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

Abstract

The invention belongs to the technical field of testing, and particularly relates to a dynamic shear testing device and method for a flexible connection assembly of an aircraft fuel system, the testing device comprises a reciprocating assembly, a clamping assembly and a loading assembly, a second push block in the reciprocating assembly is connected with a first clamping block in the clamping assembly, and the loading assembly is arranged on one side of the clamping assembly. The reciprocating assembly applies shear load to the flexible connecting assembly, the clamping assembly is responsible for clamping and fixing accompanying test tubes, the loading assembly injects pressure into the accompanying test tubes, and the two sections of accompanying test tubes are connected through the flexible connecting assembly. And then a pressurization module in the loading assembly is controlled to pressurize the interior of the accompanying test tube and an electric cylinder in the reciprocating assembly is controlled to apply thrust to the accompanying test tube, so that the internal working pressure and the external shear load of the flexible connection assembly are tested, and standard equipment and a standard method are provided for carrying out life test research on the flexible connection assembly. And a reference basis is provided during model selection of the flexible connection assembly.

Description

Technical Field

[0001] The present invention belongs to the technical field of testing, and particularly relates to a dynamic shear test device and test method for a flexible connection component of an aircraft fuel system. Background Art

[0002] The flexible connection component is an important connection component in the aircraft fuel system, used to connect two sections of ducts to ensure the sealing effect and flexible buffering function of the ducts. When the aircraft is flying, the flexible connection component not only needs to bear the internal working pressure generated by the fuel flow, but also resist the external shear load during the operation of the aircraft. During application, if the flexible connection component fails, it will not only cause fuel leakage, which may lead to a fire, but may even cause the flight control system to fail, endangering other systems and accessories, resulting in catastrophic consequences. In actual flight conditions, the flexible connection components are often in a complex and changeable environment, and they must have excellent pressure resistance and shear resistance to ensure the reliable operation of the fuel system. Therefore, it is necessary to test the flexible connection components.

[0003] Currently, in the actual field application of flexible connection components, it mainly relies on the experience of engineers to judge, and there is no relatively mature test device available. In order to provide data support and reference for more scientific and reasonable guidance of the field maintenance, repair, and replacement of new parts of flexible connection components, and to provide a reference basis for designers when selecting flexible connection components, it is urgent to design a dynamic shear test device and test method for flexible connection components of an aircraft fuel system to carry out the life test research of flexible connection components. Summary of the Invention

[0004] In order to solve the deficiencies of the above-mentioned prior art, the present invention provides a dynamic shear test device and test method for a flexible connection component of an aircraft fuel system. Two sections of companion tubes are connected by a flexible connection component, the inside of the companion tubes is pressurized by a pressurizing module in the loading component, and a radial thrust is applied to the companion tubes by an electric cylinder in the reciprocating component, so as to complete the test of the internal working pressure and external shear load that the flexible connection component can bear, provide standard equipment and methods for carrying out the life test research of flexible connection components, and can be widely applied in the aerospace field.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] The present invention provides a dynamic shear 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 clamping block in the clamping component, and the loading component is arranged on one side of the clamping component;

[0007] The reciprocating assembly includes a base, an electric cylinder mount, an electric cylinder, a first push block, a second push block, and an external pressure sensor. The electric cylinder mount is disposed at the first end of the base. The electric cylinder is mounted on the electric cylinder mount, and the output end of the electric cylinder passes through the electric cylinder mount. 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 pipeline, a sliding rod, a slider, a support plate, a middle fixing plate, and a middle pipeline. The first clamping block is docked with the second clamping block. The lateral pipeline is installed in a circular hole formed by the docking of the first clamping block and the second clamping block. The axial limiting blocks are respectively disposed at the joints of the lateral pipeline with the first clamping block and the second clamping block. The support plate is disposed at the second end of the base. Rectangular sliding grooves are provided at the four corners of the support plate. The slider is installed in the rectangular sliding groove and can slide in the rectangular sliding groove. The sliding rod sequentially passes through the slot holes at both ends of the first clamping block and the second clamping block, and both ends of the sliding rod are respectively matched with the sliders installed on the support plate. The middle fixing plate is disposed at the middle position between the two support plates. The middle pipeline is installed in a circular hole in the middle of the middle fixing plate. The axial limiting block is disposed at the joint of the middle fixing plate and the middle pipeline.

[0009] Preferably, the loading assembly includes a pressurizing module, a pressure transmission pipe, a three-way adapter, and an internal pressure sensor. The pressurizing module is connected to the first end of the three-way adapter through the pressure transmission 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 sliding rod are in a parallel positional relationship in space.

