Aircraft fuel tank leakage point screening device

Abstract

The invention belongs to the technical field of aircraft assembly detection, and relates to an aircraft fuel tank leakage point screening device. The installation water inlet structure and the inflation detection structure are adopted, during use, the aircraft fuel tank is inflated, the air pressure in the fuel tank is increased, the whole fuel tank is soaked in liquid through the arranged installation water soaking structure, and when leakage points occur in the fuel tank, gas can pass through the leakage points along with increase of the air pressure to generate continuous bubbles, so that the leakage points are prevented from leaking. On one hand, the leakage point detection effect of the aircraft fuel tank is ensured, and on the other hand, the leakage point detection cost of the aircraft fuel tank can be effectively reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft assembly detection and relates to an aircraft oil tank leakage screening device. Background Art

[0002] Aircraft fuel tanks are containers for fuel. In addition to storing fuel, they also play a role in heat dissipation, separating bubbles in the oil, and precipitating impurities. They are also required to have certain safety and durability.

[0003] After the fuel tank is processed, in order to ensure the overall sealing of the fuel tank, the entire fuel tank must be tested for leaks to ensure the safety of the aircraft fuel tank environment. Currently, most fuel tank leak detection methods are fuel tank pressure testing and oil leak detection dyes. The fuel tank pressure test method is to inject gas or liquid into the fuel tank and monitor the pressure changes. The overall detection time is relatively long and cannot meet the needs of efficient fuel tank processing. The oil leak detection dye method is to add certain special dyes to the fuel to make it change color when an oil leak occurs, resulting in a high cost for the overall leak detection process of the fuel tank. In view of this, there may already be technical means to solve the above problems in the prior art, but this case intends to provide an alternative or replacement technical solution. Summary of the invention

[0004] In order to solve the above problems, the present invention provides an aircraft fuel tank leakage screening device.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0006] An aircraft fuel tank leakage screening device comprises a detection box, wherein two water-immersing structures are arranged at the rear of the detection box, mounting frames are arranged at both sides of the detection box, and an inflation detection structure is arranged at the upper end of the mounting frame;

[0007] One of the installation immersion structures comprises: an operating frame, a first screw rod, a motor, a moving block, a fixed support plate, a clamping frame, a clamping plate and a second screw rod;

[0008] The operating frame is fixedly installed on one side of the lower end of the detection box body, the first screw rod is movably embedded in the operating frame, the motor is fixedly installed on the upper end of the operating frame, and the driving end is connected to one end of the first screw rod, the moving block is movably sleeved on the upper end of the first screw rod, and the two sides are movably sleeved on the two sides of the operating frame respectively, the fixed support plate is fixedly installed on the front side of the moving block, the clamping frame is fixedly installed on the upper end of the moving block, the clamping plate is movably sleeved on the upper end of the clamping frame, one end of the second screw rod is movably connected to the clamping frame, and is movably embedded in the clamping plate.

[0009] Structural features: An aircraft fuel tank leak screening device includes a detection box, characterized in that two water-immersed structures are provided on the rear side of the detection box, mounting frames are provided on both sides of the detection box, and an inflation detection structure is provided on the upper end of the mounting frame;

[0010] One of the installation immersion structures comprises: an operating frame, a first screw rod, a motor, a moving block, a fixed support plate, a clamping frame, a clamping plate and a second screw rod;

[0011] The operating frame is fixedly installed on one side of the lower end of the detection box body, the first screw rod is movably embedded in the operating frame, the motor is fixedly installed on the upper end of the operating frame, and the driving end is connected to one end of the first screw rod, the moving block is movably sleeved on the upper end of the first screw rod, and the two sides are movably sleeved on the two sides of the operating frame respectively, the fixed support plate is fixedly installed on the front side of the moving block, the clamping frame is fixedly installed on the upper end of the moving block, the clamping plate is movably sleeved on the upper end of the clamping frame, one end of the second screw rod is movably connected to the clamping frame, and is movably embedded in the clamping plate.

[0012] The inflation detection structure includes: two air compressors, two control valves, two connecting hoses, two sealing connectors and two camera bodies;

[0013] The two air compressors are respectively installed on both sides of the upper end of the mounting frame, the two control valves are respectively installed on the inner wall surfaces on both sides of the mounting frame, and are respectively connected to the air outlets of the two air compressors, one end of the two connecting hoses is respectively connected to the two control valves, the two sealing connectors are respectively connected to the lower ends of the two connecting hoses, and the two camera bodies are respectively fixedly installed on both sides of the upper end of the mounting frame. The shape of the clamping frame is "H"-shaped, the shape of the fixed support plate is "L"-shaped, one end of the second screw rod is provided with an operating nut, and the mounting frame is a door-shaped mounting frame.

