Airplane cabin door sealing tape performance test device and test method
By designing a test device for the performance of the sealing strip of an aircraft cabin door that can be rotated, the problem of the failure to consider the influence of movement in the existing technology was solved, and higher test accuracy and precision were achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-04
- Publication Date
- 2026-04-10
AI Technical Summary
Existing aircraft door sealing strip airtightness testing equipment fails to effectively consider the impact of movement on airtightness, resulting in poor test results.
An aircraft cabin door sealing performance testing device was designed, including a simulated cabin and a simulated cabin door. The simulated cabin door can be rotated to simulate the cabin door closing process and is equipped with an airtightness detection component to test the sealing performance by inflating the cabin with air.
It improves the accuracy and precision of aircraft door sealing strip performance testing, enabling a more realistic simulation of the sealing effect during the door closing process.
Smart Images
Figure CN121829922A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application belongs to the technical field of aviation sealing and particularly relates to a device and method for testing the performance of a sealing strip of an aircraft door. BACKGROUND
[0002] The sealing effect of an aircraft door system is guaranteed by a sealing strip. Once the sealing strip fails, it will cause an imbalance in the air pressure inside the aircraft and a lack of oxygen, directly endangering the safety of the passengers inside the aircraft. Therefore, the sealing strip must be fully verified before being installed. There are various forms of verification of the air-tightness of the sealing strip. Random verification can be performed, a single door can be verified, or a local part with typical characteristics can be verified.
[0003] During the early stage of product development, the air-tightness of a local area or a single door of the product is verified. Even if a leak occurs, there is still sufficient time for technical state changes of the product. Air-tightness tests are only performed on the entire machine during the later stage of product development. At this time, the technical state of the entire machine is determined, and if the product design is repeated, the change cycle will be very tight. Therefore, the air-tightness test focuses on verifying the sealing performance of a local area or a single door of the product. However, the existing air-tightness test device is mostly a static test device, and the influence of different actions (such as closing the door) on air-tightness is not considered, which leads to the problem of poor accuracy of the test results.
[0004] Therefore, in view of the above problems, the present application is provided. SUMMARY
[0005] The present application aims to at least partially solve the above technical problems by providing a device and method for testing the performance of a sealing strip of an aircraft door.
[0006] The first aspect of the present application provides a device for testing the performance of a sealing strip of an aircraft door, comprising: a base; a simulated cabin body disposed on the base, wherein the upper surface of the simulated cabin body is provided with an opening, and the outer periphery of the opening is provided with a mounting groove for placing the sealing strip; a simulated door hinged to the base, wherein the simulated door can rotate relative to the base and can press the sealing strip and be fixed to the upper surface of the simulated cabin body when rotated in place; an air-tightness detection assembly disposed on the simulated cabin body and capable of simulating and verifying the sealing performance between the simulated cabin body and the simulated door by inflating the simulated cabin body.
[0007] The device for testing the performance of a sealing strip of an aircraft door provided by the present application can further have the following additional technical features: In some specific embodiments of the present application, the upper surface of the simulation cabin body is formed as an arc-shaped slope curved towards the hinged end of the simulation cabin door, and the height of the arc-shaped slope corresponding to the hinged end of the simulation cabin door is smaller than the height of the other end.
[0008] In some specific embodiments of the present application, the upper surface of the simulation cabin body is provided with a plurality of mounting holes with built-in eccentric shaft sleeves, and the simulation cabin door is provided with screws which are adaptively connected with the eccentric shaft sleeves to fix the simulation cabin door to the simulation cabin body.
[0009] In some specific embodiments of the present application, a bearing seat and an adapter are further included, the bearing seat is arranged in pairs on the base, one end of the adapter is mounted on the bearing seat through a rotating shaft, and the other end of the adapter is fixedly connected with the simulation cabin door.
[0010] In some specific embodiments of the present application, a strip-shaped support part is further included, the support part is two, and the two support parts are arranged in parallel to the base, the support part is provided with a plug column, and the plug column is inserted into a plug hole of the simulation cabin body to support the simulation cabin body.
