CN115370277A - Hatch door seal assembly - Google Patents
Hatch door seal assembly Download PDFInfo
- Publication number
- CN115370277A CN115370277A CN202211062888.2A CN202211062888A CN115370277A CN 115370277 A CN115370277 A CN 115370277A CN 202211062888 A CN202211062888 A CN 202211062888A CN 115370277 A CN115370277 A CN 115370277A
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- Prior art keywords
- door
- seal assembly
- frame
- aircraft
- seal
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- 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.)
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Links
- 238000007789 sealing Methods 0.000 claims abstract description 104
- 230000001681 protective effect Effects 0.000 claims description 2
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 239000004744 fabric Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Images
Classifications
-
- E—FIXED CONSTRUCTIONS
- E06—DOORS, WINDOWS, SHUTTERS, OR ROLLER BLINDS IN GENERAL; LADDERS
- E06B—FIXED OR MOVABLE CLOSURES FOR OPENINGS IN BUILDINGS, VEHICLES, FENCES OR LIKE ENCLOSURES IN GENERAL, e.g. DOORS, WINDOWS, BLINDS, GATES
- E06B7/00—Special arrangements or measures in connection with doors or windows
- E06B7/16—Sealing arrangements on wings or parts co-operating with the wings
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- 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
- B64C1/1407—Doors; surrounding frames
Abstract
The present invention provides a hatch seal assembly, wherein the hatch seal assembly comprises: a cabin door; a door frame; the door frame stopper is arranged on the door frame; a fixed frame fixed to a side of the door facing an interior of the aircraft and having a recessed portion at a periphery of the door; and a sealing member continuously installed in the recess of the fixed frame around the circumference of the hatch door and contacting and compressively deformed by the door frame stopper when the hatch door is closed, wherein a cross-sectional area of a hollow cavity of the sealing member is continuously varied along the circumference of the hatch door.
Description
Technical Field
The invention relates to a cabin door sealing assembly for an airtight cabin door of an airplane, which allows the leakage quantity of the pressurized state in the airplane cabin at the cabin door to meet the design requirement, ensures the pressure in the airplane cabin to be stable, and prevents the rainwater outside the airplane from seeping into the airplane cabin, and belongs to the field of the structural design of the airplane cabin door.
Background
In the flying period, in order to ensure that the leakage amount at the cabin door in a charging state in the airplane cabin meets the design requirement, the pressure in the airplane cabin is stable, and the rainwater outside the airplane is prevented from seeping into the airplane cabin, a sealing structure suitable for the cabin door of the airtight area of the airplane is needed.
The sealing structure of the design of the main stream type for the cabin door of the pressurizing area mainly comprises: 1) A tongue seal and corresponding seal structure (e.g., BOEING corporation model), and 2) a hollow cavity seal and corresponding seal structure (e.g., AIRBUS corporation model, ERJ model, C series model).
However, the existing sealing structure of the hatch door has several problems: 1) The tongue-shaped sealing element has extremely high requirements on the position posture of the cabin door, the manufacturing process of the sealing element and the material of the sealing element, and any one of the position posture of the cabin door, the manufacturing process of the sealing element and the material of the sealing element has slight deviation, namely the phenomena of air leakage and water leakage are easy to occur, so the design requirement and the manufacturing requirement of the cabin door are increased; 2) The hollow cavity sealing element has higher installation requirements on the sealing element, particularly, the sealing element is usually designed to have a variable cross section at a corner, and if the sealing element is not installed in place at the corner, air leakage is easily caused, so that higher requirements on installation fineness are provided.
Accordingly, there remains a need for further improvements in the structure of existing hatch seal assemblies.
Disclosure of Invention
In view of the above problems of the prior art and in view of the combination of the opening and closing movements of the doors of the mainstream aircraft, including the lifting movement and the pivoting movement, there is a further need for the compression deformation of the sealing member, it is an object of the present invention to provide a door seal assembly for an airtight door of an aircraft, which allows the leakage amount of the pressurized state inside the aircraft cabin at the door to meet the design requirements, ensures the pressure inside the aircraft cabin to be stable, and also prevents rain water outside the aircraft from seeping into the aircraft cabin.
