Dynamic shearing test device and method for flexible connection assembly of aircraft fuel system

Abstract

This invention belongs to the field of testing technology, specifically relating to a dynamic shear test device and method for a flexible connection assembly of an aircraft fuel system. The test device includes a reciprocating assembly, a clamping assembly, and a loading assembly. A second push block in the reciprocating assembly is connected to a first locking block in the clamping assembly. The loading assembly is located on one side of the clamping assembly. The reciprocating assembly applies a shear load to the flexible connection assembly. The clamping assembly is responsible for clamping and fixing the test tube. The loading assembly injects pressure into the test tube. By connecting two test tubes using the flexible connection assembly, and controlling the pressurization module in the loading assembly to pressurize the test tube and the electric cylinder in the reciprocating assembly to apply thrust to the test tube, the internal working pressure and external shear load of the flexible connection assembly are tested. This provides standard equipment and methods for conducting life testing research on flexible connection assemblies, and also provides a reference for the selection of flexible connection assemblies.

Description

Technical Field

[0001] This invention belongs to the field of testing technology, specifically relating to a dynamic shearing test device and method for flexible connection components of an aircraft fuel system. Background Technology

[0002] Flexible connection assemblies are crucial components in aircraft fuel systems, connecting two conduits and ensuring both sealing and flexible cushioning. During flight, these assemblies must withstand both the internal working pressure from fuel flow and external shear loads generated by the aircraft's operation. Failure of a flexible connection assembly can lead not only to fuel leaks potentially causing fires, but also to flight control system malfunctions, endangering other systems and accessories and resulting in catastrophic consequences. In real-world flight conditions, flexible connection assemblies frequently operate in complex and variable environments, requiring exceptional pressure and shear resistance to ensure reliable fuel system operation; therefore, testing these assemblies is essential.

[0003] Currently, in practical field applications of flexible connection components, judgment mainly relies on engineers' experience, and there is no mature testing equipment available. To provide data support and reference for more scientific and rational guidance on the field repair, maintenance, and replacement of flexible connection components, and to offer designers a reference for selecting flexible connection components, there is an urgent need to design a dynamic shear testing device and method for aircraft fuel system flexible connection components, in order to conduct life testing research on flexible connection components. Summary of the Invention

[0004] To address the shortcomings of the prior art, this invention provides a dynamic shear testing device and method for flexible connection components in aircraft fuel systems. Two test tubes are connected using a flexible connection component. A pressurization module in the loading component applies pressure to the inside of the test tubes, and an electric cylinder in the reciprocating component applies radial thrust to the test tubes. This completes the testing of the internal working pressure and external shear load that the flexible connection component can withstand. This provides standard equipment and methods for conducting life testing research on flexible connection components and can be widely applied in the aerospace field.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] The present invention provides a dynamic shearing test device for a flexible connection component of an aircraft fuel system, which includes a reciprocating component, a clamping component and a loading component. The second push block in the reciprocating component is connected to the first locking block in the clamping component, and the loading component is disposed on one side of the clamping component.

[0007] The reciprocating assembly includes a base, an electric cylinder mounting base, an electric cylinder, a first push block, a second push block, and an external pressure sensor. The electric cylinder mounting base is disposed at a first end of the base, the electric cylinder is mounted on the electric cylinder mounting base, and the output end of the electric cylinder passes through the electric cylinder mounting base. The first end of the first push block is connected to the output shaft of the electric cylinder, and the second end of the first push block is connected to the first end of the second push block through the external pressure sensor.

[0008] The clamping assembly includes a first clamping block, a second clamping block, an axial limiting block, a lateral pipe, a sliding rod, a slider, a support plate, a central fixing plate, and a central pipe. The first clamping block and the second clamping block are connected. The lateral pipe is installed in the circular hole formed by the connection between the first clamping block and the second clamping block. The axial limiting blocks are respectively disposed at the connection points between the lateral pipe and the first and second clamping blocks. The support plate is disposed at the second end of the base. The support plate has rectangular sliding grooves at its four corners. The slider is installed in the rectangular sliding grooves and can slide in the rectangular sliding grooves. The sliding rod passes through the slots at both ends of the first and second clamping blocks in sequence, and the two ends of the sliding rod respectively cooperate with the slider mounted on the support plate. The central fixing plate is disposed in the middle of the two support plates. The central pipe is installed in the circular hole in the middle of the central fixing plate. The axial limiting block is disposed at the connection point between the central fixing plate and the central pipe.

