamp is installed and fixed through the meshing teeth.
The drawback of this spring clip mounting by boeing company is that: the spring clamp is small in size, easy to shift in position when a worker uses a constant force device for installation, and easy to loosen in a flying or taking-off and landing stage due to the general stability of the spring clamp.
The manner of installation of the airbus is shown in figures 3 to 5. Shown is the installation of the sealing glass employed by air passenger a 319/320/321. As can be seen, instead of using a spring clip to hold the sealing glass as in boeing, an integral metal gasket is used to press the sealing glass against the frame and is bolted to the sash. Specifically, for example, referring to fig. 5, the side of the peripheral edge of the seal glass facing the outside of the cabin abuts against the inside of the window frame, and the side of the peripheral edge of the seal glass facing the inside of the cabin abuts against the metal seal ring. In addition, the metal seal ring is connected to an inner ring facade of the window frame protruding towards the cabin through screws.
The defects of the installation mode of the metal sealing ring of the air passenger company are as follows: it is necessary to provide an inner ring projecting toward the inside of the window frame and fixedly mount the metal seal ring to the vertical surface of the inner ring by two threaded connectors arranged in an intersecting manner, resulting in a heavy weight of the mounting assembly.
L-shaped window frames, which are generally L-shaped in cross-section, are increasingly used on aircraft due to the advantages of being easy to shape and easy to mount to wall panels. In the L-shaped window frame, the vertical surface protruding into the cabin on the outer periphery of the window frame is spaced apart from the inner periphery of the window frame by a certain distance for attachment to the wall panel, so it is inconvenient to directly attach the transparent member on the outer periphery of the window frame.
SUMMERY OF THE UTILITY MODEL
The object of the present invention is to solve the above-mentioned problems and to provide a mounting assembly for mounting a transparent element of an aircraft observation window, said mounting assembly of said transparent element of an aircraft observation window comprising a window frame and a pressure ring, wherein,
the window frame comprises a window frame outer ring and a window frame inner ring extending inwards from the window frame outer ring in the radial direction;
the compression ring comprises a compression ring outer ring and a compression ring inner ring which radially and inwardly extends from the compression ring outer ring;
the outer ring of the window frame is connected with the outer ring of the pressure ring so as to clamp and press the transparent part of the aircraft observation window between the inner ring of the window frame and the inner ring of the pressure ring,
it is characterized in that the preparation method is characterized in that,
the window frame outer ring is provided with the orientation the outstanding clamping ring installation department in clamping ring outer ring, the window frame outer ring passes through the clamping ring installation department with the clamping ring outer ring is connected.
The arrangement of the pressure ring mounting part allows the pressure ring to be conveniently mounted with the window frame, so that the transparent part of the aircraft observation window is mounted.
In a preferred embodiment according to the utility model discloses a mounting assembly for installing aircraft observation window transparency, the clamping ring installation department is along circumference distribution a plurality of hat type supports on the window frame outer lane, hat type support including be fixed in the support fixed part of window frame outer lane and by the support fixed part supports and moves towards the protruding support protruding portion in clamping ring outer lane.
The cap-shaped support is light in weight and convenient to manufacture, and is beneficial to reducing weight and cost of the transparent part mounting assembly of the aircraft observation window.
In a preferred embodiment of a mounting assembly according to the present invention for mounting an aircraft viewing window transparency, the bracket projection is provided with a fastener passing hole therethrough;
a supporting plate nut is arranged on one side, back to the compression ring outer ring, of the protruding portion of the support, and a screw hole of the supporting plate nut is coaxial with the fastener through hole;
the press ring outer ring is provided with a press ring mounting hole, so that a threaded fastener sequentially penetrates through the press ring mounting hole and is screwed into the screw hole through the fastener through hole, and the window frame outer ring is connected with the press ring outer ring.
The arrangement of the supporting plate nut enables the compression ring to be fixed conveniently and quickly.
In a preferred embodiment of a mounting assembly according to the present invention for mounting an aircraft viewing window transparency, the carrier nut is fixed with the bracket projection by a rivet.
Installing the splint nut by rivets saves installation space.
In a preferred embodiment of a mounting assembly according to the present invention for mounting an aircraft viewing window transparency, the rivet is countersunk towards the end of the compression ring outer ring.