[0011] In some specific embodiments of the present application, the base is provided with a through hole, the support part is provided with a bolt, the support part is adaptively mounted on the base through the bolt and the through hole, and the hole diameter of the through hole is greater than the screw rod diameter of the bolt, so that the support part can move and be positioned relative to the through hole on the plane of the base.
[0012] In some specific embodiments of the present application, the base is provided with an adjusting part corresponding to the support part, and the adjusting part is used to adjust the position of the support part and the simulation cabin body.
[0013] In some specific embodiments of the present application, the end of each support part has two adjusting parts corresponding thereto, and the two adjusting parts are configured to be able to drive the support part to adjust the position in two different directions.
[0014] In some specific embodiments of the present application, the simulation cabin body is provided with a first port and a second port, the air tightness detection assembly includes a gas supply unit and a pressure detection unit, the gas supply unit is connected with the first port and is used to provide a gas source into the simulation cabin body, and the pressure detection unit is connected with the second port and is used to detect the air pressure change in the simulation cabin body to simulate and verify the sealing performance between the simulation cabin body and the simulation cabin door.
[0015] The second aspect of the present application further provides a method for testing the aircraft cabin door sealing strip performance test device, including: S1: placing the sealing band in the installation groove, rotating the simulation cabin door and fixing it on the upper surface of the simulation cabin body to compress the sealing band; S2: pressurizing the simulation cabin body through the air supply device, and judging the pressure in the simulation cabin body through the pressure detection unit, so as to judge the sealing performance between the simulation cabin body and the simulation cabin door; S3: adjusting the position of the simulation cabin body multiple times, and repeating the above S1-S2 steps.
[0016] The simulation cabin body and the simulation cabin door capable of clamping the sealing band are arranged, and the simulation cabin door has rotating capability, so that the closing process of the simulation cabin door and the simulation cabin body can be considered during the aircraft cabin door sealing band performance test, thereby further improving the accuracy and precision of the aircraft cabin door sealing band performance test. BRIEF DESCRIPTION OF DRAWINGS
[0017] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed in the specific embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.
[0018] Figure 1 The structure schematic diagram of the aircraft cabin door sealing band performance test device in the embodiment of the present application; Figure 2 The structure exploded view of Figure 1 .
[0019] Explanation of reference signs: 100-test device; 10-base, 20-simulation cabin body, 30-simulation cabin door, 40-supporting part, 50-adjusting part, 61-bearing seat, 62-adapter, 70-sealing band, 80-eccentric shaft sleeve. DETAILED DESCRIPTION
[0020] Exemplary embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided so that the present application can be more thoroughly understood and the scope of the present application can be fully conveyed to those skilled in the art.
[0021] It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises", "comprising", "includes", "including" and "has" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and / or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and / or groups thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring their performance in the particular order in which they are described unless specifically identified as an order dependent step. It is also to be understood that additional or alternative steps can be employed.
[0022] Although the terms first, second, third, etc. can be used herein to describe various elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first", "second", and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
[0023] Spatially relative terms, such as "inner", "outer", "inward", "outward", "lower", "bottom", "top", "upper", and the like, can be used herein for ease of description to describe one element or feature's relationship to another element(s) or feature(s) as illustrated in the figures. Such spatially relative terms can encompass different orientations of the device in use or operation, depending on the particular context in which it is used. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "over" the other elements or features. Thus, the exemplary term "below" can encompass both an orientation of above and below. The device can be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
[0024] Referring to Figures 1-2The first aspect of the present application provides a device 100 for testing the performance of an aircraft door sealing strip 70, which comprises a base 10, a simulated cabin body 20, a simulated cabin door 30 and a gas tightness detection assembly. The simulated cabin body 20 is arranged on the base 10, and the upper surface of the simulated cabin body 20 is provided with an opening. The outer periphery of the opening is provided with a mounting groove for placing the sealing strip 70. The simulated cabin door 30 is hinged to the base 10. The simulated cabin door 30 can rotate relative to the base 10 and can press the sealing strip 70 and be fixed to the upper surface of the simulated cabin body 20 when rotated in place. The gas tightness detection assembly is arranged in the simulated cabin body 20 and can simulate and verify the sealing performance between the simulated cabin body 20 and the simulated cabin door 30 by inflating the simulated cabin body 20.
