Arresting hook impact load measuring method and device based on strain method

Abstract

The invention belongs to the technical field of aviation arresting hook drop test, and relates to an arresting hook impact load measurement method and device based on a strain method, and the method comprises the steps: S1, obtaining three strain values fed back by strain gauges disposed at three positions of an arresting hook; s2, acquiring slopes of the three calibrated strain gauges in all directions, wherein the slopes refer to ratios of strain values to loads; and S3, calculating the component load in each direction based on the strain value and the slope. The impact load generated by the arresting hook contact table in the arresting hook drop test can be more accurately obtained, the magnitude and direction of the impact load of the arresting hook contact table can be truly reflected, and the impact load is not influenced by platform movement.

Description

Technical Field

[0001] The present application belongs to the technical field of aviation arresting hook drop shock test, and in particular, relates to an arresting hook impact load measurement method and device based on a strain method. Background Art

[0002] In the arresting hook drop shock test, a moving table is often used to simulate the relative movement between the arresting hook and the table in the heading direction, so it is impossible to measure the impact load between the arresting hook and the table by installing a load measuring device on the table. The commonly used load measuring method for the current domestic arresting hook drop shock test is to install a force sensor between the arresting hook installation point and the fixture to measure the three-dimensional load at each installation point. However, due to the rapid attenuation of the impact load transmission, the impact load measured by the force sensor has been seriously distorted. Summary of the invention

[0003] In order to solve the above problems, the present application provides a method and device for measuring the impact load of an arresting hook based on the strain method to solve the problem that the impact load cannot be directly measured.

[0004] The first aspect of the present application provides a method for measuring the impact load of an arresting hook based on a strain method, which mainly includes:

[0005] Step S1, obtaining three strain values ​​fed back by strain gauges arranged at three positions on the arresting hook;

[0006] Step S2, obtaining the slopes of the three calibrated strain gauges in various directions, where the slope refers to the ratio of the strain value to the load;

[0007] Step S3: Calculate the component loads in each direction based on the strain value and the slope.

[0008] Preferably, in step S1, three strain values ​​are obtained by sticking strain gauges on the hook rod of the arresting hook close to the hook head at three different cross-sectional positions along the axial direction of the hook rod.

[0009] Preferably, in step S1, at each cross section, two strain gauges are symmetrically pasted in the axial direction of the hook rod, and the strain average of the two strain gauges is used as the strain value at the cross section position.

[0010] Preferably, step S2 further comprises:

[0011] After fixing one end of the arresting hook connected to the aircraft, apply tension along the axial direction of the arresting hook at the hook head, and calibrate the slope of each strain gauge along the heading direction according to the strain gauge strain amount;

[0012] After fixing the end of the arresting hook connected to the aircraft and the hook head away from the aircraft, apply an upward pulling force perpendicular to the axis of the arresting hook at the hook head, and calibrate the slope of each strain gauge along the vertical direction according to the strain amount of the strain gauge;

[0013] After fixing one end of the arresting hook connected to the aircraft and the hook head away from the aircraft, a lateral pulling force is applied to the hook head perpendicular to the axis of the arresting hook, and the slope of each strain gauge along the lateral direction is calibrated according to the strain amount of the strain gauge.

[0014] Preferably, in step S3, the component loads in each direction are calculated by the following formula:

[0015]

[0016] Among them, F x 、F y 、F z are the component loads along the heading direction, lateral direction, and vertical direction, ε1, ε2, and ε3 are the three strain values ​​fed back by the strain gauge, i x 、i y 、i z are the slopes of the i-th strain gauge along the heading direction, lateral direction, and vertical direction, respectively, j x 、j y 、j z are the slopes of the jth strain gauge along the heading direction, lateral direction, and vertical direction, respectively, k x , k y , k z are the slopes of the kth strain gauge along the heading direction, lateral direction, and vertical direction, respectively.