To solve the above problems, the present invention provides a door seal assembly for an airtight door of an aircraft, wherein the door seal assembly comprises: a cabin door; a door frame; the door frame stopper is arranged on the door frame; a fixing frame fixed to a side of the door facing the interior of the aircraft and having a recessed portion at a periphery of the door; and a sealing member continuously installed in the recess of the fixed frame around the circumference of the hatch door and contacting and compressively deformed by the door frame stopper when the hatch door is closed, wherein a cross-sectional area of a hollow cavity of the sealing member is continuously varied along the circumference of the hatch door.
According to one aspect of the invention, the cross-sectional area of the hollow cavity of the seal varies continuously along the perimeter of the door and is greatest at the perimeter near the lower portion of the door, and is next to the perimeter near both sides of the door, and smallest at the perimeter near the upper portion of the door.
According to one aspect of the invention, the door sealing assembly further comprises a pneumatic sealing plate mounted on the outer skin of the outside of the door and near the periphery of the upper part of the door, and wherein the pneumatic sealing plate cooperates with the outer skin of the door and the outer skin of the door frame to have an aerodynamic profile.
According to an aspect of the present invention, the hatch sealing assembly further comprises a base fixture mounted along the perimeter of the hatch door into the recessed portion of the fixed frame by fasteners, and a groove portion of the base fixture engages the base raised portion of the sealing member by snap-fitting, such that the sealing member is detachably secured in the recessed portion of the fixed frame.
According to an aspect of the invention, the door seal assembly further comprises a lateral support selectively mounted into the recessed portion of the fixed frame by a fastener, and a support wall of the lateral support extends toward the interior of the aircraft; and the supporting wall of the lateral support defines, together with the first concave side wall of the concave portion of the fixed frame close to the perimeter of the door, a space allowing the deformation of the hollow cavity of the seal.
According to an aspect of the invention, at the periphery near the lower part of the door and at the periphery near the lower left and right corners of the door, the supporting wall of the lateral support extends towards the interior of the aircraft for a length greater than the length of the first concave side wall of the concave portion of the fixed frame towards the interior of the aircraft.
According to an aspect of the invention, at the periphery near the upper portion of the door and at the periphery near the upper left corner and the upper right corner of the door, the length of the support wall of the lateral support extending toward the interior of the aircraft is smaller than the length of the first concave sidewall of the concave portion of the fixed frame extending toward the interior of the aircraft.
According to one aspect of the invention, the cavity side wall of the hollow cavity of the seal optionally has a vent hole at a location remote from the perimeter of the door, allowing air pressure within the aircraft cabin to enter the interior of the hollow cavity of the seal.
According to an aspect of the present invention, the door seal assembly further includes a shielding plate installed outside the door frame stopper at a lower portion of the door frame for protecting the door frame stopper from being stepped on by a person.
The invention aims at the problems that the sealing element of the hollow cavity has higher requirements on the position and the attitude of the cabin door and the sealing element is installed more finely, selects the section form of the sealing element with the special-shaped structure, provides a sealing structure according to the sealing element, accurately defines the installation requirements of the sealing element, and reduces the manufacturing difficulty and the assembly difficulty of the sealing element.
Drawings
In order to describe the manner in which the above-recited and other advantages and features of the invention can be obtained, a more particular description of the invention briefly described above will be rendered by reference to exemplary embodiments thereof which are illustrated in the appended drawings. Understanding that these drawings depict only exemplary embodiments of the invention and are not therefore to be considered to be limiting of its scope, the invention will be described and explained with additional specificity and detail through the use of the accompanying drawings in which:
FIG. 1 is a schematic view of a hatch seal assembly according to a preferred embodiment of the invention.
Figure 2 is a schematic view of the overall shape of the door frame stop of the hatch seal assembly.
Figure 3 is a schematic view of the overall shape of the sealing member of the hatch sealing assembly.
Figure 4 isbase:Sub>A cross-sectional view of the door seal assembly at the upper portion of the door taken along linebase:Sub>A-base:Sub>A in figure 1.
Figure 5 is a cross-sectional view of the door seal assembly at the upper right corner of the door, taken along line B-B in figure 1.
Figure 6 is a cross-sectional view of the door seal assembly at the right side of the door taken along line C-C in figure 1.
Figure 7 is a cross-sectional view of the hatch seal assembly taken along line D-D in figure 1 at the lower right corner of the hatch.