[0025] Specifically, the simulated cabin body 20 comprises a cabin wall that encloses an internal space isolated from the external environment. The cabin body is provided with an opening on the cabin wall at the top, and a mounting groove for placing the sealing strip 70 is formed around the opening. The depth of the mounting groove is less than the thickness of the sealing strip 70, so that when the sealing strip 70 is arranged in the mounting groove, the upper surface of the sealing strip 70 protrudes from the upper surface of the simulated cabin body 20. Except for the area where the opening is located, the remaining part of the cabin wall (i.e. the complete continuous surface) ensures its air tightness through the continuity of its own material and manufacturing process (e.g. integral casting, seamless welding, one-time injection molding of polymer materials, etc.), thereby forming a completely sealed cabin structure except for the specified opening.
[0026] The simulated cabin door 30 is flexibly adapted to the upper surface of the simulated cabin body 20, and is hinged to the base 10 and can be adapted and fixedly connected to the upper surface of the simulated cabin body 20 by rotating. Ideally, the simulated cabin door 30 can clamp the sealing strip 70 between the simulated cabin body 20 and the simulated cabin door 30.
[0027] The gas tightness detection assembly is arranged in the simulated cabin body 20. The gas tightness detection assembly can not only inflate the simulated cabin body 20, but also obtain the change of air pressure in the simulated cabin body 20 to verify the sealing performance between the simulated cabin body 20 and the simulated cabin door 30.
[0028] The embodiments of the present application set the simulated cabin body 20 and the simulated cabin door 30 that can adapt to clamp the sealing strip 70, and make the simulated cabin door 30 have the rotating ability. Thus, the closing process of the simulated cabin door 30 and the simulated cabin body 20 can be considered when testing the performance of the aircraft door sealing strip 70, thereby further improving the accuracy and precision of the performance test of the aircraft door sealing strip 70.
[0029] In some embodiments, the upper surface of the simulated cabin body 20 is formed as an arc-shaped inclined surface that curves towards the hinged end of the simulated cabin door 30, and the height of the arc-shaped inclined surface corresponding to the hinged end of the simulated cabin door 30 is less than the height of the other end.
[0030] The embodiment realizes the profiling of the real structure by adjusting the shapes of the simulation cabin body 20 and the simulation cabin door 30, thereby further improving the accuracy and precision of the performance test of the aircraft cabin door sealing band 70.
[0031] In some embodiments, the upper surface of the simulation cabin body 20 is provided with a plurality of mounting holes in which eccentric shaft sleeves 80 are arranged, and the simulation cabin door 30 is provided with screws which are adaptively connected with the eccentric shaft sleeves 80 to fix the simulation cabin door 30 to the simulation cabin body 20.
[0032] By setting the screws and the eccentric shaft sleeves 80 adaptively connected with the screws, and by realizing the fixed connection of the simulation cabin door 30 and the simulation cabin body 20 through the screws and the eccentric shaft sleeves 80, the influence of the step difference of the closed simulation cabin door 30 can be considered in the test, thereby further improving the accuracy of the performance test of the aircraft cabin door sealing band 70.
[0033] In some embodiments, the base 10 is further provided with a bearing seat 61 and an adapter 62. The bearing seat 61 is arranged in pairs on the base 10, one end of the adapter 62 is installed on the bearing seat 61 through a rotating shaft, and the other end of the adapter 62 is fixedly connected with the simulation cabin door 30.