[0014] Preferably, the inflation detection structure comprises: two air compressors, two control valves, two connecting hoses, two sealing connectors and two camera bodies;

[0015] The two air compressors are respectively installed on both sides of the upper end of the mounting frame, the two control valves are respectively installed on the inner wall surfaces on both sides of the mounting frame, and are respectively connected to the air outlet ends of the two air compressors, one end of the two connecting hoses is respectively connected to the two control valves, the two sealing connectors are respectively connected to the lower ends of the two connecting hoses, and the two camera bodies are respectively fixedly installed on both sides of the upper end of the mounting frame.

[0016] Preferably, the clamping frame is in an "H" shape.

[0017] Preferably, the fixed support plate is in an "L" shape.

[0018] Preferably, an operating nut is provided at one end of the second screw rod.

[0019] Preferably, the mounting frame is a door-shaped mounting frame.

[0020] Beneficial effects of the present invention:

[0021] The water inlet installation structure and the inflation detection structure adopted in the present invention are used to inflate the aircraft fuel tank during use, so that the air pressure in the fuel tank is increased, and the entire fuel tank is immersed in liquid through the arranged water immersion installation structure. When a leak occurs in the fuel tank, as the air pressure increases, the gas will pass through the leak position to generate continuous bubbles, so that the staff can observe the leak position. On the one hand, the leak detection effect of the aircraft fuel tank is guaranteed, and on the other hand, the cost of leak detection of the aircraft fuel tank can be effectively reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the main stereoscopic structure of an aircraft fuel tank leakage screening device according to the present invention;

[0023] Figure 2 It is a schematic diagram of a side cross-sectional structure of an aircraft fuel tank leakage screening device according to the present invention;

[0024] Figure 3 The present invention is a schematic diagram of the main structure of an aircraft fuel tank leakage screening device.

[0025] In the figure: 1 detection box, 2 mounting frame, 3 operating frame, 4 first screw rod, 5 motor, 6 moving block, 7 fixed support plate, 8 clamping frame, 9 clamping plate, 10 second screw rod, 11 air compressor, 12 control valve, 13 connecting hose, 14 sealing connector, 15 camera body, 16 operating nut. DETAILED DESCRIPTION

[0026] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in the field without making any creative work shall fall within the scope of protection of the present invention.

[0027] Embodiment 1:

[0028] See also Figure 1-3 In order to solve the problems of slow detection effect and high detection cost caused by the current aircraft fuel tank pressure test and oil leakage detection dye method, an aircraft fuel tank leakage screening device is set up, including a detection box 1, two installation immersion structures are arranged on the rear side of the detection box 1, and mounting frames 2 are arranged on both sides of the detection box 1, and an inflation detection structure is arranged on the upper end of the mounting frame 2;

[0029] One of the installation immersion structures includes: an operating frame 3, a first screw rod 4, a motor 5, a moving block 6, a fixed support plate 7, a clamping frame 8, a clamping plate 9 and a second screw rod 10;

[0030] The operating frame 3 is fixedly installed on one side of the lower end of the detection box 1, the first screw rod 4 is movably embedded in the operating frame 3, the motor 5 is fixedly installed on the upper end of the operating frame 3, and the driving end is connected to one end of the first screw rod 4, the moving block 6 is movably sleeved on the upper end of the first screw rod 4, and the two sides are movably sleeved on the two sides of the operating frame 3 respectively, the fixed support plate 7 is fixedly installed on the front side of the moving block 6, the clamping frame 8 is fixedly installed on the upper end of the moving block 6, the clamping plate 9 is movably sleeved on the upper end of the clamping frame 8, and one end of the second screw rod 10 is movably connected to the clamping frame 8, and is movably embedded in the clamping plate 9.

[0031] When in use, the staff first injects liquid into the detection box 1, and the detection liquid is carried by the detection box 1, and then the device is connected to the power supply, and the motor 5 and the air compressor 11 and other electrical components of the device are driven by the power supply to work, and then the oil tank to be tested is placed on the front side of the operating frame 3, and the second screw rod 10 in the clamping frame 8 is twisted, and the second screw rod 10 rotates in the clamping frame 8, and drives the clamping plate 9 to move backward until the inner side of the clamping plate 9 fits with one side of the oil tank, and cooperates with the fixed support plate 7 to clamp and fix the oil tank. The adjustable fixing method can be adjusted according to oil tanks of different specifications to meet the detection requirements of oil tanks of different specifications. When the oil tank is fixed, the inflation detection structure is then connected with The oil tank is connected, and air is injected into the oil tank to increase the air pressure in the oil tank. Then, the motor 5 at the upper end of the operating frame 3 works to drive the first screw rod 4 to rotate in the operating frame 3. Through the rotation of the first screw rod 4, the moving block 6 moves downward in the operating frame 3 until the oil tank between the fixed support plate 7 and the clamping plate 9 is completely immersed in the liquid. When there is a leak in the oil tank immersed in the liquid, the high-pressure gas in the oil tank will spray out through the leak position and produce continuous bubbles in the liquid. By observing the position of the bubbles, the leak situation of the oil tank can be understood. After the detection is completed, the moving block 6 is reset by reversing the motor 5, and the inflation detection structure is disconnected from the oil tank. The second screw rod 10 can be turned to remove the oil tank, and the oil tanks can be classified and stored according to the leak situation.