The countersunk design of the rivet at this provides better conditions for the mounting of the pressure ring.
In a preferred embodiment of a mounting assembly according to the present invention for mounting an aircraft viewing window transparency, the end of the rivet facing away from the compression ring outer race is countersunk.
The countersunk design of the rivet at this point saves installation space of the pallet nut on the hat-shaped bracket.
In a preferred embodiment of a mounting assembly for mounting an aircraft window transparency according to the invention, the tightening torque of the threaded fastener is 1.3-1.8N m.
The tightening torque ensures the installation firmness of the transparent part of the aircraft observation window under various mechanical working conditions of the aircraft, particularly under the negative pressure state of the aircraft.
In a preferred embodiment of a mounting assembly for mounting an aircraft viewing window transparency according to the present invention, the threaded fastener is a screw.
The selection of screws as threaded fasteners reduces the number of parts required.
In a preferred embodiment according to the utility model discloses a mounting assembly for installing aircraft observation window transparency, the support fixed part pass through threaded connection with the window frame outer lane is fixed.
The cap-shaped bracket and the outer ring of the window frame are fixed conveniently.
In a preferred embodiment of a mounting assembly for mounting an aircraft viewing window transparency according to the present invention, the plurality of cap brackets is 10 in number.
The multiple hat-type brackets thus arranged compromise the reliability of installation as well as the overall weight and cost of the assembly.
To sum up, according to the utility model discloses a beneficial effect briefly summarizes as follows:
1) compared with the installation mode of the spring clamp of the Boeing series, the utility model has the characteristics of convenient and rapid installation and stronger installation stability than the installation mode of the spring clamp;
2) compare in the mounting means of air passenger series's metal seal circle, the utility model discloses a weight of clamping ring installation department is lighter.
Drawings
FIG. 1 is a perspective view of a prior art mounting assembly for mounting an aircraft window transparency employing a spring clip;
FIG. 2 is an exploded perspective view of a spring clip of the prior art mounting assembly for mounting an aircraft window transparency employing the spring clip shown in FIG. 1;
FIG. 3 is a perspective view of a prior art mounting assembly for mounting a transparency of an aircraft viewing window employing a metal seal ring;
FIG. 4 is an exploded perspective view of the mounting assembly for mounting an aircraft window transparency shown in FIG. 3 employing a metal seal ring;
FIG. 5 is a partial cross-sectional view taken along section line B-B of FIG. 3, showing a particular mounting arrangement for the aircraft viewing window transparency;
FIG. 6 is an exploded perspective view of a mounting assembly for mounting an aircraft viewing window transparency in accordance with a preferred embodiment of the present invention;
FIG. 7 is a perspective view of a cap bracket for mounting a mounting assembly for an aircraft viewing window transparency according to a preferred embodiment of the present invention showing fastener passing holes in the cap bracket; and
fig. 8 is a perspective view of a cap bracket of a mounting assembly for mounting an aircraft viewing window transparency according to a preferred embodiment of the present invention showing a pallet nut on the cap bracket.
List of reference numerals
100 mounting assembly
110 window frame
111 outer ring of window frame
112 inner ring of window frame
120 compression ring
121 compression ring outer ring
122 inner ring of pressure ring
200 aircraft viewing window transparency
300 cap type support
310 bracket fixing part
320 bracket projection
321 fastener passing through the hole
330 supporting plate nut
Detailed Description
The following detailed description of the preferred embodiments of the invention, taken in conjunction with fig. 6-8, is not intended to limit the invention.
As shown in fig. 6, a mounting assembly 100 for mounting an aircraft viewing window transparency 200 in accordance with a preferred embodiment of the present invention is shown. The aircraft window transparency 200 is, for example, a passenger window transparency assembly.
The mounting assembly 100 of the aircraft window transparency 200 includes a window frame 110 and a pressure ring 120.