[0017] The second aspect of the present application provides a device for measuring the impact load of an arresting hook based on a strain method, which mainly includes:

[0018] A strain value acquisition module, used to acquire three strain values ​​fed back by strain gauges arranged at three positions on the arresting hook;

[0019] A ratio acquisition module, used to acquire the slopes of the three calibrated strain gauges in various directions, where the slope refers to the ratio of the strain value to the load;

[0020] The component load calculation module is used to calculate the component loads in each direction based on the strain value and slope.

[0021] Preferably, three strain values ​​are obtained by sticking strain gauges on the hook rod of the arresting hook close to the hook head at three different cross-sectional positions along the axial direction of the hook rod.

[0022] Preferably, at each cross section, two strain gauges are symmetrically adhered up and down along the axial direction of the hook rod, and the strain average of the two strain gauges is used as the strain value at the cross section position.

[0023] Preferably, the ratio acquisition module includes:

[0024] The heading direction slope calibration unit is used to fix one end of the arresting hook connected to the aircraft, apply tension along the axial direction of the arresting hook at the hook head, and calibrate the slope of each strain gauge along the heading direction according to the strain amount of the strain gauge;

[0025] The vertical direction slope calibration unit is used to fix the end of the arresting hook connected to the aircraft and the hook head away from the aircraft, and then apply an upward pulling force perpendicular to the axis of the arresting hook at the hook head, and calibrate the slope of each strain gauge in the vertical direction according to the strain amount of the strain gauge;

[0026] The lateral slope calibration unit is used to fix one end of the arresting hook connected to the aircraft and the hook head away from the aircraft, and then apply a lateral pulling force perpendicular to the axis of the arresting hook at the hook head, and calibrate the slope of each strain gauge along the lateral direction according to the strain amount of the strain gauge.

[0027] Preferably, in the component load calculation module, the component loads in each direction are calculated by the following formula:

[0028]

[0029] Among them, F x 、F y 、F z are the component loads along the heading direction, lateral direction, and vertical direction, ε1, ε2, and ε3 are the three strain values ​​fed back by the strain gauge, i x 、i y 、i z are the slopes of the i-th strain gauge along the heading direction, lateral direction, and vertical direction, respectively, j x 、j y 、j z are the slopes of the jth strain gauge along the heading direction, lateral direction, and vertical direction, respectively, k x , k y , k z are the slopes of the kth strain gauge along the heading direction, lateral direction, and vertical direction, respectively.

[0030] A third aspect of the present application provides a computer device, comprising a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the arresting hook impact load measurement method based on the strain method as described above.

[0031] A fourth aspect of the present application provides a readable storage medium storing a computer program, wherein the computer program, when executed by a processor, is used to implement the arresting hook impact load measurement method based on the strain method as described above.

[0032] The present application can more accurately obtain the impact load generated by the arresting hook contacting the platform in the arresting hook drop shock test, can truly reflect the size and direction of the impact load of the arresting hook contacting the platform, and is not affected by the movement of the platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a flow chart of a preferred embodiment of the method for measuring the impact load of an arresting hook based on the strain method of the present application.

[0034] Figure 2 This is a schematic diagram of the arresting hook structure.

[0035] Figure 3 This is a schematic diagram of the arresting hook sticking strain gauge.

[0036] Figure 4 It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application.

[0037] Among them, 1-hook head, 2-hook rod, 3-hook arm, 4-table, 5-installation point, 6-arresting hook coordinate system. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0039] The first aspect of the present application provides a method for measuring the impact load of an arresting hook based on a strain method, such as Figure 1 As shown, it mainly includes:

[0040] Step S1, obtaining three strain values ​​fed back by strain gauges arranged at three positions on the arresting hook;

[0041] Step S2, obtaining the slopes of the three calibrated strain gauges in various directions, where the slope refers to the ratio of the strain value to the load;

[0042] Step S3: Calculate the component loads in each direction based on the strain value and the slope.

