An aircraft door frame seal stop and aircraft

Abstract

The utility model discloses an aircraft door frame sealing stop piece and aircraft relates to aircraft parts field. The utility model provides an aircraft door frame sealing stop piece, avoids the rainwater infiltration fuselage inside through setting drainage groove, still fills the gap for filling sealant through setting, thereby carries out the protection to the wallboard edge through sealant. The utility model provides an aircraft, and the rainwater between aircraft door frame sealing stop piece and sealing piece can flow out in time through drainage groove, thereby avoids the rainwater infiltration fuselage inside, still forms the filling gap through surrounding setting side plate part, wallboard and bottom edge part, and the filling gap is used for filling sealant, thereby carries out the protection to the wallboard edge through sealant.

Description

Technical Field

[0001] This utility model relates to the field of aircraft parts, and in particular to an aircraft door frame sealing component and an aircraft. Background Technology

[0002] For pressurized aircraft, a sealing element must be installed around the door frame, which must cooperate with the sealing element around the door to achieve the sealing function of the pressurized cabin door. Considering manufacturing and assembly tolerances, a certain design clearance must be reserved between the door and the fuselage door frame and panel.

[0003] In rainy weather, external rainwater can seep into the semi-enclosed space formed by the sealing elements and baffles through the gaps between the hatches and the fuselage. If the rainwater cannot drain out in time, even a slight misalignment between the sealing elements can allow rainwater to seep into the fuselage, causing leaks. Furthermore, due to their humid and heat-sensitive properties and their susceptibility to impact, heat, and shock, the opening edges of the composite fuselage panels require edge protection to prevent damage from impacts, wind erosion, and moisture infiltration, which could affect the panels' mechanical properties.

[0004] Therefore, it is urgent to propose a solution to the above problems. Utility Model Content

[0005] The first objective of this utility model is to provide an aircraft door frame sealing baffle to solve the problems in the prior art where rainwater cannot drain between the sealing baffles and the sealing elements on the aircraft door frame, and the edges of the wall panels are not effectively protected.

[0006] The second objective of this invention is to provide an aircraft that solves the problems in the prior art where rainwater cannot drain between the sealing elements on the aircraft door frame and the edges of the wall panels are not effectively protected.

[0007] To achieve this objective, the present invention adopts the following technical solution:

[0008] An aircraft door frame sealing element is installed on an aircraft door frame. The aircraft door frame includes a main board portion and two side panels connected to both sides of the main board portion. One of the side panels is fitted to a wall panel. The aircraft door frame sealing element includes a bottom edge portion, a belly edge portion, and a flange portion. One end of the belly edge portion is connected to the bottom edge portion, and the other end is connected to the flange portion. The bottom edge portion is fitted to the main board portion. The flange portion is located on the side of the belly edge portion closer to the wall panel, and the flange portion can abut against a seal on the aircraft door. The bottom edge portion, the belly edge portion, and the flange portion can form a drainage groove. The side panels, the wall panel, and the bottom edge portion can form a filling gap, which is used to fill a sealant.

[0009] Optionally, along the thickness direction of the wall panel, the length of the bottom edge is greater than the length of the flange.

[0010] Optionally, the aircraft door frame sealing member further includes an extension portion, which includes a first extension sub-part and a second extension sub-part. One end of the first extension sub-part is connected to the bottom edge portion, and the other end is connected to one end of the second extension sub-part. The second extension sub-part is fitted and installed on the main board portion, and the first extension sub-part is fitted and installed on the wall panel. The first extension sub-part, the wall panel, and the bottom edge portion can form the filling gap.

[0011] Optionally, the end of the flange portion away from the ventral edge portion is arc-shaped.

[0012] Optionally, the connection between the flange and the ventral edge is rounded.

[0013] And / or, the connection between the ventral edge and the bottom edge is made of a rounded transition.

[0014] Optionally, the main board portion has mounting holes, and the bottom edge portion has fastening holes. The mounting holes and fastening holes correspond one-to-one, and fasteners are provided for the corresponding mounting holes and fastening holes.

[0015] Optionally, the bottom edge protrudes a predetermined distance toward the side of the belly edge away from the wall panel.

