Aviation elbow sealing test device and method

Abstract

The invention discloses an aviation elbow sealing test device and method. One side of the base (1) is hinged to the bent portion of the bent connecting rod (2), the pressing assembly (3) is arranged at the vertical rod end of the bent connecting rod (2), and the transverse rod end of the bent connecting rod (2) is hinged to the bottom end of the connecting plate (4). A vertical plate (5) is arranged on one side, close to the connecting plate (4), of the base (1); the top end of the connecting plate (4) is hinged to one end of a rotating plate (6), and the other end of the rotating plate (6) is hinged to a vertical plate (5). A sealing assembly A (7) capable of translating along the normal direction of the vertical plate (5) is arranged on the vertical plate (5); the base (1) is further provided with a sealing assembly B (17), and the sealing assembly B (17) is communicated with the air tap (8). The connecting plate (4) is further in threaded connection with an ejector rod (9), and the head end of the ejector rod (9) abuts against the sealing assembly A (7). The sealing structure has the characteristics of high mounting efficiency, reliable sealing and convenience in disassembly.

Description

Technical Field

[0001] This invention belongs to the field of airtightness testing technology for aerospace parts, specifically relating to an aerospace bend sealing test device and method. Background Technology

[0002] Mechanical and aerospace system structural components include many cast parts. Due to the casting process, these parts need to undergo airtightness testing to check for casting defects. Since these parts are 90-degree bent pipe parts, space avoidance issues must be considered when designing airtightness testing fixtures.

[0003] According to traditional design methods, a clamping device needs to be installed at the back bend of the part. Due to the spatial requirements of the part, the clamping device needs to be set high and far away to ensure the installation requirements of the part. This will result in longer installation time and inconvenient clamping. Summary of the Invention

[0004] The purpose of this invention is to provide a device and method for testing the sealing performance of aerospace bends. This invention features high installation efficiency, reliable sealing, and convenient disassembly.

[0005] The technical solution of this invention is: an aviation bend pipe sealing test device, comprising a base, one side of which is hinged to the bend of a bending connecting rod, the vertical end of the bending connecting rod being provided with a clamping component, and the horizontal end of the bending connecting rod being hinged to the bottom end of a connecting plate; a vertical plate is provided on the side of the base near the connecting plate; the top end of the connecting plate is hinged to one end of a rotating plate, and the other end of the rotating plate is hinged to the vertical plate; a sealing component A that can translate along the normal direction of the vertical plate is provided on the vertical plate; the base is also provided with a sealing component B, which is connected to an air nozzle; a push rod is also threadedly connected to the connecting plate, and the head end of the push rod abuts against the sealing component A.

[0006] In the aforementioned aviation bend sealing test device, the clamping assembly includes an adjusting rod, which is threadedly connected to the vertical end of the bending connecting rod, and the head end of the adjusting rod is provided with a pressure cap.

[0007] In the aforementioned aviation bend sealing test device, the rotating plate is provided with a handle at the position where it is hinged to the vertical plate.

[0008] In the aforementioned aviation bend sealing test device, an elastic component is provided between the sealing component A and the vertical plate; a limiting plate for limiting the sealing component A is provided on the vertical plate.

[0009] In the aforementioned aviation bend sealing test device, the connecting plate is provided with a locking groove, and a T-shaped locking rod is provided in the locking groove. The end of the T-shaped locking rod is threadedly connected to the vertical plate. In the locked state, the locking head of the T-shaped locking rod is perpendicular to the locking groove. In the released state, the locking head of the T-shaped locking rod is parallel to the locking groove.

[0010] The aforementioned test method for the air-bend tube sealing test device involves sealing one end of the test bend tube with sealing component A and the other end with sealing component B; turning the rotating plate drives the connecting plate to make the top rod head abut against sealing component A, while the connecting plate drives the bending connecting rod to move so that the clamping component presses against the outside of the bend of the test bend tube; after clamping is completed, air is injected into the test bend tube through the air nozzle via sealing component B to conduct a sealing test.

[0011] In the aforementioned test method for the air-bend pipe sealing test device, after clamping is completed, a T-shaped locking rod is used to lock the vertical plate and the connecting plate.