The window frame 110 includes a frame outer ring 111 and a frame inner ring 112 extending radially inward from the frame outer ring 111. As shown in fig. 6, the window frame 110 may preferably have the same shape as the outer circumference of the aircraft window transparency 200. In the embodiment schematically shown in the drawings, the window frame 110 may have a substantially oblong shape. In other words, the window frame 110 may have two ends having substantially curved arc portions, and the two ends may be correspondingly connected by a substantially straight line portion. Further, preferably, the sash outer ring 111 may be disposed on the same plane as the sash inner ring 112, or alternatively, the sash outer ring 111 and the sash inner ring 112 may be disposed on two different planes that are substantially parallel.
As best shown in fig. 6, the window frame outer ring 111 has a certain radial width, which can be used to arrange fasteners for installation with the bulkhead plate, and leaves an installation space for installation with the compression ring 120. The outer ring 111 of the window frame may also be provided with a facade projecting inwards towards the cabin, thus forming an L-shaped window frame for mounting with the cabin wall panel.
The pressure ring 120 includes a pressure ring outer ring 121 and a pressure ring inner ring 122 extending radially inward from the pressure ring outer ring 121. As shown in fig. 6, the pressing ring 120 may preferably have the same shape as the outer circumference of the aircraft window transparency 200, similar to the window frame 110. In the embodiment schematically shown in the drawings, the pressure ring 120 may have a substantially oblong shape. In other words, the two ends of the pressing ring 120 may have substantially curved arc-shaped portions, and the arc-shaped portions at the two ends may be correspondingly connected by substantially straight linear portions. Further, preferably, the pressure ring outer ring 121 and the pressure ring inner ring 122 may be disposed on two different planes that are substantially parallel, or alternatively, the pressure ring outer ring 121 may be disposed on the same plane as the pressure ring inner ring 122.
As best shown in fig. 6, the pressing ring outer ring 121 has a certain radial width so as to leave an installation space for installation with the window frame 110. The pressure ring 120 may preferably be formed from sheet metal of an aluminium alloy, or alternatively from a composite material.
The window frame outer ring 111 and the pressure ring outer ring 121 are connected to sandwich the aircraft observation window transparent member 200 between the window frame inner ring 112 and the pressure ring inner ring 122. In other words, the window frame 110 and the pressing ring 120 are in contact with the peripheral edge of the aircraft window transparency 200 by the radial widths of the window frame inner ring 112 and the pressing ring inner ring 122 thereof, respectively, thereby fixing the aircraft window transparency 200.
In order to be connected window frame outer lane 111 and clamping ring outer lane 121 to press between window frame inner lane 112 and clamping ring inner lane 122 with aircraft observation window transparency 200, according to the utility model discloses an among the installation component 100, be provided with the clamping ring installation department towards clamping ring outer lane 121 salient on the window frame outer lane 111, the window frame outer lane 111 passes through the clamping ring installation department and is connected with clamping ring outer lane 121.
The purpose of the provision of the pressure ring mount is to provide a height that projects inwardly of the outer ring of the window frame to partially or wholly offset the thickness of the aircraft viewing window transparency 200 and to provide a mounting location for the window frame 110 to the pressure ring 120. Accordingly, the compression ring mounting portion encompassed by the present invention is not limited to the embodiments explicitly shown or suggested herein, but includes any suitable structure that achieves the above objectives.
A preferred embodiment of the pressure ring mounting portion is described further below in connection with fig. 7 and 8.
Preferably, as shown in fig. 7 and 8, the pressing ring mounting part may be configured as a plurality of hat-shaped brackets 300 circumferentially distributed on the window frame outer ring 111.
In the preferred embodiment shown in the drawings, the number of the plurality of cap type brackets 300 may be 10. Wherein, 3 cap-shaped brackets 300 are respectively arranged at the arc-shaped parts at the two ends of the window frame 110 and the pressure ring 120, and 2 cap-shaped brackets 300 are respectively arranged at the middle straight part of the window frame 110 and the pressure ring 120. It is noted that the arrangement scheme of the cap brackets 300 is not limited thereto, but the total number of the cap brackets 300 and the distribution thereof may be selected according to actual needs.
The material of the cap bracket 300 may be selected according to the material of the window frame 110, and preferably, for example, a metal material or a composite material is selected.