[0016] Optionally, the bottom edge, the ventral edge, and the flange are all plate-shaped.

[0017] Optionally, the end of the bottom edge away from the main board is flush with the side of the wall panel away from the aircraft door frame.

[0018] An aircraft, including the aforementioned aircraft door frame sealing member.

[0019] The beneficial effects of this utility model are:

[0020] This utility model proposes an aircraft door frame sealing baffle, which is installed on an aircraft door frame. The aircraft door frame includes a main board portion and two side plates connected to both sides of the main board portion. One side plate portion is fitted to the wall panel. The aircraft door frame sealing baffle includes a bottom edge portion, a belly edge portion, and a flange portion. One end of the belly edge portion is connected to the bottom edge portion, and the other end is connected to the flange portion. The bottom edge portion is fitted to the main board portion. The flange portion is located on the side of the belly edge portion near the wall panel, and the flange portion can abut against the seal on the aircraft door. The bottom edge portion, belly edge portion, and flange portion can form a drainage groove. The side plates portion, wall panel, and bottom edge portion can form a filling gap, which is used to fill the sealant. By incorporating a door frame sealing element, which includes a bottom edge, a belly edge, and a flange, the aircraft door frame sealing element forms a drainage channel. When the flange abuts against the seal on the aircraft door, the flange and the seal are in close contact to achieve a seal on the pressurized cabin door. In rainy weather, external rainwater can seep into the semi-enclosed space formed by the door frame sealing element and the seal through the gap between the door and the fuselage. By incorporating the drainage channel, the rainwater between the door frame sealing element and the seal can flow out in a timely manner, thus preventing rainwater from seeping into the fuselage. In addition, by incorporating a filling gap formed by the side panel, wall panel, and bottom edge, the filling gap is filled with sealant, thereby protecting the edge of the wall panel with the sealant. No additional components are required; the protection of the wall panel edge can be achieved through the inherent structure of the aircraft and the door frame sealing element, reducing the weight of the fuselage.

[0021] This invention proposes an aircraft with a door frame sealing baffle. The door frame sealing baffle includes a bottom edge, a belly edge, and a flange. The bottom edge, belly edge, and flange can form a drainage groove. When the flange abuts against the seal on the aircraft door, the flange and the seal are in close contact to achieve a seal on the pressurized cabin door. In rainy weather, external rainwater can seep into the semi-enclosed space formed by the door frame sealing baffle and the seal through the gap between the door and the fuselage. By setting the drainage groove, the rainwater between the door frame sealing baffle and the seal can flow out in time, thereby preventing rainwater from seeping into the fuselage. In addition, a filling gap is formed by the side panel, wall panel, and bottom edge. The filling gap is used to fill the sealant, thereby protecting the edge of the wall panel with the sealant. No additional components are required. The protection of the wall panel edge can be achieved by the inherent structure of the aircraft and the door frame sealing baffle, reducing the weight of the fuselage. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of an aircraft door frame sealing baffle that cooperates with the aircraft door frame and wall panel according to an embodiment of the present utility model;

[0023] Figure 2This is a structural schematic diagram from another perspective of the cooperation between an aircraft door frame sealing baffle and an aircraft door frame and wall panel provided in an embodiment of this utility model;

[0024] Figure 3 yes Figure 2 Sectional view at point AA;

[0025] Figure 4 yes Figure 2 Sectional view at point BB;

[0026] Figure 5 yes Figure 2 Sectional view at CC;

[0027] Figure 6 yes Figure 2 Sectional view at point DD.

[0028] In the picture:

[0029] 100. Aircraft door frame; 101. Main board section; 102. Side panel section; 200. Wall panel;

[0030] 1. Bottom edge; 2. Abdominal edge; 3. Flange; 4. Extension; 41. First extension sub-section; 42. Second extension sub-section; 5. Filling gap; 6. Fastener; 7. Drainage groove. Detailed Implementation

[0031] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, not the entire structure.

[0032] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0033] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0034] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0035] This embodiment proposes an aircraft door frame sealing baffle and an aircraft to solve the problems in the prior art where rainwater cannot be discharged between the sealing baffles and the sealing elements on the aircraft door frame, and the edges of the wall panels are not effectively protected.