[0011] Preferably, the first clamping block, the second clamping block, the axial limiting block, the lateral pipeline, the sliding rod, and the slider in the reciprocating assembly and the clamping assembly are symmetrically disposed on both sides of the middle fixing plate.

[0012] Preferably, the center line of the middle circular hole of the lateral pipeline and the center line of the middle circular hole of the middle pipeline are collinear.

[0013] In the second aspect of the present invention, a test method for a dynamic shear test device of a flexible connection assembly of an aircraft fuel system is provided, which includes the following steps:

[0014] S1. Set up the test device: Install the first and third companion tubes in the middle of two lateral pipelines respectively, install the second companion tube in the middle of the middle pipeline, install a plug at the outer end of the first companion tube, install the flexible connection component to be tested at the inner end of the first companion tube and the first end of the second companion tube, install the flexible connection component to be tested at the second end of the second companion tube and the inner end of the third companion tube, and connect the outer end of the third companion tube to the third end of the three-way adapter;

[0015] S2. Dynamic shear test: Start the pressurization module to inject pressure into the companion tube. When the internal pressure of the companion tube rises to 0.02 Mpa, record it as the moment of t = 0 ms, and continue to increase the internal pressure. When the internal pressure of the companion tube reaches the first pressure holding value, stop pressurization and continue to hold the pressure. At the same time, start the electric cylinder to apply a radial thrust to the companion tube. The flexible connection component is subjected to a shear load. When the shear load reaches the preset load value, the electric cylinder stops. After maintaining for a certain time, the electric cylinder works in the reverse direction, and the shear load decays back to zero. After the shear load drops to zero, close the pressurization module. When the internal pressure of the companion tube decays to the low-pressure value, complete a dynamic shear test of the flexible connection component;

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

[0017] S31. If the oil leakage amount of the flexible connection component < the leakage amount threshold, the damage degree of the flexible connection component is less than the damage threshold, and the internal pressure of the companion tube is within the specified theoretical value range, continue to increase the number of repetitions according to S2 for testing;

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

[0019] Preferably, it further includes S4. Analyze the service life and change law of the flexible connection component.

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

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

[0022] Preferably, in S2, the first pressure holding 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 internal pressure of the companion 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 the flexible connection component of the aircraft fuel system provided by the present invention drives the reciprocating motion of the side pipeline through the electric cylinder in the reciprocating component, thereby realizing the reciprocating motion of the companion test tube, and further 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, and the tests on two flexible connection components can be carried out simultaneously, improving the test efficiency.

[0025] (2) The dynamic shear test device for the flexible connection component of the aircraft fuel system provided by the present invention has a slider in the clamping component sliding in the rectangular chute 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 pipeline and the middle pipeline with different apertures, it can adapt to companion test tubes with different diameters to meet the test requirements of flexible connection components of different specifications.

[0026] (3) The dynamic shear test method for the flexible connection component provided by the present invention tests the internal working pressure and external shear load that the flexible connection component can withstand by pressurizing the inside of the companion test tube through the pressurization module and applying a radial thrust to the companion test tube by the electric cylinder, providing standard equipment and methods for carrying out the life test research of the flexible connection component, and can be widely applied in the aerospace field, having great application value. Description of the Drawings

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

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

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

[0030] Figure 4 is a schematic structural diagram of the clamping component of the dynamic shear test device for the flexible connection component of the aircraft fuel system of the present invention;

[0031] Figure 5 is a schematic structural diagram of the installation of the flexible connection component and the companion test tube of the dynamic shear test device for the flexible connection component of the aircraft fuel system of the present invention;

[0032] Figure 6 It is a schematic flow chart of the dynamic shear test method for the flexible connection component of the aircraft fuel system flexible connection component dynamic shear test device of the present invention.

[0033] Main reference numerals:

[0034] Reciprocating component 1, base 11, electric cylinder mounting seat 12, electric cylinder 13, first push block 14, second push block 15, external pressure sensor 16, clamping component 2, first clamping block 21, second clamping block 22, axial limiting block 23, lateral pipeline 24, sliding rod 25, slider 26, support plate 27, middle fixing plate 28, middle pipeline 29, loading component 3, pressurizing module 31, pressure transmission pipe 32, three-way adapter 33, internal pressure sensor 34, flexible connection component 4, first companion test tube 5, second companion test tube 6, third companion test tube 7. Specific embodiments

[0035] To elaborate on the technical content, achieved objectives and effects of the present invention, the following will be described in detail with reference to the accompanying drawings of the specification.