Figure 8 is a cross-sectional view of the door seal assembly at the lower portion of the door taken along line E-E in figure 1.
Figure 9 is a cross-sectional view of the door seal assembly of figure 4 with the door closed, and without the deformation of the seal as a result of compression by the doorframe stop.
Figure 10 is a cross-sectional view of the hatch seal assembly of figure 5 with the hatch closed and without the seal deformed by the compression of the door frame stop.
Figure 11 is a cross-sectional view of the door seal assembly of figure 6 with the door closed, wherein the deformation of the seal as a result of being pressed against the doorframe stop is not shown.
Figure 12 is a cross-sectional view of the door seal assembly of figure 7 with the door closed, wherein the deformation of the seal as a result of being pressed against the doorframe stop is not shown.
Figure 13 is a cross-sectional view of the door seal assembly of figure 8 with the door closed, wherein deformation of the seal by compression of the doorframe stop is not shown.
Figures 1 to 13 are drawn substantially to scale. However, in other embodiments, other relative dimensions may be used. Here and in the following all, the same features appearing in different figures are denoted by the same or similar reference numerals.
List of reference numerals:
1. door frame stopper
2. Pneumatic sealing plate
3. Sealing element
4. Fixing frame
5. Outer skin of cabin door
6. Base fixing piece
7. Lateral support
8. Fastening piece
9. Protective plate
Detailed Description
The present invention will be further described with reference to the following detailed description and the accompanying drawings, wherein the following description sets forth further details for the purpose of providing a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms other than those described herein, and it will be readily apparent to those skilled in the art that the present invention may be embodied in many different forms without departing from the spirit or essential characteristics thereof, and therefore the scope of the invention should not be limited by the specific embodiments disclosed herein.
Fig. 1 schematically shows a door seal assembly of a preferred embodiment of the present invention, viewed from the interior of an aircraft towards a door, comprising a door of an aircraft air-tight cabin, a door frame (not shown) cooperating with the door, a door frame stop 1 mounted on the door frame, a fixed frame 4 mounted on the side of the door facing the interior of the aircraft, and a sealing member 3 mounted on the fixed frame 4 in the form of a hollow chamber tube, which comes into contact with the door frame stop 1 and deforms under pressure to produce a sealing effect when the door is closed.
In a preferred embodiment of the invention, the door frame stop 1 of the hatch seal assembly is shaped as a whole, as shown in figure 2, to be arranged around the periphery of the door frame.
In a preferred embodiment of the invention, the overall shape of the sealing member 3 of the door seal assembly is arranged around the perimeter of the door as shown in figure 3.
Preferably, the fixing frame 4 may have a recessed portion at the periphery of the hatch door. The seal 3 may be continuously around the perimeter of the hatch door and mounted in a recessed portion of the fixed frame 4.
Preferably, the recessed portion of the fixed frame 4 may have a first recessed sidewall close to the perimeter of the door and a second recessed sidewall remote from the perimeter of the door. The first concave side wall is used for limiting the space for the hollow cavity of the sealing member 3 to deform. The fixed frame 4 is selectively mounted to the inside of the door at some locations of the second concave sidewall by conventional fasteners 8.
Preferably, in order to ensure that the doors of the aircraft capsule do not open or close unintentionally, the doors of the mainstream models comprise a door lift mechanism safety function. In particular, the opening movement of the hatch of the mainstream model comprises the presence of a first lifting movement towards the upper side and a second pivoting movement towards the outer side when the hatch is open, and the closing movement of the hatch of the mainstream model comprises the presence of a first pivoting movement towards the inner side and a second falling movement towards the lower side when the hatch is closed.
Considering that the opening and closing movements of the hatches of the mainstream model include a combination of a lifting movement and a pivoting movement, the compression deformation of the sealing element 3 varies over the entire perimeter of the hatch, and therefore the cross-sectional area of the hollow cavity of the sealing element 3 may vary continuously along the perimeter of the hatch, as will be described in detail below.
Turning now to FIG. 4,base:Sub>A cross-sectional view of the door seal assembly at the upper portion of the door is schematically shown, taken along line A-A in FIG. 1.