[0009] Preferably, the loading component includes a pressurization module, a pressure supply pipe, a three-way adapter, and an internal pressure sensor. The pressurization module is connected to the first end of the three-way adapter via the pressure supply pipe, and the internal pressure sensor is connected to the second end of the three-way adapter.

[0010] Preferably, the center line of the output shaft of the electric cylinder and the center line of the slide rod are in a spatially parallel position.

[0011] Preferably, the first locking block, the second locking block, the axial limiting block, the lateral pipe, the slide bar, and the slider in the reciprocating assembly and the clamping assembly are symmetrically arranged on both sides of the central fixing plate.

[0012] Preferably, the centerline of the central hole in the lateral pipe is collinear with the centerline of the central hole in the middle pipe.

[0013] A second aspect of the present invention provides a test method for a dynamic shear test device for a flexible connection component of an aircraft fuel system, comprising the following steps:

[0014] S1. Set up the test device: Install the first and third test tubes in the middle of the two side pipes respectively, and install the second test tube in the middle of the middle pipe. Install a plug on the outer end of the first test tube, install the flexible connection component to be tested on the inner end of the first test tube and the first end of the second test tube, install the flexible connection component to be tested on the second end of the second test tube and the inner end of the third test tube, and connect the outer end of the third test tube to the third end of the tee adapter.

[0015] S2. Dynamic Shear Test: The pressurization module is activated to inject pressure into the test tube. When the internal pressure of the test tube rises to 0.02 MPa, it is recorded as t = 0 ms. The internal pressure is increased further. When the internal pressure of the test tube reaches the first holding pressure value, the pressurization is stopped and the pressure is held. At the same time, the electric cylinder is activated to apply radial thrust to the test tube. The flexible connection component is subjected to shear load. When the shear load reaches the preset load value, the electric cylinder stops. After a certain period, the electric cylinder reverses its operation, and the shear load decays back to zero. After the shear load drops to zero, the pressurization module is turned off. When the internal pressure of the test tube decays to a low pressure value, one dynamic shear test of the flexible connection component is completed.

[0016] S3. Repeat the dynamic shear test in S2. After every N test cycles, check the flexible connection component to determine if it has failed. Specifically:

[0017] S31. If the oil leakage of the flexible connection component is less than the leakage threshold, the damage of the flexible connection component is less than the damage threshold, and the internal pressure of the test tube is within the specified theoretical value range, continue to repeat the test by increasing the number of repetitions according to S2.

[0018] S32. If the oil leakage of the flexible connection component exceeds the leakage threshold, or the damage of the flexible connection component exceeds the damage threshold, or the internal pressure of the test tube exceeds the specified theoretical value range, the flexible connection component fails and the test is terminated.

[0019] Preferably, it also includes S4, analyzing the service life and variation pattern of the flexible connection component.

[0020] Preferably, in S2, the time range for the shear load of the flexible connecting component to be applied from zero to the preset load value is 1000 to 2000 ms; when the shear load of the flexible connecting component is the preset load value and is maintained for 100 ms, the internal pressure of the test tube is within 0.86 to 0.9 MPa.

[0021] Preferably, the test cycle rate in S3 is less than or equal to 40 cycles / minute.

[0022] Preferably, in S2, the first holding pressure value is set to 0.86 MPa, the preset load value of the shear load of the flexible connection component is 161 kg ± 1 kg, and the low pressure value to which the pressure inside the test tube decays is 0.03 (+0.01 / -0.02) MPa.

[0023] Compared with the prior art, the beneficial effects of the present invention include:

[0024] (1) The dynamic shear test device for flexible connection components of aircraft fuel system provided by the present invention drives the reciprocating motion of the lateral pipeline through the electric cylinder in the reciprocating component, thereby realizing the reciprocating motion of the test tube, and thus realizing the dynamic shear test of the flexible connection component. At the same time, the reciprocating component and the clamping component are symmetrically arranged along the middle fixed plate, so that two flexible connection components can be tested at the same time, improving the test efficiency.