[0036] like Figures 1-3 As shown, an aircraft door frame sealing baffle is installed on an aircraft door frame 100. The aircraft door frame 100 includes a main board portion 101 and two side plate portions 102 connected to both sides of the main board portion 101. One side plate portion 102 is fitted to the wall panel 200. The aircraft door frame sealing baffle includes a bottom edge portion 1, a belly edge portion 2, and a flange portion 3. One end of the belly edge portion 2 is connected to the bottom edge portion 1, and the other end is connected to the flange portion 3. The bottom edge portion 1 is fitted to the main board portion 101. The flange portion 3 is located on the side of the belly edge portion 2 near the wall panel 200, and the flange portion 3 can abut against the seal on the aircraft door. The bottom edge portion 1, belly edge portion 2, and flange portion 3 can form a drainage groove 7. The side plate portion 102, wall panel 200, and bottom edge portion 1 can form a filling gap 5, which is used to fill sealant.

[0037] Understandably, by setting up an aircraft door frame sealing baffle, which includes a bottom edge 1, a belly edge 2, and a flange 3, the bottom edge 1, belly edge 2, and flange 3 can form a drainage groove 7. When the flange 3 abuts against the seal on the aircraft door, the flange 3 and the seal are in close contact to achieve a seal on the aircraft pressurized cabin door. In rainy weather, external rainwater will seep into the semi-enclosed space formed by the aircraft door frame sealing baffle and the seal through the gap between the door and the fuselage. By setting up a drainage groove 7, the drainage groove can be effectively sealed. The groove 7 allows rainwater between the aircraft door frame sealing baffle and the sealing element to flow out in a timely manner, thus preventing rainwater from seeping into the fuselage. In addition, a filling gap 5 is formed by the side panel 102, the wall panel 200 and the bottom edge 1. The filling gap 5 is used to fill the sealant, thereby protecting the edge of the wall panel 200 with the sealant. No additional parts are required. The protection of the edge of the wall panel 200 can be achieved by the inherent structure of the aircraft and the aircraft door frame sealing baffle, thus reducing the weight of the fuselage.

[0038] For example, the sealant is a liquid polysulfide rubber-based sealant, thereby improving the sealant's corrosion resistance and durability.

[0039] Of course, the type of sealant is not limited to this; it can be selected as needed according to the application scenario, without too many restrictions here.

[0040] like Figures 3-4 As shown, optionally, along the thickness direction of the panel 200, the length of the bottom edge 1 is greater than the length of the flange 3. This arrangement can improve the connection strength between the bottom edge 1 and the main panel 101, thereby improving the installation stability of the aircraft door frame sealing stop.

[0041] like Figure 5 As shown, optionally, the length of the abdominal edge 2 is greater than the length of the wall panel 200 along the thickness direction perpendicular to the wall panel 200. In areas where the size requirement of the drainage channel 7 is large, such as the upper side of the aircraft door frame 100, where rainwater accumulation is more serious and it is necessary to increase the intensity of rainwater drainage, the abdominal edge 2 can be made longer, thereby increasing the drainage speed of the drainage channel 7 and improving the structural rationality of the aircraft door frame sealing baffle.

[0042] like Figure 6 As shown, optionally, the aircraft door frame sealing baffle also includes an extension 4, which includes a first extension sub-part 41 and a second extension sub-part 42. One end of the first extension sub-part 41 is connected to the bottom edge part 1, and the other end is connected to one end of the second extension sub-part 42. The second extension sub-part 42 is fitted to the main board part 101, and the first extension sub-part 41 is fitted to the wall panel 200. The first extension sub-part 41, the wall panel 200, and the bottom edge part 1 can form a filling gap 5.

[0043] Understandably, when the aircraft door frame 100 is far from the wall panel 200, in order to ensure the installation stability of the aircraft door frame sealing baffle, an extension portion 4 is provided, with its first extension sub-part 41 and second extension sub-part 42 connected. The second extension sub-part 42 is fitted to the main board portion 101, and the first extension sub-part 41 is fitted to the wall panel 200. This greatly increases the contact area between the aircraft door frame sealing baffle and the aircraft door frame 100 and the wall panel 200, thereby significantly improving the installation stability of the aircraft door frame sealing baffle and preventing the reliability of the aircraft door frame sealing baffle from being compromised when the aircraft door frame 100 is far from the wall panel 200.