The sealing element 3 may be mainly made of rubber material, and the surface and the internal reinforcing fabric together form a tube of a hollow cavity with a special-shaped structure, and the C-shaped sealing element base fixing piece 6, the L-shaped sealing element lateral supporting piece 7, the fixing frame 4 and the door frame stopper 1 of the door frame together determine the appearance of the sealing element after installation. After the cabin door is closed, the sealing stopper 1 on the door frame structure of the body is contacted with the sealing element 3 and extrudes the sealing element 3, so that the sealing function is realized.
In particular, the door frame stopper 1 presses the sealing element inwards after contacting with the reinforcing fabric on the outer surface of the sealing element 3, the pressing amount of the door frame stopper 1 to the sealing element 3 can be 30-50% of the area size of the sealing element 3,
due to the upward lifting movement of the door when opened, the outer skin of the door frame at the upper part of the door has a corresponding recess for accommodating the upward lifting movement of the door. However, this leaves the presence of the aerodynamic profile of the outer skin of the door frame at the upper part of the door missing.
In a preferred embodiment, the hatch seal assembly may also include a pneumatic seal plate 2. The pneumatic sealing plate 2 is mounted on the outer skin 5 of the outside of the door close to the periphery of the upper part of the door and the extended part of the pneumatic sealing plate 2 blocks the recess of the outer skin of the door frame, so that the pneumatic sealing plate 2 cooperates with the outer skin 5 of the door and the outer skin of the door frame with an aerodynamic profile.
In a preferred embodiment, the hatch sealing assembly may further comprise a base fixture 6 for detachably securing the sealing member 3 to the stationary frame 4. The base fixture 6 may be mounted along the perimeter of the door in a recessed portion of the fixed frame 4 by conventional fasteners 8.
Preferably, the groove portion of the base fixing member 6 engages the base projection portion of the sealing member 3 by snap-fitting, and the sealing member 3 can be easily attached to and detached from the fixing frame 4 by elastic deformation of the material of the sealing member 3.
Preferably, the base fixing member 6 may have a substantially flat "C" shape in cross section, and the bent portions at both ends serve as groove portions for connecting the sealing members 3. Preferably, the base of the seal 3 may be substantially flat in cross-section in the shape of a "convex" with both ends slightly raised as base raised portions.
Preferably, the base of the sealing member 3 may have a recess to receive the fixing member 8.
In a preferred embodiment, the door seal assembly may further comprise lateral supports 7 for limiting the deformation of the seal 3 in a certain space, ensuring the airtight performance of the door. In particular, the supporting wall of the lateral support 7 defines, together with the first concave side wall of the concave portion of the fixed frame 4 close to the perimeter of the door, a space that allows the deformation of the hollow cavity of the sealing element 3.
Preferably, the lateral supports 7 can be selectively mounted by means of conventional fasteners 8 in the recessed portion of the fixed frame 4, with the supporting walls of the lateral supports 7 extending a predetermined distance towards the interior of the aircraft, but the structure of the lateral supports 7 varies everywhere along the perimeter of the door.
Due to the downward-directed back-down movement of the door when closed, the amount and direction of deformation of the sealing member 3 in contact with the door frame 1 and the compression deformation will be affected by the back-down movement and will be different everywhere along the perimeter of the door.
Considering the direction of deformation of the seal 3 in contact with the door frame stop 1 and the pressing deformation, further reference is made to fig. 5-8, where fig. 5 shows a sectional view of the door seal assembly at the upper right corner of the door, taken along the line B-B in fig. 1, fig. 6 shows a sectional view of the door seal assembly at the right side of the door, taken along the line C-C in fig. 1, fig. 7 shows a sectional view of the door seal assembly at the lower right corner of the door, taken along the line D-D in fig. 1, and fig. 8 shows a sectional view of the door seal assembly at the lower part of the door, taken along the line E-E in fig. 1.
With further reference to fig. 9-13, which show cross-sectional views of the door seal assembly of fig. 4-8 when the door is closed, in view of the amount of deformation of the seal 3 in contact with and in compression deformation of the door frame stop 1, the deformation of the seal 3 due to compression by the door frame stop 1 is not shown.
Preferably, at the periphery close to the lower part of the door and at the periphery close to the lower left and right corners of the door, the length of the support wall of the lateral support 7 extending towards the interior of the aircraft is greater than the length of the first concave side wall of the concave portion of the fixed frame 4 extending towards the interior of the aircraft.
