Testing device for sealing structure between cabin door and cabin door frame of airplane

Abstract

The utility model belongs to the technical field of test design of a sealing structure between an aircraft cabin door and a cabin door frame, and particularly relates to a device for testing the sealing structure between the aircraft cabin door and the cabin door frame, and the device comprises an annular frame which is provided with a pressurizing port, one end of the annular frame is a test maintenance end, and the other end is an airtight test end; the test maintenance door is arranged at the test maintenance end; the cabin door frame simulation plate is connected to the airtight test end; the cabin door simulation plate is connected to the airtight test end; and the plurality of step difference adjusting base plates can be connected to the cabin door simulation plate through bolts to cover the edge of the cabin door frame simulation plate, and an airtight test seam is formed between the step difference adjusting base plates and the edge of the cabin door frame simulation plate.

Description

Technical Field

[0001] The present application belongs to the technical field of test design of sealing structures between aircraft cabin doors and cabin door frames, and specifically relates to a test device for sealing structures between aircraft cabin doors and cabin door frames. Background Art

[0002] For aircraft, especially transport aircraft, cabin airtightness is an extremely important technical indicator. The gap between the cabin door and the door frame is sealed with a sealing structure, which is a key part of the aircraft cabin airtightness design.

[0003] Under the action of aerodynamic load and pressurization load, aircraft doors, especially pressurized doors, are prone to deformation, which will cause relative deformation step difference between them and the door frame, seriously affecting the sealing performance of the sealing structure. Experimental research on the sealing performance of the sealing structure has important guiding significance for the improvement of the sealing structure.

[0004] Currently, the sealing performance of the sealing structure between the aircraft cabin door and the door frame is mostly tested and studied after installation during the aircraft pressurization test. The test cost is high and the cycle is long. It is also impossible to effectively study the impact of various relative deformation steps between the aircraft cabin door and the door frame on the sealing performance of the sealing structure. It is difficult to meet the needs of rapid technology iteration at the beginning of the sealing structure design.

[0005] This application is proposed in view of the above-mentioned technical defects. Utility Model Content

[0006] The purpose of the present application is to provide a sealing structure testing device between an aircraft door and a door frame, so as to overcome or alleviate at least one of the existing technical defects.

[0007] The technical solution of this application is:

[0008] A device for testing the sealing structure between an aircraft door and a door frame, comprising:

[0009] A ring frame with a pressure charging port, one end of which is a test maintenance end and the other end is an airtight test end;

[0010] Test maintenance door, set at the test maintenance end;

[0011] Door frame simulation board, connected to the airtight test end;

[0012] Hatch door simulation board, connected to the airtight test end;

[0013] Multiple step adjustment pads can be connected to the door simulation plate by bolts, covering the edge of the door frame simulation plate and forming an airtight test seam between the edge of the door frame simulation plate.

[0014] Optionally, in the above-mentioned test device for the sealing structure between an aircraft door and a door frame, each step adjustment pad has a different thickness.

[0015] Optionally, in the above-mentioned test device for the sealing structure between an aircraft door and a door frame, the bolt holes on the step adjustment pad are strip-shaped holes, and the strip-shaped holes are along the transverse direction of the airtight test seam.

[0016] Optionally, in the above-mentioned test device for the sealing structure between an aircraft door and a door frame, the annular frame is composed of an upper wall panel, a lower wall panel, a left wall panel, and a right wall panel that are interconnected.

[0017] Optionally, the above-mentioned test device for the sealing structure between an aircraft door and a door frame further includes:

[0018] A support plate connected to the test maintenance end and having a test maintenance port;

[0019] The test maintenance door is arranged in the test maintenance opening.

[0020] This application has at least the following beneficial technical effects:

[0021] Provided is a test device for the sealing structure between an aircraft cabin door and a door frame. The device can be used to test and study the sealing structure at the beginning of the design of the sealing structure between the aircraft cabin door and the door frame. By selecting different step-adjustment pads or a combination of different step-adjustment pads, the width of the airtight test seam can be adjusted to simulate the gap width caused by various relative deformation steps between the aircraft cabin door and the door frame. This allows for test and study of the sealing performance of the sealing structure in an efficient and convenient manner. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 1 is a schematic diagram of the appearance of a sealing structure test device between an aircraft door and a door frame provided in an embodiment of the present application at one angle;

[0023] Figure 2 2 is a schematic diagram of the appearance of the sealing structure test device between an aircraft door and a door frame provided in an embodiment of the present application from another angle;

[0024] Figure 3 This is a partial schematic diagram of a test device for the sealing structure between an aircraft door and a door frame provided in an embodiment of the present application;

[0025] in:

[0026] 1- Ring frame; 2- Test maintenance door; 3- Door frame simulation board; 4- Door simulation board; 5- Step adjustment pad; 6- Support plate.