[0034] Specifically, the bearing seat 61 is fixed to the base 10 through threaded fasteners, the adapter 62 includes a first connecting part and a second connecting part arranged in an L shape, the first connecting part is connected to the bearing seat 61 through a rotating shaft and can rotate relative to the bearing seat 61, and the second connecting part is connected to the upper surface of the simulation cabin door 30.
[0035] The embodiment further improves the profiling effect of the simulation cabin door 30 by setting the bearing seat 61 and the adapter 62, thereby further improving the accuracy of the performance test of the aircraft cabin door sealing band 70.
[0036] In some embodiments, the base 10 is further provided with two strip-shaped support parts 40 which are arranged in parallel on the base 10. The support parts 40 are provided with insertion columns which are inserted into insertion holes of the simulation cabin body 20 to support the simulation cabin body 20.
[0037] In some embodiments, the base 10 is provided with through holes, the support parts 40 are provided with bolts, and the support parts 40 are adaptively installed on the base 10 through the bolts and the through holes. The diameter of the through holes is greater than the diameter of the screw rods of the bolts, so that the support parts 40 can be moved and positioned relative to the through holes on the plane of the base 10.
[0038] The structure described above enables the support part 40 to move relative to the base 10 and still achieve the fastening effect with the base 10. Since the support part 40 has the relative movement capability on the base 10, the simulation cabin body 20 provided thereon also has the relative movement capability, that is, the simulation cabin body 20 and the simulation cabin door 30 have the relative movement capability, thereby enabling the air-tightness simulation of the simulation cabin body 20 and the simulation cabin door 30 in different positions, and further improving the accuracy of the performance test of the aircraft cabin door sealing strip 70.
[0039] In some embodiments, the base 10 is provided with adjusting parts 50 corresponding to the support parts 40, and the adjusting parts 50 are used to adjust the positions of the support parts 40 and the simulation cabin body 20. The end of each support part 40 is provided with two adjusting parts 50 corresponding thereto, and the two adjusting parts 50 are configured to drive the support part 40 to adjust the position in two different directions.
[0040] Specifically, the adjusting part 50 includes an adjusting seat fixed to the base 10 and an adjusting bolt screwed into the penetrating threaded hole of the adjusting seat and capable of adjusting the extension length by rotating.
[0041] The adjusting part 50 is 8, and each two of the 8 adjusting parts 50 are provided at one end of the corresponding support part 40. In the two adjusting parts 50 corresponding to the same end of the support part 40, the axial directions of the adjusting bolts are arranged perpendicularly. Thus, the 8 adjusting parts 50 cooperate with each other to achieve the adjustment of the position of the support part 40.
[0042] In some embodiments, the simulation cabin body 20 is provided with a first port and a second port, and the air-tightness detection assembly includes a gas supply unit and a pressure detection unit. The gas supply unit is connected with the first port and used to provide the air source in the simulation cabin body 20. The pressure detection unit is connected with the second port and used to detect the air pressure change in the simulation cabin body 20 to simulate and verify the sealing performance between the simulation cabin body 20 and the simulation cabin door 30.
[0043] The gas supply unit can be a gas cylinder or the like, and the gas outlet thereof is connected with the first port of the simulation cabin body 20 through a flow meter and used to inflate the simulation cabin body 20. The pressure detection unit can be a pressure gauge. Specifically, when the air pressure in the simulation cabin body 20 reaches a preset value, the pressure is maintained for a period of time, and the air pressure change before and after the pressure maintenance is compared. Wherein, the initial air pressure is set as p, the simulation cabin body 20 is inflated to the test pressure p1, at this time, the flow meter outputs the gas flow V, and after maintaining the pressure for a period of time t, the air pressure decreases to p2 due to the existence of a certain air leakage, and the air pressure leakage rate in this period of time is (p1-p2) / (p1-p).