[0032] Embodiment 2:

[0033] The inflation detection structure includes: two air compressors 11, two control valves 12, two connecting hoses 13, two sealing connectors 14 and two camera bodies 15;

[0034] The two air compressors 11 are respectively installed on both sides of the upper end of the mounting frame 2, the two control valves 12 are respectively installed on the inner wall surfaces on both sides of the mounting frame 2, and are respectively connected to the air outlet ends of the two air compressors 11, one end of the two connecting hoses 13 is respectively connected to the two control valves 12, the two sealing connectors 14 are respectively connected to the lower ends of the two connecting hoses 13, and the two camera bodies 15 are respectively fixedly installed on both sides of the upper end of the mounting frame 2.

[0035] When leak detection is performed on the aircraft fuel tank, the staff first connects the sealing connector 14 to the fixed fuel tank, and then drives the air compressor 11 at the upper end of the mounting frame 2 to work, compresses the gas and injects it into the fuel tank through the connecting hose 13 and the sealing connector 14, and pressurizes the fuel tank. During the inflation process, the sealing connector 14 is used to ensure the connection sealing with the fuel tank. The connecting hose 13 is used to ensure the connection stability between the sealing connector 14 and the fuel tank when the fuel tank descends. The control valve 12 is used to control the internal air pressure of the fuel tank in real time to ensure that the air pressure in the fuel tank is always in a high pressure state. The camera body 15 is used to realize remote monitoring of the leakage state of the fuel tank. The shape of the clamping frame 8 is "H". The shape of the fixed support plate 7 is "L". An operating nut 16 is provided at one end of the second screw rod 10. The mounting frame 2 is a door-shaped mounting frame.

Claims

1. An aircraft fuel tank leak screening device, characterized in that: It comprises a detection box (1), wherein a water immersion installation structure is provided at the inner rear side of the detection box (1), mounting frames (2) are provided at both sides of the detection box (1), and an inflation detection structure is provided at the upper end of the mounting frame (2); The installation immersion structure comprises an operating frame (3), a first screw rod (4), a motor (5), a moving block (6), a fixed support plate (7), a clamping frame (8), a clamping plate (9) and a second screw rod (10); The operating frame (3) is fixedly mounted on one side of the lower end of the detection box (1); the first screw rod (4) is movably embedded in the operating frame (3); the motor (5) is fixedly mounted on the upper end of the operating frame (3), and the driving end is connected to one end of the first screw rod (4); the moving block (6) is movably mounted on the upper end of the first screw rod (4), and the two sides are movably mounted on the two sides of the operating frame (3); the fixed support plate (7) is fixedly mounted on the front side of the moving block (6); the clamping frame (8) is fixedly mounted on the upper end of the moving block (6); the clamping plate (9) is movably mounted on the upper end of the clamping frame (8); one end of the second screw rod (10) is movably connected to the clamping frame (8), and is movably embedded in the clamping plate (9); The inflation detection structure comprises: two air compressors (11), two control valves (12), two connecting hoses (13), two sealing connectors (14) and two camera bodies (15); The two air compressors (11) are respectively installed on both sides of the upper end of the mounting frame (2); the two control valves (12) are respectively installed on the inner wall surfaces on both sides of the mounting frame (2) and are respectively connected to the air outlet ends of the two air compressors (11); one end of the two connecting hoses (13) is respectively connected to the two control valves (12); the two sealing connectors (14) are respectively connected to the lower ends of the two connecting hoses (13); and the two camera bodies (15) are respectively fixedly installed on both sides of the upper end of the mounting frame (2).

2. The aircraft fuel tank leak screening device according to claim 1, characterized in that: The clamping frame (8) is in an "H" shape.

3. An aircraft fuel tank leak screening device as claimed in claim 1 or 2, characterized in that: The fixed support plate (7) is in an "L" shape.

4. An aircraft fuel tank leak screening device as claimed in claim 1 or 2, characterized in that: An operating nut (16) is provided at one end of the second screw rod (10).

5. The aircraft fuel tank leakage screening device according to claim 3, characterized in that: An operating nut (16) is provided at one end of the second screw rod (10).

6. An aircraft fuel tank leak screening device as claimed in claim 1, 2 or 5, characterized in that: The mounting frame (2) is a door-shaped mounting frame.

7. The aircraft fuel tank leakage screening device according to claim 3, characterized in that: The mounting frame (2) is a door-shaped mounting frame.

8. The aircraft fuel tank leak screening device according to claim 4, characterized in that: The mounting frame (2) is a door-shaped mounting frame.

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