Aircraft fuel tank sealing performance detection test tool

Abstract

The utility model discloses an airplane fuel tank sealing performance detection test tool comprising a detection box, the inner bottom wall of the detection box is fixedly connected with two placing seats, the inner walls of the two placing seats are jointly clamped with an airplane fuel tank, the right side surface of the detection box is fixedly connected with a pressurizing air pump, and the pressurizing air pump is fixedly connected with a pressure sensor. And the output end of the pressurizing air pump fixedly communicates with a conveying air pipe. Through the arrangement of the detection box, the placement seat, the fastening support plate, the fastening bolt, the clamping plate, the water conveying pipe, the pressurizing air pump, the conveying air pipe, the inflation head and the fastening cap, the inflation head can be in butt joint communication with the input end of the aircraft fuel tank through the fastening cap, pressurization and inflation of the interior of the aircraft fuel tank are achieved through work of the pressurizing air pump, and water injection and storage can be conducted; and through the arrangement of the waterproof illuminating lamp and the observation frame, detection personnel can conveniently detect and observe the air tightness of the aircraft fuel tank, and effective detection work of the aircraft fuel tank is facilitated.

Description

Technical Field

[0001] This utility model relates to the field of aircraft fuel tank testing technology, and in particular to a testing fixture for testing the sealing performance of aircraft fuel tanks. Background Technology

[0002] With the development of society, the application of aircraft fuel tanks is becoming more and more widespread. Aircraft fuel tanks are containers for storing fuel on aircraft and are special containers for storing hydraulic oil or hydraulic fluid in hydraulic systems. The fuel tank must have a sufficiently large volume, and the oil suction pipe and oil return pipe should be inserted below the lowest liquid level to prevent air suction and oil return splashing that will generate air bubbles. The distance between the oil suction pipe and the oil return pipe should be as far as possible, and a baffle should be installed between them. After the aircraft fuel tank is manufactured, it needs to be tested for air tightness.

[0003] Among them, the utility model patent with announcement number CN219084334U discloses a test fixture for testing the sealing performance of aircraft fuel tanks. However, the above patent still has certain shortcomings in use. When testing aircraft fuel tanks, it is not possible to directly and effectively observe and detect whether the fuel tank is leaking, which is not convenient for the effective testing of the airtightness of aircraft fuel tanks. Therefore, we propose a test fixture for testing the sealing performance of aircraft fuel tanks to solve the above problems. Utility Model Content

[0004] The purpose of this invention is to provide a testing fixture for detecting the sealing performance of aircraft fuel tanks, in order to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A testing fixture for aircraft fuel tank sealing performance includes a testing chamber. Two placement seats are fixedly connected to the inner bottom wall of the testing chamber, and the inner walls of the two placement seats are jointly engaged with an aircraft fuel tank. A pressurizing air pump is fixedly connected to the right side of the testing chamber. The output end of the pressurizing air pump is fixedly connected to a delivery air pipe, and the output end of the delivery air pipe is fixedly connected to an inflation head. A fastening cap is fitted onto the outer surface of the inflation head. Two sets of symmetrical fastening support plates are fixedly connected to the inner wall of the testing chamber. A fastening bolt is threaded onto the inner wall of each fastening support plate. A clamping plate is provided below each fastening support plate, and a bearing is fixedly embedded on the upper surface of each clamping plate. The bottom end of each fastening bolt is fixedly connected to the inner ring of the bearing. Two sets of observation frames are fixedly embedded on the outer surface of the testing chamber. A water supply pipe is fixedly connected to the left side of the testing chamber, and a first control valve is fixedly connected to the outer surface of the water supply pipe.

[0007] In a further embodiment, a protective shell is fixedly connected to the right side of the testing box, and a control panel is fixedly connected to the inner wall of the protective shell. The control panel is electrically connected to the pressurizing air pump via wires.

[0008] In a further embodiment, two waterproof lights are fixedly connected to the inner wall of the testing box, and the waterproof lights are located in the middle of the testing box.

[0009] In a further embodiment, the outer surface of the fastening cap is fixedly connected with an annular arrangement of anti-slip protrusions, which are made of rubber.