[0012] In the aforementioned test method of the aviation bend sealing test device, after the test is completed, the T-shaped locking rod is rotated to be parallel to the locking groove, and then the rotating plate is moved to make the top rod disengage from the sealing component A. The sealing component A is withdrawn from the end of the bend under test until it is limited and abutted by the limiting plate. At the same time, the pressing component is also disengaged from the bend under test, and the bend under test can be taken out at this time.

[0013] The advantages of this invention are: In this invention, when the device needs to be released, the T-shaped locking rod is turned so that the locking head of the T-shaped locking rod is parallel to the locking groove provided on the connecting plate. Then, the handle is turned so that the rotating plate rotates at a certain angle, the connecting plate moves, and drives the bending connecting rod and the top rod away from the tested bend tube. The sealing component A also disengages from the tested bend tube under the action of the elastic component. Simultaneously, the pressing component also moves away from the tested bend tube under the action of the bending connecting rod, making the product easy to disassemble.

[0014] When the product needs to be pressed, the present invention can achieve rapid pressing by simply turning the handle, which enables the rotating plate, connecting plate, bending connecting rod and top rod to work together quickly.

[0015] When the product is in a compressed state, the present invention can lock the tooling state of the device by turning the T-shaped locking rod 90 degrees.

[0016] The present invention allows for fine-tuning of the pressure state of the tested pump by turning the adjusting rod.

[0017] When adjusting the tightening screw, the present invention can achieve fine adjustment of the clamping force of the pressure cap on the tested bent tube.

[0018] The present invention has a compact structure and high clamping efficiency. Traditional clamping takes 10 minutes to complete, while the present invention only takes 2 minutes. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of the present invention;

[0020] Figure 2 This is a schematic diagram of the disassembly of the present invention;

[0021] Figure 3 for Figure 1 Right view. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0024] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0025] Example 1. An aircraft bend sealing test device, see [link to example]. Figure 1-3 The system includes a base 1, one side of which is hinged to the bent portion of a bending connecting rod 2. The vertical end of the bending connecting rod 2 is provided with a clamping component 3, and the horizontal end of the bending connecting rod 2 is hinged to the bottom end of a connecting plate 4. A vertical plate 5 is provided on the side of the base 1 near the connecting plate 4. The top end of the connecting plate 4 is hinged to one end of a rotating plate 6, and the other end of the rotating plate 6 is hinged to the vertical plate 5. A sealing component A7 that can translate along the normal direction of the vertical plate 5 is provided on the vertical plate 5. The base 1 is also provided with a sealing component B17, which is connected to an air nozzle 8. A push rod 9 is also threadedly connected to the connecting plate 4, and the head end of the push rod 9 abuts against the sealing component A7.

[0026] The aforementioned clamping assembly 3 includes an adjusting rod 3.1, which is threadedly connected to the vertical end of the bent connecting rod 2, and the head end of the adjusting rod 3.1 is provided with a pressure cap 3.2.

[0027] The aforementioned rotating plate 6 is provided with a handle 10 at the position where it is hinged to the vertical plate 5.

[0028] An elastic component 11 is provided between the aforementioned sealing component A7 and the vertical plate 5; a limiting plate 12 for limiting the sealing component A7 is provided on the vertical plate 5.

[0029] The aforementioned connecting plate 4 is provided with a locking groove 13, and a T-shaped locking rod 14 is provided in the locking groove 13. The end of the T-shaped locking rod 14 is threadedly connected to the vertical plate 5. In the locked state, the locking head 15 of the T-shaped locking rod 14 is perpendicular to the locking groove 13. In the released state, the locking head 15 of the T-shaped locking rod 14 is parallel to the locking groove 13.

[0030] The test method of the aforementioned aircraft bend sealing test device is as follows: one end of the bend 16 under test is sealed with sealing component A7, and the other end is sealed with sealing component B17; the rotating plate 6 is moved to drive the connecting plate 4 so that the head of the push rod 9 abuts against the sealing component A7, and at the same time the connecting plate 4 drives the bending connecting rod 2 to move so that the clamping component 3 presses against the outside of the bend of the bend 16 under test; after the clamping is completed, the bend 16 under test is inflated through the air nozzle 8 via the sealing component B17 to conduct the sealing test.