[0036] The aircraft fuel system flexible connection component dynamic shear test device, as Figure 1 and Figure 2 shown, 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 clamping block 21 in the clamping component 2. The loading component 3 is arranged on one side of the clamping component 1. The reciprocating component 1 applies a shear load to the flexible connection component 4, the clamping component 2 is responsible for clamping and fixing the companion test tube, and the loading component 3 injects pressure into the interior of the companion test tube.

[0037] The first clamping block 21, second clamping block 22, axial limiting block 23, lateral pipeline 24, sliding rod 25, and slider 26 in the reciprocating component 1 and the clamping component 2 are symmetrically arranged on both sides of the middle fixing plate 28. The loading component 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 received by the flexible connection component 4 in real time.

[0038] As Figure 3As shown in the figure, the reciprocating assembly 1 includes a base 11, an electric cylinder mounting seat 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 seat 12 is arranged at the first end of the base 11. The electric cylinder 13 is mounted on the electric cylinder mounting seat 12, and the output end of the electric cylinder 13 passes through the electric cylinder mounting seat 12. The first end of the first push block 14 is connected to the output shaft of the electric cylinder 13, and 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 received by the flexible connection assembly 4 in real time.

[0039] As Figure 4 shown in the figure, the clamping assembly 2 includes a first clamping block 21, a second clamping block 22, an axial limiting block 23, a lateral pipeline 24, a sliding rod 25, a sliding block 26, a support plate 27, a middle fixing plate 28, and a middle pipeline 29. The first clamping block 21 is docked with the second clamping block 22. The lateral pipeline 24 is installed in the circular hole formed by the docking of the first clamping block 21 and the second clamping block 22. The axial limiting blocks 23 are respectively arranged at the joints of the lateral pipeline 24 with the first clamping block 21 and the second clamping block 22. The axial limiting blocks 23 are used to limit the axial movement of the locked lateral pipeline 24 to ensure that the lateral pipeline 24 does not slip out of the first clamping block 21 and the second clamping block 22. The support plate 27 is arranged at the second end of the base 11. Rectangular sliding grooves are provided at the four corners of the support plate 27. The sliding block 26 is installed in the rectangular sliding groove, and the sliding block 26 can slide in the rectangular sliding groove. The sliding rod 25 sequentially passes through the slot holes at both ends of the first clamping block 21 and the second clamping block 22, and the two ends of the sliding rod 25 are respectively matched with the sliding blocks 26 installed on the support plate 27. The first clamping block 21 and the second clamping block 22 can move axially along the sliding rod 25. The center line of the output shaft of the electric cylinder 13 and the center line of the sliding rod 25 are in a parallel positional relationship in space to ensure that the thrust of the electric cylinder 13 acts entirely on the lateral pipeline 24. The middle fixing plate 28 is arranged at the middle position between the two support plates 27. The middle pipeline 29 is installed in the circular hole in the middle of the middle fixing plate 28. The axial limiting block 23 is arranged at the joint of the middle fixing plate 28 and the middle pipeline 29. The axial limiting block 23 is used to limit the axial movement of the middle pipeline 29. The center line of the middle circular hole of the lateral pipeline 24 and the center line of the middle circular hole of the middle pipeline 29 are collinear 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] As Figure 6 shown in the figure, the test method of a dynamic shear test device for a flexible connection assembly of an aircraft fuel system according to the present invention is further described, which includes the following steps:

[0041] S1. Set up the test device: Install the first auxiliary test tube 5 and the third auxiliary test tube 7 respectively in the middle of two lateral pipelines 24, install the second auxiliary test tube 6 in the middle of the middle pipeline 29, install a plug at the outer end of the first auxiliary test tube 5, install the flexible connection component 4 to be tested at the inner end of the first auxiliary test tube 5 and the first end of the second auxiliary test tube 7, install the flexible connection component 4 to be tested at the second end of the second auxiliary test tube 6 and the inner end of the third auxiliary test tube 7, connect the outer end of the third auxiliary test tube 7 to the third end of the three-way adapter 33. This dynamic shear test device can install two flexible connection components 4 to be tested at one time for testing. As shown in Figure 5 After completion of the installation, wipe the area around the flexible connection component 4 to be tested with a dry paper.