[0010] In a further embodiment, a drain pipe is fixedly connected to the left side of the detection box, and a second control valve is fixedly connected to the upper surface of the drain pipe.

[0011] In a further embodiment, the bottom surface of the testing box is fixedly connected to two sets of mounting plates, and each mounting plate has mounting holes on its upper surface.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] This device, consisting of a testing box, a placement base, a fastening support plate, fastening bolts, a clamping plate, a water supply pipe, a pressurizing air pump, a delivery air pipe, an inflation head, and a fastening cap, allows the inflation head to connect to the input end of the aircraft fuel tank via the fastening cap. The pressurizing air pump then pressurizes and inflates the interior of the aircraft fuel tank, and can also fill it with water to test its water tightness. Furthermore, the included waterproof lighting and observation frame facilitate the testing and observation of the aircraft fuel tank's air tightness, enabling effective testing of the aircraft fuel tank. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall three-dimensional structure of the testing fixture used for testing the sealing performance of aircraft fuel tanks.

[0015] Figure 2 This is a side view of the test chamber in a testing fixture used for testing the sealing performance of aircraft fuel tanks.

[0016] Figure 3 This is a schematic diagram of the internal cross-sectional structure of the test chamber in a testing fixture used for testing the sealing performance of aircraft fuel tanks.

[0017] Figure 4 This is a top view of the test chamber in a testing fixture used for testing the sealing performance of aircraft fuel tanks.

[0018] Figure 5 For use in aircraft fuel tank sealing test fixtures Figure 1 A magnified structural diagram of part A in the middle.

[0019] In the diagram: 1. Testing box; 2. Mounting hole; 3. Observation frame; 4. Mounting support plate; 5. Water supply pipe; 6. First control valve; 7. Fastening support plate; 8. Fastening bolt; 9. Bearing; 10. Waterproof lighting lamp; 11. Anti-slip protrusion; 12. Air supply pipe; 13. Pressurizing air pump; 14. Protective shell; 15. Second control valve; 16. Drain pipe; 17. Control panel; 18. Fastening cap; 19. Aircraft fuel tank; 20. Placement seat; 21. Inflation head; 22. Clamping plate. Detailed Implementation

[0020] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this utility model and simplifying the description, 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, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0021] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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; and they can refer to the internal connection of 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.

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Please see Figure 1-5In this utility model, a testing fixture for testing the sealing performance of aircraft fuel tanks includes a testing box 1. Two placement seats 20 are fixedly connected to the inner bottom wall of the testing box 1. An aircraft fuel tank 19 is clamped to the inner wall of the two placement seats 20. A pressurizing air pump 13 is fixedly connected to the right side of the testing box 1. A delivery air pipe 12 is fixedly connected to the output end of the pressurizing air pump 13. An inflation head 21 is fixedly connected to the output end of the delivery air pipe 12. A fastening cap 18 is fitted onto the outer surface of the inflation head 21. The inner wall of the test box 1 is fixedly connected with two sets of symmetrical fastening support plates 7. Each fastening support plate 7 has a fastening bolt 8 threadedly connected to its inner wall. Each fastening support plate 7 has a clamping plate 22 below it. Each clamping plate 22 has a bearing 9 fixedly embedded on its upper surface. The bottom end of each fastening bolt 8 is fixedly connected to the inner ring of the bearing 9. The outer surface of the test box 1 is fixedly embedded with two sets of observation frames 3. The left side of the test box 1 is fixedly connected to a water supply pipe 5. The outer surface of the water supply pipe 5 is fixedly connected to a first control valve 6.

[0024] A protective shell 14 is fixedly connected to the right side of the test chamber 1. A control panel 17 is fixedly connected to the inner wall of the protective shell 14. The control panel 17 is electrically connected to the pressurizing air pump 13 via wires, which can conveniently control this tooling and facilitate the sealing test of the oil tank. Two waterproof lights 10 are fixedly connected to the inner wall of the test chamber 1. The waterproof lights 10 are located in the middle of the test chamber 1 and can provide illumination for the interior of the test chamber 1, which is convenient for effective observation of bubbles.