[0044] like Figures 3-6 As shown, optionally, the end of the flange portion 3 away from the ventral edge portion 2 is arc-shaped. This design not only improves the tightness of the contact between the flange portion 3 and the seal, but also facilitates the drainage of rainwater between the flange portion 3 and the seal, thus improving the structural rationality of the aircraft door frame sealing element.

[0045] Optionally, the connection between the flange 3 and the belly edge 2 is rounded. This design prevents rainwater from accumulating at the connection between the flange 3 and the belly edge 2. If the connection between the flange 3 and the belly edge 2 is at a right angle, the risk of rainwater accumulating at the right angle would increase.

[0046] Optionally, the connection between the abdominal edge 2 and the bottom edge 1 is rounded. This design allows rainwater to drain more easily from both ends of the abdominal edge 2, ensuring good water flow at both ends and comprehensively improving the drainage performance of the aircraft door frame sealing components.

[0047] Optionally, the main board portion 101 has mounting holes, and the bottom edge portion 1 has fastening holes. Multiple mounting holes and multiple fastening holes correspond one-to-one, and fasteners 6 are provided in the corresponding mounting holes and fastening holes. This arrangement enhances the connection strength between the bottom edge portion 1 and the main board portion 101, thereby improving the reliability of the aircraft door frame sealing element.

[0048] For example, fastener 6 is a bolt. Using bolts as fastener 6 is more reliable and less expensive, which helps to improve the economics of aircraft manufacturing.

[0049] like Figure 4 As shown, optionally, the bottom edge 1 protrudes a predetermined distance from the side of the belly edge 2 away from the wall panel 200. This arrangement can further increase the connection area between the bottom edge 1 and the main board 101, thereby significantly improving the connection strength between the bottom edge 1 and the main board 101 and enhancing the reliability of the aircraft door frame sealing stop.

[0050] It should be noted that the preset distance can be set as needed according to the length of the motherboard 101, as long as it does not interfere with other components, and no further restrictions are imposed here.

[0051] For example, the portion of the bottom edge 1 that protrudes beyond the belly edge 2 also has a fastening hole, and the main board portion 101 has a mounting hole corresponding to the fastening hole. Fasteners 6 are provided in the fastening hole and the mounting hole. This arrangement can further enhance the connection strength between the bottom edge 1 and the main board portion 101, thereby improving the installation stability of the aircraft door frame sealing baffle.

[0052] Optionally, the bottom edge 1, the belly edge 2, and the flange 3 are all plate-shaped. This design can reduce the weight of the aircraft door frame sealing element and maximize the contact area between the bottom edge 1 and the main board 101, thereby improving the installation stability of the aircraft door frame sealing element.

[0053] Optionally, the bottom edge 1 and the belly edge 2 are set at an angle, and the flange 3 and the belly edge 2 are also set at an angle. This arrangement allows the angle of the flange 3 and the shape of the drainage groove 7 to be set as needed according to the type of seal, thereby improving the adaptability and structural flexibility of the aircraft door frame sealing stop.

[0054] It is worth noting that the included angle between the bottom edge 1 and the abdominal edge 2, as well as the included angle between the flange 3 and the abdominal edge 2, are not specifically limited. They can be set as needed according to the actual application scenario and drainage requirements, and will not be elaborated on here.

[0055] Optionally, the end of the bottom edge 1 away from the main board 101 is flush with the side of the wall panel 200 away from the aircraft door frame 100. This arrangement makes the cross-section of the filling gap 5 rectangular, thereby preventing the filler from falling out. At the same time, this arrangement can prevent the end of the bottom edge 1 away from the main board 101 from scratching personnel or other parts, thus improving the structural rationality of the aircraft door frame sealing baffle.