[0025] (2) The aircraft fuel system flexible connection component dynamic shear test device provided by the present invention has a slider in the clamping component sliding in the rectangular groove of the support plate, which can adjust the position of the flexible connection component to meet different test requirements. At the same time, by replacing the side pipes and the middle pipes with different apertures, it can adapt to the test tubes of different diameters to meet the test requirements of flexible connection components of different specifications.

[0026] (3) The dynamic shear test method for flexible connection components provided by the present invention pressurizes the inside of the test tube by pressurizing module and applies radial thrust to the test tube by electric cylinder, so as to test the internal working pressure and external shear load that the flexible connection component can withstand. It provides standard equipment and methods for carrying out life test research of flexible connection components, and can be widely used in the aerospace field, with great application value. Attached Figure Description

[0027] Figure 1 This is a three-dimensional schematic diagram of the dynamic shear test device for the flexible connection component of the aircraft fuel system according to the present invention.

[0028] Figure 2 This is a front view of the dynamic shear test device for the flexible connection component of the aircraft fuel system according to the present invention.

[0029] Figure 3 This is a schematic diagram of the reciprocating component structure of the dynamic shear test device for the flexible connection component of the aircraft fuel system of the present invention.

[0030] Figure 4 This is a schematic diagram of the clamping component structure of the dynamic shearing test device for the flexible connection component of the aircraft fuel system of the present invention.

[0031] Figure 5 This is a schematic diagram of the structure of the aircraft fuel system flexible connection component dynamic shear test device of the present invention, which includes the flexible connection component and the accompanying test tube.

[0032] Figure 6 This is a flowchart illustrating the dynamic shear test method for the flexible connection component of the aircraft fuel system flexible connection component of the present invention.

[0033] Key reference numerals:

[0034] Reciprocating assembly 1, base 11, electric cylinder mounting base 12, electric cylinder 13, first push block 14, second push block 15, external pressure sensor 16, clamping assembly 2, first locking block 21, second locking block 22, axial limiting block 23, lateral pipeline 24, slide rod 25, slider 26, support plate 27, central fixing plate 28, central pipeline 29, loading assembly 3, pressurizing module 31, pressure transmission pipe 32, tee adapter 33, internal pressure sensor 34, flexible connection assembly 4, first test tube 5, second test tube 6, third test tube 7. Detailed Implementation

[0035] To provide a detailed description of the technical content, objectives, and effects of this invention, the following description will be provided in conjunction with the accompanying drawings.

[0036] Dynamic shear testing device for flexible connection components of aircraft fuel systems, such as Figure 1 and Figure 2 As shown, it includes a reciprocating component 1, a clamping component 2, and a loading component 3. The second push block 15 in the reciprocating component 1 is connected to the first locking block 21 in the clamping component 2. The loading component 3 is located on one side of the clamping component 1. The reciprocating component 1 applies a shear load to the flexible connecting component 4. The clamping component 2 is responsible for clamping and fixing the test tube. The loading component 3 injects pressure into the test tube.

[0037] The first locking block 21, the second locking block 22, the axial limiting block 23, the lateral pipe 24, the slide rod 25, and the slider 26 in the reciprocating assembly 1 and the clamping assembly 2 are symmetrically arranged on both sides of the central fixing plate 28; the loading assembly 3 includes a pressurizing module 31, a pressure transmission pipe 32, a three-way adapter 33, and an internal pressure sensor 34. The pressurizing module 31 is connected to the first end of the three-way adapter 33 through the pressure transmission pipe 32, and the internal pressure sensor 34 is connected to the second end of the three-way adapter 33. The internal pressure sensor 34 can detect the internal pressure on the flexible connection assembly 4 in real time.

[0038] like Figure 3As shown, the reciprocating assembly 1 includes a base 11, an electric cylinder mounting base 12, an electric cylinder 13, a first push block 14, a second push block 15, and an external pressure sensor 16. The electric cylinder mounting base 12 is located at the first end of the base 11. The electric cylinder 13 is mounted on the electric cylinder mounting base 12, and the output end of the electric cylinder 13 passes through the electric cylinder mounting base 12. The first end of the first push block 14 is connected to the output shaft of the electric cylinder 13. The second end of the first push block 14 is connected to the first end of the second push block 15 through the external pressure sensor 16. The external pressure sensor 16 can detect the shear load on the flexible connection assembly 4 in real time.