[0043] refer to Figure 2The arresting hook of the present application includes a hook head 1, a hook rod 2 and a hook arm 3. The load size calculation of the impact load generated between the hook head 1 and the table 4 is the invention purpose of the present application. The calculated load size can be used to verify whether the design of the arresting hook is reasonable, or to guide the design of the arresting hook or the design of the flight load. The end of the hook arm 3 is connected to the aircraft through the installation point 5. Figure 2 In the present application, an arresting hook coordinate system 6 is constructed, wherein the x-axis extends along the axial direction of the arresting hook, the z-axis is perpendicular to the x-axis and extends upward, and the y-axis extends laterally.

[0044] The present application utilizes the impact load generated between the hook head 1 and the table surface 4 during a drop test of the arresting hook, and in the process of being uploaded to the installation point 5 through the arresting hook hook rod 2 and hook arm 3, the various components will be loaded and the material will undergo local micro-deformation. By performing strain measurement on the main load-transmitting section, according to the principles of structural mechanics, the size of the impact load is inferred from the strain measurement data, thereby solving the problem that the impact load cannot be directly measured.

[0045] In some optional embodiments, in step S1, three strain values ​​are obtained by sticking strain gauges on the hook rod 2 of the arresting hook close to the hook head 1 at three different cross-sectional positions along the axial direction of the hook rod 2.

[0046] In this embodiment, the impact load of the arresting hook contact platform is transmitted through the hook head 1, the hook rod 2 and the hook arm 3. Since the impact load decays quickly during the transmission process and is affected by the assembly gap and stiffness mutation in the connection area of ​​the hook rod 2 and the hook arm 3, the impact load will suddenly change. Therefore, the impact load measurement sensitive section should be selected in the hook rod 2. At least three sections are selected here, such as Figure 3 As shown in the AA section, BB section and CC section.

[0047] In some optional implementations, in step S1, at each cross section, two strain gauges are symmetrically pasted up and down along the axial direction of the hook rod 2, and the strain average of the two strain gauges is used as the strain value at the cross section position.

[0048] In this embodiment, the arresting hook is a single force transmission structure, and the strain direction of the measuring part is mainly along the axial direction of the hook rod 2. A single strain gauge is used for measurement, and it is symmetrically pasted along the AA section, BB section and CC section. The direction of the strain gauge is arranged along the axial direction of the hook rod 2. After pasting two strains on any section, the average strain value of the two strain gauges can be used as the strain value of the section.

[0049] In some optional implementations, step S2 further includes:

[0050] After fixing one end of the arresting hook connected to the aircraft, apply tension along the axial direction of the arresting hook at the hook head 1, and calibrate the slope of each strain gauge along the heading direction according to the strain gauge strain amount;

[0051] After fixing one end of the arresting hook connected to the aircraft and the hook head 1 away from the aircraft, apply an upward pulling force perpendicular to the axis of the arresting hook at the hook head 1, and calibrate the slope of each strain gauge along the vertical direction according to the strain amount of the strain gauge;

[0052] After fixing one end of the arresting hook connected to the aircraft and the hook head 1 away from the aircraft, a lateral pulling force is applied to the hook head 1 perpendicular to the axis of the arresting hook, and the slope of each strain gauge along the lateral direction is calibrated according to the strain amount of the strain gauge.

[0053] Step S2 is used to obtain the corresponding relationship between the input load and strain of each strain gauge in each direction through a load calibration test. By attaching strain gauges to the main force transmission section of the arresting hook for loading measurement, a quantitative conversion relationship between the input load and the strain value is established. The impact load can be decomposed into two components, the heading load and the vertical load, in the arresting hook coordinate system 6. According to this load characteristic, the heading load and the vertical load are applied to the arresting hook respectively. According to the load calibration test results, the relationship between the input load and the strain of each strain gauge in each direction is obtained, that is, the slope of the input load and strain curve. For example, the slopes of the i-th strain gauge in the three load directions are i and i respectively. x 、i y 、i z ,but:

[0054] i x =a x / b x ;i y =a y / b y ;i z =a z / b z .

[0055] Among them, a x 、a y 、a z are the strain values ​​after applying loads along the three axes of the arresting hook coordinate system 6, b x 、b y 、b z are the corresponding loads respectively. In the case of no lateral load, i y =0.