[0044] The second aspect of the present application also provides a method for testing the performance test device 100 of the aircraft cabin door sealing strip 70, which includes: S1: placing the sealing band 70 in the installation groove, rotating the simulation cabin door 30 and fixing it on the upper surface of the simulation cabin body 20 to compress the sealing band 70; S2: pressurizing the simulation cabin body 20 through the air supply device, and judging the pressure in the simulation cabin body 20 through the pressure detection unit, so as to judge the sealing performance between the simulation cabin body 20 and the simulation cabin door 30; S3: adjusting the position of the simulation cabin body 20 for multiple times, and repeating the above S1-S2 steps.
[0045] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.
Claims
1. A device for testing the performance of an aircraft cabin door sealing strip, characterized in that, include: Base; A simulation chamber is disposed on the base, and the upper surface of the simulation chamber is provided with an opening, and the outer periphery of the opening is provided with an installation groove for placing a sealing strip; The simulated hatch is hinged to the base, and the simulated hatch can rotate relative to the base. When rotated into position, it can press the sealing strip and fix it to the upper surface of the simulated hatch. An airtightness testing component is installed in the simulated chamber and can simulate and verify the sealing performance between the simulated chamber and the simulated door by inflating the simulated chamber with air.
2. The aircraft door sealing strip performance testing device according to claim 1, characterized in that, The upper surface of the simulated cabin is formed as an arc-shaped inclined surface that curves toward the hinge end of the simulated cabin door, and the height of the arc-shaped inclined surface at the hinge end of the simulated cabin door is less than the height of the other end.
3. The aircraft cabin door sealing strip performance testing device according to claim 1, characterized in that, The upper surface of the simulation chamber is provided with a plurality of mounting holes for internal eccentric bushings. The simulation chamber door is provided with screws, which are adapted to the eccentric bushings to fix the simulation chamber door to the simulation chamber.
4. The aircraft door sealing strip performance testing device according to claim 1, characterized in that, It also includes a bearing housing and a connecting part. The bearing housings are arranged in pairs on the base. One end of the connecting part is mounted on the bearing housing via a rotating shaft, and the other end of the connecting part is fixedly connected to the simulated hatch.
5. The aircraft door sealing strip performance testing device according to claim 1, characterized in that, It also includes two strip-shaped support parts, which are arranged parallel to the base. Each support part is provided with a post, which is inserted into the insertion hole of the simulation cabin to support the simulation cabin.
6. The aircraft door sealing strip performance testing device according to claim 5, characterized in that, The base has a through hole, and the support part has a bolt. The support part is fitted to the base through the bolt and the through hole, and the diameter of the through hole is larger than the diameter of the bolt, so that the support part can move and be positioned relative to the through hole on the plane of the base.
7. The aircraft door sealing strip performance testing device according to claim 6, characterized in that, The base is provided with an adjustment part corresponding to the support part, and the adjustment part is used to adjust the position of the support part and the simulated cabin.
8. The aircraft door sealing strip performance testing device according to claim 7, characterized in that, Each support has two corresponding adjustment parts at its end, and the two adjustment parts are configured to drive the support to adjust its position in two different directions.
9. The aircraft door sealing strip performance testing device according to claim 1, characterized in that, The simulated chamber is provided with a first port and a second port. The airtightness detection component includes an air supply unit and a pressure detection unit. The air supply unit is connected to the first port and is used to provide an air source to the simulated chamber. The pressure detection unit is connected to the second port and is used to detect the air pressure change in the simulated chamber to simulate and verify the sealing performance between the simulated chamber and the simulated door.
10. A method for testing the performance of an aircraft door sealing strip using the testing apparatus described in any one of claims 1-9, characterized in that, include: S1: Place the sealing strip in the mounting groove, rotate the simulation hatch door and fix it to the upper surface of the simulation hatch to press the sealing strip tight; S2: Pressurize the simulated chamber through the air supply device, and determine the pressure inside the simulated chamber through the pressure detection unit, thereby determining the sealing performance between the simulated chamber and the simulated door; S3: Adjust the position of the simulated cabin multiple times and repeat steps S1-S2 above.