[0039] like Figure 4 As shown, the clamping assembly 2 includes a first locking block 21, a second locking block 22, an axial limiting block 23, a lateral pipe 24, a sliding rod 25, a slider 26, a support plate 27, a central fixing plate 28, and a central pipe 29. The first locking block 21 and the second locking block 22 are connected. The lateral pipe 24 is installed in the circular hole formed by the connection between the first locking block 21 and the second locking block 22. The axial limiting blocks 23 are respectively set at the connection between the lateral pipe 24 and the first locking block 21 and the second locking block 22. The axial limiting blocks 23 are used to restrict the axial movement of locking the lateral pipe 24, ensuring that the lateral pipe 24 will not slip out of the first locking block 21 and the second locking block 22. The support plate 27 is set at the second end of the base 11. The four corners of the support plate 27 are provided with rectangular sliding grooves. The slider 26 is installed in the rectangular sliding grooves and can slide in the rectangular sliding grooves. The sliding rod 25 passes through the first locking block 21 and the second locking block in sequence. The slots at both ends of the slide rod 25 are respectively engaged with the slider 26 mounted on the support plate 27. The first locking block 21 and the second locking block 22 can move axially along the slide rod 25. The center line of the output shaft of the electric cylinder 13 and the center line of the slide rod 25 are in a spatially parallel position to ensure that the thrust of the electric cylinder 13 is entirely applied to the lateral pipe 24. The middle fixing plate 28 is located in the middle of the two support plates 27. The middle pipe 29 is installed in the middle hole of the middle fixing plate 28. The axial limiting block 23 is located at the connection between the middle fixing plate 28 and the middle pipe 29. The axial limiting block 23 is used to limit the axial movement of the middle pipe 29. The center line of the middle hole of the lateral pipe 24 is collinear with the center line of the middle hole of the middle pipe 29 to ensure that the first test tube 5, the second test tube 6 and the third test tube 7 are on the same axis before the test.

[0040] like Figure 6 As shown, the test method of the dynamic shear test device for a flexible connection component of an aircraft fuel system according to the present invention is further described, which includes the following steps:

[0041] S1. Setting up the test apparatus: Install the first test tube 5 and the third test tube 7 between the two lateral pipes 24, respectively. Install the second test tube 6 between the middle pipe 29. Install a plug on the outer end of the first test tube 5. Install the flexible connection component 4 to be tested on the inner end of the first test tube 5 and the first end of the second test tube 7. Install the flexible connection component 4 to be tested on the second end of the second test tube 6 and the inner end of the third test tube 7. Connect the outer end of the third test tube 7 to the third end of the tee adapter 33. This dynamic shear test apparatus can install two flexible connection components 4 to be tested at one time. Figure 5 As shown, after installation, wipe the area around the flexible connection component 4 to be tested clean with dry paper.

[0042] S2. Dynamic Shear Test: The pressurization module 31 is activated to inject pressure into the test tube. When the internal pressure rises to 0.02 MPa, it is recorded as t = 0 ms. The internal pressure continues to increase. When the internal pressure of the test tube reaches the first holding pressure value, the pressurization is stopped and the pressure is maintained. At the same time, the electric cylinder 13 is activated to apply radial thrust to the test tube. The flexible connecting component 4 is subjected to shear load. When the shear load reaches the maximum shear load value, i.e., the preset load value, the electric cylinder 13 is stopped. After maintaining this position for a certain period of time, such as 100 ms, the electric cylinder 13 reverses its operation, and the shear load gradually decays back to zero. After the shear load drops to zero, the pressurization module 31 is turned off, and the internal pressure of the test tube gradually decays to a low pressure value. This is one dynamic shear test of the flexible connecting component 4. In a specific embodiment, the first holding pressure value is set to 0.86 MPa, the preset load value of the shear load of the flexible connecting component is 161 kg ± 1 kg, and the low pressure value to which the internal pressure of the test tube decays is 0.03 (+0.01 / -0.02) MPa.

[0043] S3. Repeat the dynamic shear test in S2. After every N test cycles, check the flexible connection component 4 to determine whether the flexible connection component 4 has failed. The test cycle rate shall not exceed 40 times per minute. In a specific implementation, N is set to 500 times.

[0044] S31. If the oil leakage of the flexible connection component 4 is less than the leakage threshold, and the damage degree of the flexible connection component 4 is less than the damage threshold, and the internal pressure of the test tube is within the specified theoretical value range, continue to repeat the test by increasing the number of repetitions according to S2.