[0042] S2. Dynamic shear test: Start the pressurization module 31 to inject pressure into the auxiliary test tube. When the internal pressure rises to 0.02 Mpa, record it as the moment of t = 0 ms, and continue to increase the internal pressure. When the internal pressure of the auxiliary test tube reaches the first pressure holding value, stop pressurization and maintain the pressure. At the same time, start the electric cylinder 13 to apply a radial thrust to the auxiliary test tube. The flexible connection component 4 is subjected to a shear load. When the shear load reaches the maximum shear load value, that is, the preset load value, stop the electric cylinder 13. After maintaining for a certain time, such as 100 ms, the electric cylinder 13 works in the reverse direction, and the shear load gradually decays back to zero. After the shear load drops to zero, close the pressurization module 31, and the internal pressure of the auxiliary test tube gradually decays to a low pressure value. This is a dynamic shear test of the flexible connection component 4. In a specific embodiment, the first pressure holding 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 internal pressure of the auxiliary 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 fails. The test cycle rate shall not exceed 40 times per minute. In a specific embodiment, N is set to 500 times.

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

[0045] S32. If the oil leakage amount of the flexible connection component 4 > the leakage amount threshold, or the damage degree of the flexible connection component 4 is greater than the damage threshold, or the internal pressure of the auxiliary test tube exceeds the specified theoretical value range, it indicates that the flexible connection component 4 fails and the test terminates.

[0046] S4. Analyze the service life and change law of the flexible connection component 4.

[0047] Further, in S2, when the shear load of the flexible connection component 4 is applied from zero to the maximum, it must be completed within the range of 1000 - 2000 ms.

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

[0049] The following further describes a dynamic shear test device for a flexible connection component of an aircraft fuel system according to the present invention in conjunction with embodiments. The specific use process of the dynamic shear test device for the flexible connection component of the aircraft fuel system of the present invention is as follows:

[0050] First, install the first companion test tube 5 and the third companion test tube 7 between two lateral pipelines 24 respectively, install the second companion test tube 6 in the middle of the middle pipeline 29, adjust the distance between the lateral pipeline 24 and the middle fixing plate 28 by moving the position of the slider 26 in the rectangular chute of the support plate 27, install a plug at the outer end of the first companion test tube 5, connect the inner end of the first companion test tube 5 and the first end of the second companion test tube 7 through the flexible connection component 4 to be tested, connect the second end of the second companion test tube 6 and the inner end of the third companion test tube 7 through the flexible connection component 4 to be tested, connect the outer end of the third companion test tube 7 to the third end of the three-way adapter 33, and lock the slider 2 to the support plate 27.

[0051] Then, start the pressurization module 31. The pressure enters the interior of the companion test tube through the pressure transmission pipe 32 and the three-way adapter 33. The internal pressure sensor 34 detects the internal pressure received by the flexible connection component 4 in real time and feeds it back to the computer. When the pressure reaches the set value, start the electric cylinder 13. 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 clamping block 21 and the second clamping block 22 to move axially along the slide rod 25. The external pressure sensor 16 detects the thrust in real time and feeds it back to the computer. The first companion test tube 5 and the third companion test tube 7 are both misaligned with the second companion test tube 6, and the flexible connection component 4 is subjected to a shear load.

[0052] Next, when the shear load reaches the set value, the electric cylinder 13 works in the reverse direction. The output end of the electric cylinder 13 drives the first push block 14 to move backward. The first companion test tube 5 and the third companion test tube 7 gradually return to their original positions, and the shear load received by the flexible connection component 4 gradually decays back to zero; after the shear load drops to zero, turn off the pressurization module 31, and the internal pressure of the companion test tube also gradually decays to zero. Thus, a complete dynamic shear test of the flexible connection component 4 is ended.

[0053] Finally, repeat the number of tests according to the above process until the required number of tests is completed.

[0054] The embodiments described above are only descriptions of the preferred embodiments of the present invention, and do not limit the scope of the present invention. Without departing from the spirit of the present invention's design, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. A dynamic shear test device for flexible connection components of an aircraft fuel system, characterized in that: It comprises a reciprocating assembly, a clamping assembly and a loading assembly, wherein the second push block in the reciprocating assembly is connected to the first clamping block in the clamping assembly, and the loading assembly is arranged on one side of the clamping assembly; The reciprocating assembly comprises a base, an electric cylinder mounting seat, an electric cylinder, a first push block, a second push block and an external pressure sensor, wherein the electric cylinder mounting seat is arranged at a first end of the base, the electric cylinder is mounted on the electric cylinder mounting seat, and the output end of the electric cylinder passes through the electric cylinder mounting seat, 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 comprises a first clamping block, a second clamping block, an axial limit block, a lateral pipeline, a sliding rod, a sliding block, a support plate, a middle fixed plate and a middle pipeline, the first clamping block is docked with the second clamping block, the lateral pipeline is installed in a circular hole formed by the docking of the first clamping block and the second clamping block, the support plate is arranged on the second end of the base, the four corners of the support plate are respectively provided with rectangular slide grooves, the slide block is installed in the rectangular slide groove and can slide in the rectangular slide groove, the sliding rod passes through the slot holes at both ends of the first clamping block and the second clamping block in sequence, and the two ends of the sliding rod are respectively matched with the slide blocks installed on the support plate, the middle fixed plate is arranged in the middle position of the two support plates, the middle pipeline is installed in the circular hole in the middle of the middle fixed plate, and the axial limit blocks are respectively provided at the connection between the lateral pipeline and the first clamping block and the second clamping block and at the connection between the middle fixed plate and the middle pipeline.