In order to achieve the above-described object of the pressure ring mounting part, the cap bracket 300 may include a bracket fixing part 310 fixed to the window frame outer ring 111 and a bracket protrusion part 320 supported by the bracket fixing part 310 and protruding toward the pressure ring outer ring 121. Preferably, the holder fixing part 310 and the holder protrusion part 320 may be integrally formed in a manufacturing manner, for example, by sheet metal or punching. Alternatively, the bracket fixing portion 310 and the bracket protrusion portion 320, which are separately manufactured, may be connected together by a common fixing connection manner. The holder securing portion 310 and the holder protrusion 320 may be any suitable shape.
The bracket fixing portion 310 may be fixed to the window frame outer ring 111 preferably by a screw connector. The bracket fixing portion 310 may be fixed to the window frame outer ring 111 by other means such as gluing, welding, or the like. Further, the holder protrusion 320 preferably has a flat surface portion to which the press ring is contacted.
Further preferably, in the case of connecting the window frame 110 and the pressing ring 120 by a screw fastener, the holder protrusion 320 may be provided with a fastener passing hole 321 penetrating the holder protrusion 320. The bore diameter of the fastener passing bore 321 is preferably larger than the outer diameter of the fastener with which it is mated. In cooperation therewith, a retainer nut 330 may be provided on a side of the holder protrusion 320 facing away from the pressure ring outer 121, and a screw hole of the retainer nut 330 is preferably coaxial with the fastener passing hole 321. The pallet nut 330 is preferably secured with rivets to the bracket tabs 320. In order to better contact with the pressure ring outer ring 121, in the case where the pallet nut 330 and the bracket projection 320 are fixed by rivets, one end of the rivets facing the pressure ring outer ring 121 may be provided to be countersunk. More preferably, the end of the rivet facing away from the outer ring 121 may also be countersunk.
In order to fix the pressing ring 120 to the pressing ring mounting portion on the window frame outer ring 111, a pressing ring mounting hole may be provided on the pressing ring outer ring 121. Specifically, in the case where the pressure ring mounting portion is the above-described cap bracket 300, the screw fastener is screwed into the screw hole through the pressure ring mounting hole and the fastener passing hole 321 in this order, thereby connecting the window frame outer ring 111 and the pressure ring outer ring 121. Preferably, the tightening torque of the threaded fastener is, for example, 1.3-1.8N m, for example 1.6N m. The threaded fastener may comprise a screw.
The following describes the steps of assembling a mounting assembly 100 for mounting an aircraft viewing window transparency 200 in accordance with a preferred embodiment of the present invention.
First, the components constituting the mounting assembly 100 are prepared. Each aircraft window transparency 200 installation requires 10 (the number is determined as desired, and can be adjusted according to the window frame 110 size and fastener location) cap brackets 300 and pallet nuts 330. The installation of each aircraft window transparency 200 also requires a press ring 120 and a window frame 110 connected thereto. In order to complete the assembly, a corresponding number of bolts and washers also need to be provided.
Secondly, manufacturing and mounting each part, wherein the mounting steps are as follows:
1) the above-mentioned hat-shaped bracket 300 (as shown in fig. 7 and 8) is manufactured using a metal sheet mold or a composite material molding mold, and the bracket fixing portions 310 at both sides of the hat-shaped bracket 300 should be previously formed according to the fastener hole positions reserved on the window frame outer ring 111 so as to be fixedly mounted to the window frame outer ring 111.
2) The plate nut 330 is mounted on the inner side of the cap type bracket 300 by a rivet, and the screw hole of the plate nut 330 is overlapped (coaxial) with the fastener passing hole 321 of the bracket projection 320 in the middle of the cap type bracket 300, and the rivet for connecting the plate nut 330 with the cap type bracket 300 is preferably countersunk on both sides (at least the side contacting with the pressure ring 120 is countersunk). After completion as shown in fig. 8.
3) Repeating the steps 1) and 2) until 10 sets of the cap type bracket 300 and the pallet nut 330 are manufactured (the specific number is determined as required).
4) The fabricated assembly of the above-described 10 sets of the hat-shaped bracket 300 and the pallet nut 330 is mounted to the window frame outer ring 111.
5) Each window frame 110 corresponds to one press ring 120, and the press ring 120 needs to be correspondingly provided with holes according to the fixing position of the cap-shaped support 300 on the outer ring 111 of the window frame.