[0045] S32. If the oil leakage of the flexible connection component 4 is greater than the leakage threshold, or the damage of the flexible connection component 4 is greater than the damage threshold, or the internal pressure of the test tube exceeds the specified theoretical value range, it indicates that the flexible connection component 4 has failed and the test is terminated.

[0046] S4. Analyze the service life and variation pattern of the flexible connection component 4.

[0047] Furthermore, in S2, the shear load of the flexible connection component 4 must be applied from zero to its maximum within a range of 1000–2000 ms.

[0048] Furthermore, in S2, when the flexible connection component 4 is subjected to the maximum shear load and held for 100 ms, the internal pressure of the test tube must be stabilized within the range of 0.86 to 0.9 MPa.

[0049] The following describes in further detail the dynamic shear testing device for a flexible connection assembly in an aircraft fuel system according to the present invention, with reference to specific embodiments. The specific usage process of the dynamic shear testing device for a flexible connection assembly in an aircraft fuel system according to the present invention is as follows:

[0050] First, the first test tube 5 and the third test tube 7 are installed in the middle of the two side pipes 24 respectively, and the second test tube 6 is installed in the middle of the middle pipe 29. The distance between the side pipes 24 and the central fixing plate 28 is adjusted by moving the slider 26 in the rectangular groove of the support plate 27. A plug is installed on the outer end of the first test tube 5. The inner end of the first test tube 5 and the first end of the second test tube 7 are connected by the flexible connection component to be tested 4. The second end of the second test tube 6 and the inner end of the third test tube 7 are connected by the flexible connection component to be tested 4. The outer end of the third test tube 7 is connected to the third end of the three-way adapter 33. The slider 2 is locked to the support plate 27.

[0051] Then, the pressurization module 31 is activated, and the pressure enters the test tube through the pressure transmission pipe 32 and the three-way adapter 33. The internal pressure sensor 34 detects the internal pressure on the flexible connection assembly 4 in real time and feeds it back to the computer. When the pressure reaches the set value, the electric cylinder 13 is activated. The output end of the electric cylinder 13 drives the first push block 14 to move forward. The second push block 15 then pushes the first locking block 21 and the second locking block 22 to move along the axial direction of the slide rod 25. The external pressure sensor 16 detects the thrust in real time and feeds it back to the computer. The first test tube 5 and the third test tube 7 are both misaligned with the second test tube 6, and the flexible connection assembly 4 is subjected to shear load.

[0052] Next, when the shear load reaches the set value, the electric cylinder 13 works in the opposite direction. The output end of the electric cylinder 13 drives the first push block 14 to move backward. The first test tube 5 and the third test tube 7 gradually return to their original positions, and the shear load on the flexible connection component 4 gradually decreases back to zero. After the shear load drops to zero, the pressurization module 31 is turned off, and the internal pressure of the test tubes also gradually decreases to zero. Thus, a complete dynamic shear test of the flexible connection component 4 is completed.

[0053] Finally, repeat the above process a certain number of times until the required number of tests is completed.

[0054] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A dynamic shear testing device for a flexible connection component of an aircraft fuel system, characterized in that, It includes a reciprocating assembly, a clamping assembly, and a loading assembly. The second push block in the reciprocating assembly is connected to the first locking block in the clamping assembly, and the loading assembly is disposed on one side of the clamping assembly. The reciprocating assembly includes a base, an electric cylinder mounting base, an electric cylinder, a first push block, a second push block, and an external pressure sensor. The electric cylinder mounting base is disposed at a first end of the base, the electric cylinder is mounted on the electric cylinder mounting base, and the output end of the electric cylinder passes through the electric cylinder mounting base. The first end of the first push block is connected to the output shaft of the electric cylinder, and the second end of the first push block is connected to the first end of the second push block through the external pressure sensor. The clamping assembly includes a first clamping block, a second clamping block, an axial limiting block, a lateral pipe, a sliding rod, a slider, a support plate, a central fixing plate, and a central pipe. The first clamping block and the second clamping block are connected. The lateral pipe is installed in the circular hole formed by the connection between the first clamping block and the second clamping block. The support plate is disposed at the second end of the base. The four corners of the support plate are respectively provided with rectangular sliding grooves. The slider is installed in the rectangular sliding grooves and can slide in the rectangular sliding grooves. The sliding rod passes through the slots at both ends of the first clamping block and the second clamping block in sequence, and the two ends of the sliding rod respectively cooperate with the slider installed on the support plate. The central fixing plate is disposed in the middle of the two support plates. The central pipe is installed in the circular hole in the middle of the central fixing plate. The axial limiting block is provided at the connection between the lateral pipe and the first clamping block and the second clamping block, and at the connection between the central fixing plate and the central pipe. The center line of the output shaft of the electric cylinder is parallel to the center line of the slide rod in space; The first clamping block, the second clamping block, the axial limiting block, the lateral pipe, the slide rod, and the slider in the clamping assembly are symmetrically arranged on both sides of the central fixing plate. The centerline of the central hole in the lateral pipe is collinear with the centerline of the central hole in the middle pipe.