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

3. The dynamic shear test device for flexible connection components of an aircraft fuel system according to claim 1, characterized in that: The center line of the output shaft of the electric cylinder and the center line of the sliding rod are parallel to each other in space.

4. The dynamic shear test device for flexible connection components of an aircraft fuel system according to claim 1, characterized in that: The first clamping block, the second clamping block, the axial limit block, the lateral pipeline, the sliding rod and the sliding block in the reciprocating assembly and the clamping assembly are symmetrically arranged on both sides of the middle fixing plate.

5. The dynamic shear test device for flexible connection components of an aircraft fuel system according to claim 1, characterized in that: The center line of the middle circular hole of the lateral pipeline is collinear with the center line of the middle circular hole of the middle pipeline.

6. A method for testing a dynamic shear test device for a flexible connection assembly of an aircraft fuel system according to any one of claims 1 to 5, characterized in that: It includes the following steps: S1. Build a test device: install the first accompanying test tube and the third accompanying test tube in the middle of the two lateral pipelines respectively, install the second accompanying test tube in the middle of the middle pipeline, install a plug on the outer end of the first accompanying test tube, install the flexible connection component to be tested on the inner end of the first accompanying test tube and the first end of the second accompanying test tube, install the flexible connection component to be tested on the second end of the second accompanying test tube and the inner end of the third accompanying test tube, and connect the outer end of the third accompanying test tube to the third end of the three-way adapter; S2, dynamic shear test: start the pressurizing module to inject pressure into the accompanying test tube. When the internal pressure of the accompanying test tube rises to 0.02Mpa, it is recorded as t=0ms, and the internal pressure continues to increase. When the internal pressure of the accompanying test tube reaches the first pressure-maintaining value, the pressurizing is stopped and the pressure is maintained continuously. At the same time, the electric cylinder is started to apply radial thrust to the accompanying test tube, and the flexible connection component is subjected to shear load. When the shear load reaches the preset load value, the electric cylinder stops. After maintaining for a certain period, the electric cylinder works in the reverse direction, and the shear load decays back to zero. After the shear load drops to zero, the pressurizing module is closed. When the internal pressure of the accompanying test tube decays to the low pressure value, a dynamic shear test of the flexible connection component is completed; S3, repeat the dynamic shear test in S2, and after every N test cycles, check the flexible connection component to determine whether the flexible connection component fails, specifically: S31. If the oil leakage of the flexible connection component is less than the leakage threshold, the damage degree of the flexible connection component is less than the damage threshold, and the internal pressure of the test tube is within the prescribed theoretical value range, continue to increase the number of repetitions according to S2 for testing; S32. If the oil leakage of the flexible connection component is greater than the leakage threshold, or the damage degree of the flexible connection component is greater than the damage threshold, or the internal pressure of the test tube exceeds the prescribed theoretical value range, the flexible connection component fails and the test is terminated.

7. The test method of the dynamic shear test device for the flexible connection assembly of an aircraft fuel system according to claim 6, characterized in that: It also includes S4, analyzing the service life and change patterns of flexible connection components.

8. The test method of the dynamic shear test device for the flexible connection assembly of an aircraft fuel system according to claim 6, characterized in that: In S2, the time range for the shear load of the flexible connection component to be applied from zero to a preset load value is 1000 to 2000 ms; when the shear load of the flexible connection component is the preset load value and is maintained for 100 ms, the internal pressure of the test tube is within the range of 0.86 to 0.9 MPa.

9. The test method of the dynamic shear test device for the flexible connection assembly of an aircraft fuel system according to claim 6, characterized in that: The test cycle rate in S3 is less than or equal to 40 times / minute.

10. The test method of the dynamic shear test device for the flexible connection assembly of an aircraft fuel system according to claim 6, characterized in that: In S2, the first pressure holding 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 internal pressure of the test tube decays is 0.03 (+0.01 / -0.02) MPa.

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