[0056] This embodiment also proposes an aircraft to solve the problems in the prior art where rainwater cannot drain between the sealing baffle and the sealing element on the aircraft door frame 100, and the edges of the wall panel 200 are not effectively protected. The aircraft proposed in this embodiment, by setting an aircraft door frame sealing baffle, includes a bottom edge 1, a belly edge 2, and a flange 3. The bottom edge 1, belly edge 2, and flange 3 can form a drainage groove 7. When the flange 3 abuts against the sealing element on the aircraft door, the flange 3 and the sealing element are in close contact to achieve a seal on the aircraft pressurized cabin door. In rainy weather, external rainwater will seep into the semi-enclosed space formed by the aircraft door frame sealing baffle and the sealing element through the gap between the cabin door and the fuselage. By setting... The drainage channel 7 allows rainwater between the aircraft door frame sealing elements and the sealing elements to flow out in a timely manner, thus preventing rainwater from seeping into the fuselage. In addition, a filling gap 5 is formed by the side panel 102, the wall panel 200, and the bottom edge 1. The filling gap 5 is used to fill the sealant, thereby protecting the edge of the wall panel 200 with the sealant. No additional components are required. The protection of the edge of the wall panel 200 can be achieved by the inherent structure of the aircraft and the aircraft door frame sealing elements, thus reducing the weight of the fuselage.

[0057] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. An aircraft door frame sealing baffle, installed on an aircraft door frame (100), the aircraft door frame (100) comprising a main board portion (101) and two side plate portions (102) connected to both sides of the main board portion (101), one of the side plate portions (102) being fitted and installed onto a wall panel (200), characterized in that, The aircraft door frame sealing member includes a bottom edge (1), a belly edge (2) and a flange (3). One end of the belly edge (2) is connected to the bottom edge (1) and the other end is connected to the flange (3). The bottom edge (1) is fitted to the main board (101). The flange (3) is located on the side of the belly edge (2) near the wall panel (200) and can abut against the sealing member on the aircraft door. The bottom edge (1), the belly edge (2) and the flange (3) can form a drainage groove (7). The side panel (102), the wall panel (200) and the bottom edge (1) can form a filling gap (5). The filling gap (5) is used to fill the sealant.

2. The aircraft door frame sealing member according to claim 1, characterized in that, Along the thickness direction of the wall panel (200), the length of the bottom edge (1) is greater than the length of the flange (3).

3. The aircraft door frame sealing member according to claim 1, characterized in that, The aircraft door frame sealing member also includes an extension (4), the extension (4) includes a first extension sub-part (41) and a second extension sub-part (42), one end of the first extension sub-part (41) is connected to the bottom edge part (1), and the other end is connected to one end of the second extension sub-part (42), the second extension sub-part (42) is fitted and installed on the main board part (101), and the first extension sub-part (41) is fitted and installed on the wall panel (200), the first extension sub-part (41), the wall panel (200) and the bottom edge part (1) can surround and form the filling gap (5).

4. The aircraft door frame sealing member according to claim 1, characterized in that, The end of the flange (3) away from the ventral edge (2) is arc-shaped.

5. The aircraft door frame sealing member according to claim 1, characterized in that, The connection between the flange portion (3) and the ventral edge portion (2) is made of arc transition; And / or, the connection between the ventral edge (2) and the bottom edge (1) is made of a rounded transition.

6. The aircraft door frame sealing member according to claim 1, characterized in that, The main board (101) has mounting holes, and the bottom edge (1) has fastening holes. The mounting holes and the fastening holes correspond one-to-one, and fasteners (6) are provided for the corresponding mounting holes and fastening holes.

7. The aircraft door frame sealing member according to claim 1, characterized in that, The bottom edge (1) protrudes a predetermined distance toward the side of the belly edge (2) away from the wall panel (200).

8. The aircraft door frame sealing member according to any one of claims 1-7, characterized in that, The bottom edge (1), the ventral edge (2), and the flange (3) are all plate-shaped.

9. The aircraft door frame sealing member according to any one of claims 1-7, characterized in that, The bottom edge (1) is flush with the side of the wall panel (200) away from the main board (101) at one end.

10. An aircraft, characterized in that, Includes the aircraft door frame sealing element as described in any one of claims 1-9.

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