Preferably, at the peripheries close to the left and right sides of the door, the side supports 7 may not be fitted at the peripheries close to the left and right sides of the door, taking into account that the frictional forces of the seal 3 acting there on the downward-directed fall movement of the door when closed are in the direction of extension of the seal 3, while still ensuring that the seal 3 is not deformed too much to cause damage and tightness of contact of the seal 3 with the door frame barrier 1.
Preferably, at the periphery close to the upper part of the door and at the periphery close to the upper left and right corners of the door, the length of the supporting wall of the lateral support 7 extending towards the interior of the aircraft is less than the length of the first concave side wall of the concave portion of the fixed frame 4 extending towards the interior of the aircraft.
Preferably, the cross-sectional area of the hollow cavity of the seal 3 around the perimeter of the door is continuously variable and is greatest at the perimeter near the lower portion of the door, next to the perimeter near both sides of the door, and smallest at the perimeter near the upper portion of the door. This design thus also results in less deformation of the sealing member 3 on the whole when opening and closing the door, which is less labour-saving and still meets the sealing requirements.
In a preferred embodiment, such as schematically shown in fig. 6, the cavity side wall of the hollow cavity of the seal 3 is optionally provided with several ventilation holes at a position away from the perimeter of the door, allowing higher gas pressures inside the aircraft cabin to be able to enter the interior of the hollow cavity of the seal 3.
When the hollow cavity of the seal 3 is in contact with the door frame stop 1 and deformed by pressure, the higher air pressure inside the aircraft cabin enters inside the hollow cavity of the seal 3, so that the seal 3 abuts against the door frame stop 1, contributing to the improved air tightness of the seal 3 and therefore of the entire door seal assembly.
It will be appreciated that the position of the vent is not limited to the left and right sides of the door as shown in figure 6, but may be at other positions around the door.
In a preferred embodiment, as shown in fig. 12 and 13, a protection plate is installed outside the door frame stopper 1 at the lower portion of the door frame for protecting the door frame stopper 1 from deformation of the door frame stopper 1 caused by a person stepping on the door frame stopper 1 when entering or exiting the aircraft interior through the door, resulting in failure of the engagement of the door frame stopper 1 with the sealing member 3.
The sealing component is arranged at the peripheral edge of the cabin door structure, the sealing component is different in position according to different airtight working conditions, and the section shape of the sealing component is also adaptively changed. The sealing part is arranged on the periphery of the door frame, the root of the sealing part is installed on the inner side of the door together with the fixed frame by using a base fixing part, and the side wall of the hollow cavity of the sealing part is in contact with the side wall of the concave part of the fixed frame.
The invention realizes the sealing of the aircraft charging area cabin door in a mode that the sealing element 3 has the continuously-changed section of the hollow cavity along the periphery of the cabin door, and according to the size of the supporting structure at the position of the sealing element 3 (the side wall of the concave part of the fixed frame 4, the base fixing piece 6 and the bearing wall of the lateral bearing piece 7), the deformation of the section of the sealing element 7 is accurately limited, and simultaneously, the range of the extrusion amount of the sealing element 3 by the sealing baffle piece 1 in the closed state of the cabin door is limited, so that the sealing performance of the sealing element 3 can be met under the condition that the material consumption of the sealing element 3 is reduced as much as possible.
The invention comprehensively considers the appearance of a sealing element, a cabin door structure and a door frame structure of a machine body, and the sealing element is arranged on a sealing element fixing frame of the cabin door structure. The appearance of the sealing element supporting structure is scientifically designed according to the sealing principle, and the appearance of the sealing element is supported and limited through all parts for limiting the deformation of the sealing element, so that the appearance of the sealing element is ensured to meet the design requirement, and after the cabin door is closed, the sealing element is extruded by the pressure plate part on the door frame structure of the airplane body, and the sealing function of the cabin door of the airplane is realized. The sealing element is arranged on the sealing element supporting structure assembly, so that the appearance of the sealing element can meet the design requirement, and the design difficulty and the manufacturing difficulty of the sealing element are reduced
While various embodiments have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to those skilled in the relevant art that the disclosed subject matter can be embodied in other specific forms without departing from the spirit or essential characteristics thereof.
The present disclosure also includes various modifications and variations within an equivalent range. In addition, various combinations and modes, including only one element, one or more other combinations and modes, also belong to the scope and the idea of the present disclosure.