2. The dynamic shear test device for flexible connection components of an aircraft fuel system according to claim 1, characterized in that, The loading component includes a pressurization module, a pressure transmission pipe, a three-way adapter, and an internal pressure sensor. The pressurization module is connected to the first end of the three-way adapter through the pressure transmission pipe, and the second end of the three-way adapter is connected to the internal pressure sensor.

3. A test method for a dynamic shear test device for a flexible connection assembly of an aircraft fuel system according to claim 1 or 2, characterized in that, It includes the following steps: S1. Set up the test device: Install the first and third test tubes in the middle of the two side pipes respectively, and install the second test tube in the middle of the middle pipe. Install a plug on the outer end of the first test tube, install the flexible connection component to be tested on the inner end of the first test tube and the first end of the second test tube, install the flexible connection component to be tested on the second end of the second test tube and the inner end of the third test tube, and connect the outer end of the third test tube to the third end of the tee adapter. S2. Dynamic Shear Test: The pressurization module is activated to inject pressure into the test tube. When the internal pressure of the test tube rises to 0.02 MPa, it is recorded as t=0 ms. The internal pressure is increased further. When the internal pressure of the test tube reaches the first holding pressure value, the pressurization is stopped and the pressure is held continuously. At the same time, the electric cylinder is activated to apply radial thrust to the test tube. The flexible connection component is subjected to shear load. When the shear load reaches the preset load value, the electric cylinder stops. After a certain period, the electric cylinder reverses its operation, and the shear load decays back to zero. After the shear load drops to zero, the pressurization module is turned off. When the internal pressure of the test tube decays to a low pressure value, one dynamic shear test of the flexible connection component is completed. S3. Repeat the dynamic shear test in S2. After every N test cycles, check the flexible connection component to determine if it has failed. Specifically: S31. If the oil leakage of the flexible connection component is less than the leakage threshold, the damage of the flexible connection component is less than the damage threshold, and the internal pressure of the test tube is within the specified theoretical value range, continue to repeat the test by increasing the number of repetitions according to S2. S32. If the oil leakage of the flexible connection component exceeds the leakage threshold, or the damage of the flexible connection component exceeds the damage threshold, or the internal pressure of the test tube exceeds the specified theoretical value range, the flexible connection component fails and the test is terminated.

4. The test method of the dynamic shear test device for flexible connection components of aircraft fuel systems according to claim 3, characterized in that, It also includes S4, analyzing the service life and variation patterns of flexible connection components.

5. The test method of the dynamic shear test device for flexible connection components of aircraft fuel systems according to claim 4, characterized in that, In S2, the time range for the shear load of the flexible connection component to be applied from zero to the preset load value is 1000~2000ms; when the shear load of the flexible connection component is the preset load value and is maintained for 100ms, the internal pressure of the test tube is within 0.86~0.9MPa.

6. The test method of the dynamic shear test device for flexible connection components of aircraft fuel systems according to claim 4, characterized in that, The test cycle rate in S3 is less than or equal to 40 cycles / minute.

7. The test method of the dynamic shear test device for flexible connection components of aircraft fuel systems according to claim 5, characterized in that, In S2, the first holding pressure value is set to 0.86 MPa, the preset load value of the shear load of the flexible connection component is 161 kg ± 1 kg, and the low pressure value of the pressure inside the test tube is 0.03 (+0.01 / -0.02) MPa.

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