[0025] The outer surface of the fastening cap 18 is fixedly connected with annularly arranged anti-slip protrusions 11. The anti-slip protrusions 11 are made of rubber, which can increase the surface anti-slip properties of the fastening cap 18 and facilitate the rotation operation of the fastening cap 18. The left side of the test box 1 is fixedly connected to a drain pipe 16, and the upper surface of the drain pipe 16 is fixedly connected to a second control valve 15, which can facilitate the discharge of water inside the test box 1. The bottom surface of the test box 1 is fixedly connected to two sets of mounting plates 4. Each mounting plate 4 has a mounting hole 2 on its upper surface, which can install and fix the test box 1, facilitating the stable use of this testing fixture.

[0026] The working principle of this utility model is as follows:

[0027] In use, the test box 1 is first installed and fixed by the mounting plate 4 and mounting hole 2. Then, the tooling is powered on, and the aircraft fuel tank 19 is hoisted into the placement seat 20 inside the aircraft fuel tank 19. Next, the fastening bolt 8 is rotated to move the clamping plate 22 downward to clamp and position the aircraft fuel tank 19. Then, the inflation head 21 is inserted into the input port of the aircraft fuel tank 19 and the fastening cap 18 is threaded on to achieve a sealed connection between the inflation head 21 and the aircraft fuel tank 19. Next, the pressurizing air pump 13 is controlled to work to supply pressure to the inside of the aircraft fuel tank 19 through the air supply pipe 12. Then, the first control valve 6 is opened to supply water to the inside of the test box 1 through the water supply pipe 5. Then, the airtightness of the aircraft fuel tank 19 is tested by observing whether air bubbles are generated through the observation frame 3 and the top of the test box 1.

[0028] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0029] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A testing fixture for detecting the sealing performance of aircraft fuel tanks, characterized in that: The test chamber includes a test box (1), the inner bottom wall of which is fixedly connected to two placement seats (20), the inner walls of which are jointly fitted with an aircraft fuel tank (19). A pressurizing air pump (13) is fixedly connected to the right side of the test box (1), the output end of which is fixedly connected to a delivery air pipe (12), the output end of which is fixedly connected to an inflation head (21), the outer surface of which is fitted with a fastening cap (18). Two sets of symmetrical... The fastening support plate (7) is threaded with a fastening bolt (8) on the inner wall of each fastening support plate (7). A clamping plate (22) is provided below each fastening support plate (7). A bearing (9) is fixedly embedded on the upper surface of each clamping plate (22). The bottom end of each fastening bolt (8) is fixedly connected to the inner ring of the bearing (9). Two sets of observation frames (3) are fixedly embedded on the outer surface of the detection box (1). A water supply pipe (5) is fixedly connected to the left side of the detection box (1). A first control valve (6) is fixedly connected to the outer surface of the water supply pipe (5).

2. The testing fixture for aircraft fuel tank sealing performance according to claim 1, characterized in that: A protective shell (14) is fixedly connected to the right side of the test box (1), and a control panel (17) is fixedly connected to the inner wall of the protective shell (14). The control panel (17) is electrically connected to the pressurizing air pump (13) through a wire.

3. The testing fixture for aircraft fuel tank sealing performance according to claim 1, characterized in that: Two waterproof lights (10) are fixedly connected to the inner wall of the testing box (1), and the waterproof lights (10) are located in the middle of the testing box (1).

4. The testing fixture for detecting the sealing performance of aircraft fuel tanks according to claim 1, characterized in that: The outer surface of the fastening cap (18) is fixedly connected with annularly arranged anti-slip protrusions (11), which are made of rubber.

5. The testing fixture for detecting the sealing performance of aircraft fuel tanks according to claim 1, characterized in that: The left side of the detection box (1) is fixedly connected to a drain pipe (16), and the upper surface of the drain pipe (16) is fixedly connected to a second control valve (15).

6. The testing fixture for detecting the sealing performance of aircraft fuel tanks according to claim 1, characterized in that: The bottom surface of the testing box (1) is fixedly connected to two sets of mounting plates (4), and each mounting plate (4) has a mounting hole (2) on its upper surface.

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