[0031] After clamping, use the T-shaped locking rod 14 to lock the vertical plate 5 and the connecting plate 4.

[0032] After the test is completed, rotate the T-shaped locking rod 14 so that the locking head is parallel to the locking groove 13, and then turn the rotating plate 6 to make the top rod 9 disengage from the sealing component A7. The sealing component A7 exits from the end of the tested bent tube 16 until it is limited and abutted by the limiting plate 12. At the same time, the pressing component 3 also disengages from the tested bent tube 16. At this time, the tested bent tube 16 can be taken out.

[0033] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. An aviation elbow sealing test device, characterized in that: The invention comprises a base (1), one side of which is hinged to the bending part of the bending connecting rod (2), the vertical rod end of the bending connecting rod (2) is provided with a clamping assembly (3), and the transverse rod end of the bending connecting rod (2) is hinged to the bottom end of the connecting plate (4); a vertical plate (5) is provided on the side of the base (1) close to the connecting plate (4); the top end of the connecting plate (4) is hinged to one end of the rotating plate (6), and the other end of the rotating plate (6) is hinged to the vertical plate (5); a sealing assembly A (7) capable of translating along the normal direction of the vertical plate (5) is provided on the vertical plate (5); the base (1) is also provided with a sealing assembly B (17), and the sealing assembly B (17) is connected to the air nozzle (8); a push rod (9) is also threadedly connected to the connecting plate (4), and the head end of the push rod (9) is in contact with the sealing assembly A (7).

2. The aviation elbow sealing test device according to claim 1, characterized in that: The clamping assembly (3) comprises an adjusting rod (3.1), the adjusting rod (3.1) is threadedly connected to the vertical rod end of the bent connecting rod (2), and a pressure cover (3.2) is provided at the head end of the adjusting rod (3.1).

3. The aviation elbow sealing test device according to claim 1, characterized in that: The rotating plate (6) is provided with a handle (10) at the position where it is hinged to the vertical plate (5).

4. The aviation elbow sealing test device according to claim 1, characterized in that: An elastic component (11) is provided between the sealing component A (7) and the vertical plate (5); and a limiting plate (12) for limiting the sealing component A (7) is provided on the vertical plate (5).

5. The aviation elbow sealing test device according to claim 1, characterized in that: The connecting plate (4) is provided with a locking groove (13), a T-shaped locking rod (14) is provided in the locking groove (13), and the end of the T-shaped locking rod (14) is threadedly connected to the vertical plate (5); in a locked state, a locking head (15) of the T-shaped locking rod (14) is perpendicular to the locking groove (13), and in a released state, the locking head (15) of the T-shaped locking rod (14) is parallel to the locking groove (13).

6. A test method for the aviation elbow sealing test device as described in claims 1-5, characterized in that: One end of the test curved pipe (16) is sealed using the sealing assembly A (7), and the other end is sealed using the sealing assembly B (17); the rotating plate (6) is turned to drive the connecting plate (4) so ​​that the head end of the push rod (9) is pressed against the sealing assembly A (7), and at the same time, the connecting plate (4) drives the bending connecting rod (2) to move so that the clamping assembly (3) is pressed against the outer side of the bending part of the test curved pipe (16); after the clamping is completed, the test curved pipe (16) is inflated by the air nozzle (8) through the sealing assembly B (17) to perform a sealing test.

7. The test method of the aviation elbow sealing test device according to claim 6, characterized in that: After the clamping is completed, the vertical plate (5) and the connecting plate (4) are locked using a T-shaped locking rod (14).

8. The test method of the aviation elbow sealing test device according to claim 7, characterized in that: After the test is completed, the T-shaped locking rod (14) is rotated so that the locking head is parallel to the locking groove (13), and the rotating plate (6) is then turned to make the push rod (9) disengage from the sealing assembly A (7). The sealing assembly A (7) is withdrawn from the end of the tested curved pipe (16) until it is limited and abutted by the limiting plate (12). At the same time, the pressing assembly (3) is also disengaged from the tested curved pipe (16), and the tested curved pipe (16) can be taken out at this time.

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