6) As shown in fig. 6, the transparent aircraft observation window member 200 and the press ring 120 are sequentially pressed against the window frame 110, and the bolts are tightened by a torque of 1.3 to 1.8N × m.
7) After installation, the aircraft window transparency 200 is checked for centering and for a uniform gap between the aircraft window transparency 200 and the window frame 110.
The inventive concept has been described in detail with reference to specific preferred embodiments thereof, but further modifications and variations within the scope of the inventive concept will be apparent to those skilled in the art, which modifications and variations fall within the scope of the appended claims.
Claims (10)
1. A mounting assembly (100) for mounting an aircraft viewing window transparency (200), the mounting assembly (100) of the aircraft viewing window transparency (200) comprising a window frame (110) and a pressure ring (120), wherein,
the sash (110) comprises a sash outer ring (111) and a sash inner ring (112) extending radially inward from the sash outer ring (111);
the compression ring (120) comprises a compression ring outer ring (121) and a compression ring inner ring (122) which extends radially inwards from the compression ring outer ring (121);
the window frame outer ring (111) is connected with the pressure ring outer ring (121) to clamp and press the transparent part (200) of the aircraft observation window between the window frame inner ring (112) and the pressure ring inner ring (122),
it is characterized in that the preparation method is characterized in that,
the window frame outer ring (111) is provided with a pressing ring installation portion facing the pressing ring outer ring (121) in a protruding mode, and the window frame outer ring (111) is connected with the pressing ring outer ring (121) through the pressing ring installation portion.
2. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 1,
the clamping ring installation part is distributed along the circumferential direction a plurality of cap type supports (300) on the window frame outer ring (111), the cap type supports (300) are fixed on the support fixing part (310) of the window frame outer ring (111) and the support protruding part (320) supported by the support fixing part (310) and oriented to the protruding clamping ring outer ring (121).
3. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 2,
the bracket protruding part (320) is provided with a fastener passing hole (321) penetrating through the bracket protruding part (320);
a supporting plate nut (330) is arranged on one side, back to the pressure ring outer ring (121), of the support protruding portion (320), and a screw hole of the supporting plate nut (330) is coaxial with the fastener through hole (321);
the press ring outer ring (121) is provided with a press ring mounting hole, so that a threaded fastener sequentially penetrates through the press ring mounting hole and the fastener through hole (321) and is screwed into the screw hole, and the window frame outer ring (111) is connected with the press ring outer ring (121).
4. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 3,
the pallet nut (330) is fixed to the bracket protrusion (320) by a rivet.
5. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 4,
one end of the rivet, which faces the pressing ring outer ring (121), is installed in a countersunk mode.
6. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 4,
one end, back to the pressing ring outer ring (121), of the rivet is installed in a countersunk mode.
7. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 3,
the tightening torque of the threaded fastener is 1.3-1.8N m.
8. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 3,
the threaded fastener is a screw.
9. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 2,
the support fixing part (310) is fixed with the window frame outer ring (111) through a threaded connecting piece.
10. The mounting assembly (100) for mounting an aircraft viewing window transparency (200) according to claim 2,
the number of the plurality of cap type brackets (300) is 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920619264.3U CN209870717U (en) | 2019-04-30 | 2019-04-30 | Installation assembly for installing transparent part of aircraft observation window |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920619264.3U CN209870717U (en) | 2019-04-30 | 2019-04-30 | Installation assembly for installing transparent part of aircraft observation window |
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| Publication Number | Publication Date |
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| CN209870717U true CN209870717U (en) | 2019-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920619264.3U Active CN209870717U (en) | 2019-04-30 | 2019-04-30 | Installation assembly for installing transparent part of aircraft observation window |
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| Country | Link |
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| CN (1) | CN209870717U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112960136A (en) * | 2021-02-08 | 2021-06-15 | 中国商用飞机有限责任公司 | Plugging device, aircraft window and plugging method thereof |
-
2019
- 2019-04-30 CN CN201920619264.3U patent/CN209870717U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112960136A (en) * | 2021-02-08 | 2021-06-15 | 中国商用飞机有限责任公司 | Plugging device, aircraft window and plugging method thereof |
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