[0056] In some optional implementations, in step S3, the component loads in each direction are calculated by the following formula:

[0057]

[0058] Among them, F x 、F y 、F zare the component loads along the heading direction, lateral direction, and vertical direction, ε1, ε2, and ε3 are the three strain values ​​fed back by the strain gauge, i x 、i y 、i z are the slopes of the i-th strain gauge along the heading direction, lateral direction, and vertical direction, respectively, j x 、j y 、j z are the slopes of the jth strain gauge along the heading direction, lateral direction, and vertical direction, respectively, k x , k y , k z are the slopes of the kth strain gauge along the heading direction, lateral direction, and vertical direction, respectively.

[0059] In this embodiment, a certain input load can be decomposed into three directional component loads F in the arresting hook coordinate system 6: x 、F y 、F z , arbitrarily select three strain gauges, whose strains are ε1, ε2, and ε3 respectively, thus, the following equation can be established:

[0060]

[0061] After the equation is expanded, the calculation formula for each component load in step S3 can be obtained.

[0062] The application method is simple and easy to implement, can truly reflect the size and direction of the impact load of the upper arresting hook touching the platform, is not affected by the movement of the platform, and has strong practicality.

[0063] The second aspect of the present application provides a device for measuring the impact load of an arresting hook based on a strain method corresponding to the above method, mainly comprising:

[0064] A strain value acquisition module, used to acquire three strain values ​​fed back by strain gauges arranged at three positions on the arresting hook;

[0065] A ratio acquisition module, used to acquire the slopes of the three calibrated strain gauges in various directions, where the slope refers to the ratio of the strain value to the load;

[0066] The component load calculation module is used to calculate the component loads in each direction based on the strain value and slope.

[0067] In some optional embodiments, three strain values ​​are obtained by sticking strain gauges on the hook rod 2 of the arresting hook near the hook head 1 at three different cross-sectional positions along the axial direction of the hook rod 2.

[0068] In some optional embodiments, at each cross section, two strain gauges are symmetrically adhered up and down along the axial direction of the hook rod 2, and the strain average of the two strain gauges is used as the strain value at the cross section position.

[0069] In some optional implementations, the ratio acquisition module includes:

[0070] The heading direction slope calibration unit is used to apply tension along the axial direction of the arresting hook at the hook head 1 after fixing one end of the arresting hook connected to the aircraft, and calibrate the slope of each strain gauge along the heading direction according to the strain amount of the strain gauge;

[0071] The vertical direction slope calibration unit is used to fix one end of the arresting hook connected to the aircraft and the hook head 1 away from the aircraft, and then apply an upward pulling force perpendicular to the axis of the arresting hook at the hook head 1, and calibrate the slope of each strain gauge in the vertical direction according to the strain amount of the strain gauge;

[0072] The lateral slope calibration unit is used to fix one end of the arresting hook connected to the aircraft and the hook head 1 away from the aircraft, and then apply a lateral pulling force perpendicular to the axis of the arresting hook at the hook head 1, and calibrate the slope of each strain gauge along the lateral direction according to the strain amount of the strain gauge.

[0073] In some optional implementations, in the component load calculation module, the component loads in each direction are calculated by the following formula:

[0074]

[0075] Among them, F x 、F y 、F z are the component loads along the heading direction, lateral direction, and vertical direction, ε1, ε2, and ε3 are the three strain values ​​fed back by the strain gauge, i x 、i y 、i z are the slopes of the i-th strain gauge along the heading direction, lateral direction, and vertical direction, respectively, j x 、j y 、j z are the slopes of the jth strain gauge along the heading direction, lateral direction, and vertical direction, respectively, k x , k y , k z are the slopes of the kth strain gauge along the heading direction, lateral direction, and vertical direction, respectively.

[0076] In a third aspect of the present application, a computer device includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement a method for measuring the impact load of an arresting hook based on a strain method.