The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, and not restrictive.
Claims (9)
1. A door seal assembly, characterized in that the door seal assembly comprises:
a cabin door;
a door frame;
the door frame stopper (1), the said door frame stopper (1) is installed on said door frame;
a fixed frame (4), the fixed frame (4) being fixed to a side of the door facing the interior of the aircraft and having a recessed portion at a periphery of the door; and
a sealing member (3), said sealing member (3) being mounted in a recessed portion of said fixed frame (4) continuously around the perimeter of said door and being in contact with said door frame stop (1) and being compressively deformed when said door is closed,
wherein the cross-sectional area of the hollow cavity of the seal (3) is continuously variable along the circumference of the door.
2. The door seal assembly according to claim 1,
the cross-sectional area of the hollow cavity of the seal (3) varies continuously along the perimeter of the hatch and
is largest at the periphery near the lower portion of the door, next to the periphery near both sides of the door, and smallest at the periphery near the upper portion of the door.
3. The door seal assembly according to claim 1,
further comprising a pneumatic sealing plate (2), the pneumatic sealing plate (2) being mounted on an outer skin (5) of the outside of the door and near the periphery of the upper part of the door, and
wherein the pneumatic sealing plate (2) has an aerodynamic profile in cooperation with the outer skin (5) of the hatch and the outer skin of the door frame.
4. The door seal assembly according to claim 1,
further comprising a base fixture (6), the base fixture (6) being mounted by fasteners along the perimeter of the door into a recessed portion of the fixed frame (4), and
the groove part of the base fixing piece (6) is jointed with the base convex part of the sealing piece (3) in a clamping mode, so that the sealing piece (3) is detachably fixed in the concave part of the fixing frame (4).
5. The door seal assembly according to claim 1,
further comprising a lateral support (7), said lateral support (7) being selectively mounted by means of fasteners into a recessed portion of a fixed frame (4) and a support wall of said lateral support (7) extending towards the aircraft interior; and is
The supporting walls of the lateral supports (7) define, together with the first concave side wall of the concave portion of the fixed frame (4) close to the perimeter of the door, a space which allows the deformation of the hollow cavity of the seal (3).
6. The door seal assembly according to claim 5,
at the periphery close to the lower part of the door and at the periphery close to the lower left and right corners of the door, the support wall of the lateral support (7) extends towards the interior of the aircraft for a length greater than the length of the first concave side wall of the concave portion of the fixed frame (4) towards the interior of the aircraft.
7. The door seal assembly according to claim 5,
at the periphery close to the upper part of the door and at the periphery close to the upper left and right corners of the door, the length of the support wall of the lateral support (7) extending towards the interior of the aircraft is less than the length of the first concave side wall of the concave portion of the fixed frame (4) extending towards the interior of the aircraft.
8. The door seal assembly according to claim 1,
the cavity side wall of the hollow cavity of the seal (3) is optionally provided with a vent hole at a position far away from the periphery of the door, allowing the air pressure in the aircraft cabin to enter the interior of the hollow cavity of the seal (3).
9. The hatch seal assembly according to claim 1,
the protective plate (9) is arranged outside the door frame stopper (1) at the lower part of the door frame and used for protecting the door frame stopper (1) from being stepped by people.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211062888.2A CN115370277A (en) | 2022-09-01 | 2022-09-01 | Hatch door seal assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211062888.2A CN115370277A (en) | 2022-09-01 | 2022-09-01 | Hatch door seal assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115370277A true CN115370277A (en) | 2022-11-22 |
Family
ID=84069497
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211062888.2A Pending CN115370277A (en) | 2022-09-01 | 2022-09-01 | Hatch door seal assembly |
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| CN (1) | CN115370277A (en) |
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| CN108430817A (en) * | 2015-12-22 | 2018-08-21 | 东海兴业株式会社 | Seal member and its connecting structure |
| CN111120654A (en) * | 2018-10-30 | 2020-05-08 | 空中客车德国运营有限责任公司 | Aircraft door sealing system and aircraft door assembly |
| CN113371176A (en) * | 2021-07-20 | 2021-09-10 | 中国商用飞机有限责任公司 | Sealing element for an aircraft pressure buildup compartment door and aircraft pressure buildup compartment door equipped with such a sealing element |
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