[0027] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0028] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0029] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0030] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0031] A test device for the sealing structure between an aircraft door and a door frame, such as Figure 1-3 Shown, including:

[0032] The ring frame 1 is provided with a pressure charging port, one end of which is a test maintenance end and the other end is an airtight test end;

[0033] The support plate 6 is connected to the test maintenance end, specifically by bolt connection, and has a test maintenance port;

[0034] A test maintenance door 2 is provided in the test maintenance opening;

[0035] The door frame simulation plate 3 is connected to the airtight test end, specifically by bolt connection;

[0036] The door simulation board 4 is connected to the airtight test end, specifically by bolt connection;

[0037] A plurality of step adjustment pads 5 can be connected to the door simulation plate 4 by bolts, covering the edge of the door frame simulation plate 3 and forming an airtight test seam between the edge of the door frame simulation plate 3.

[0038] The step-adjusting pads 5 have different thicknesses.

[0039] When designing the sealing structure between an aircraft door and a door frame, the sealing structure can be tested and studied using the test device for the sealing structure between an aircraft door and a door frame disclosed in the above embodiment. Specific references are as follows:

[0040] Select different step adjustment pads 5 or a combination of different step adjustment pads 5 and bolt them to the door frame simulation plate 3 so that the width of the airtight test seam matches the gap width caused by the relative deformation step between the door and the door frame;

[0041] A sealing structure is provided in the airtight test seam;

[0042] Close the test maintenance door 2, and fill the sealing structure formed in the annular frame 1 with gas through the pressure charging port to generate the required pressure, and conduct a test study on the sealing performance of the sealing structure.

[0043] The sealing structure test device between the aircraft cabin door and the cabin door frame disclosed in the above embodiment can adjust the width of the airtight test seam by selecting different step adjustment pads 5 or a combination of different step adjustment pads 5, simulate the gap width caused by various different relative deformation steps between the aircraft cabin door and the cabin door frame, and conduct experimental research on the sealing performance of the sealing structure. It is efficient and convenient, and can meet the needs of rapid technical iteration at the beginning of the sealing structure design.

[0044] The bolt holes on the step adjustment plate 5 can be designed as strip holes, which are along the transverse direction of the airtight test seam. When the bolts are loosened, the step adjustment plate 5 can be slid to adjust the coverage width of the step adjustment plate 5 on the edge of the door frame simulation plate 3, thereby simulating the actual overlapping width between the edge of the door and the edge of the door frame, thereby ensuring the accuracy of the experimental research on the sealing performance of the sealing structure.

[0045] The annular frame 1 is composed of an upper wall plate, a lower wall plate, a left wall plate, and a right wall plate which are connected to each other.

[0046] The upper wall plate, the lower wall plate, the left wall plate, the right wall plate and the outer side of the support plate 6 of the annular frame 1 are provided with crisscross reinforcing ribs.

[0047] The door frame simulation plate 3, the door simulation plate 4 and the step adjustment pad 5 can be designed to be arc-shaped so that the direction of the airtight test seam is consistent with the actual direction of the gap between the door and the door frame.

[0048] The inner sides of the hatch frame simulation plate 3 and the hatch door simulation plate 4 are provided with longitudinal and transverse staggered reinforcing ribs.

[0049] The outer sides of the door frame simulation plate 3 and the door simulation plate 4 are provided with integrated transverse reinforcing ribs.

[0050] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A test device for the sealing structure between an aircraft door and a door frame, characterized in that: include: An annular frame (1) is provided with a pressure charging port, one end of which is a test maintenance end and the other end is an airtight test end; A test maintenance door (2), provided at the test maintenance end; The door frame simulation plate (3) is connected to the airtight test end; A door simulation board (4) connected to the airtight test end; A plurality of step adjustment pads (5) can be connected to the door simulation plate (4) by bolts, covering the edge of the door frame simulation plate (3) and forming an airtight test seam between the edge of the door frame simulation plate (3).

2. The sealing structure testing device between an aircraft door and a door frame according to claim 1, characterized in that: Each step-adjusting pad (5) has a different thickness.

3. The sealing structure testing device between an aircraft door and a door frame according to claim 1, characterized in that: The bolt holes on the step adjustment pad (5) are strip holes, and the strip holes are along the transverse direction of the airtight test seam.

4. The sealing structure testing device between a cabin door and a door frame according to claim 1, characterized in that: The annular frame (1) is composed of an upper wall plate, a lower wall plate, a left wall plate, and a right wall plate which are connected to each other.

5. The sealing structure testing device between an aircraft door and a door frame according to claim 1, characterized in that: Also includes: A support plate (6) is connected to the test maintenance end and has a test maintenance port; The test maintenance door (2) is arranged in the test maintenance opening.

Images