[0077] In a fourth aspect of the present application, a readable storage medium stores a computer program, and when the computer program is executed by a processor, it is used to implement the arresting hook impact load measurement method based on the strain method as described above. The computer readable storage medium may be included in the device described in the above embodiment; or it may exist independently without being assembled into the device. The above computer readable storage medium carries one or more programs, and when the above one or more programs are executed by the device, the data is processed according to the above method.

[0078] Reference below Figure 4 , which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 4 The computer device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0079] like Figure 4 As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage part 408 into a random access memory (RAM) 403. In the RAM 403, various programs and data required for the operation of the device 400 are also stored. The CPU 401, the ROM 402, and the RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0080] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, etc.; an output section 407 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, a modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as needed. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.

[0081] In particular, according to the embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the method of the present application are executed. It should be noted that the computer storage medium of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, - but not limited to - a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection with one or more conductors, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, an apparatus or a device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, an apparatus or a device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0082] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0083] The modules or units involved in the embodiments described in this application may be implemented by software or hardware. The modules or units described may also be set in a processor, and the names of these modules or units do not constitute limitations on the modules or units themselves in some cases.

[0084] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for measuring the impact load of an arresting hook based on a strain method, characterized in that: include: Step S1, obtaining three strain values ​​fed back by strain gauges arranged at three positions on the arresting hook; Step S2, obtaining the slopes of the three calibrated strain gauges in various directions, where the slope refers to the ratio of the strain value to the load; Step S3: Calculate the component loads in each direction based on the strain value and the slope.

2. The method for measuring the impact load of an arresting hook based on the strain method according to claim 1, characterized in that: In step S1, three strain values ​​are obtained by sticking strain gauges on the hook rod (2) close to the hook head (1) of the arresting hook at three different cross-sectional positions along the axial direction of the hook rod (2).

3. The method for measuring the impact load of an arresting hook based on the strain method according to claim 2, characterized in that: In step S1, at each cross section, two strain gauges are symmetrically pasted in the vertical direction along the axial direction of the hook rod (2), and the strain average of the two strain gauges is used as the strain value at the cross section position.

4. The method for measuring the impact load of an arresting hook based on the strain method according to claim 1, characterized in that: Step S2 further comprises: After one end of the arresting hook connected to the aircraft is fixed, a tensile force is applied along the axial direction of the arresting hook at the hook head (1), and the slope of each strain gauge along the heading direction is calibrated according to the strain amount of the strain gauge; After fixing one end of the arresting hook connected to the aircraft and the hook head (1) away from the aircraft, an upward pulling force is applied to the hook head (1) in a direction perpendicular to the axis of the arresting hook, and the slope of each strain gauge in the vertical direction is calibrated according to the strain amount of the strain gauge; After fixing one end of the arresting hook connected to the aircraft and the hook head (1) away from the aircraft, a lateral pulling force is applied to the hook head (1) in a direction perpendicular to the axis of the arresting hook, and the slope of each strain gauge along the lateral direction is calibrated according to the strain amount of the strain gauge.

5. The method for measuring the impact load of an arresting hook based on the strain method according to claim 1, characterized in that: In step S3, the component loads in each direction are calculated by the following formula: Among them, F x 、F y 、F z are the component loads along the heading direction, lateral direction, and vertical direction, ε1, ε2, and ε3 are the three strain values ​​fed back by the strain gauge, i x 、i y 、i z are the slopes of the i-th strain gauge along the heading direction, lateral direction, and vertical direction, respectively, j x 、j y 、j z are the slopes of the jth strain gauge along the heading direction, lateral direction, and vertical direction, respectively, k x , k y , k z are the slopes of the kth strain gauge along the heading direction, lateral direction, and vertical direction, respectively.

6. A device for measuring the impact load of an arresting hook based on a strain method, characterized in that: include: A strain value acquisition module, used to acquire three strain values ​​fed back by strain gauges arranged at three positions on the arresting hook; A ratio acquisition module, used to acquire the slopes of the three calibrated strain gauges in various directions, where the slope refers to the ratio of the strain value to the load; The component load calculation module is used to calculate the component loads in each direction based on the strain value and slope.

7. The arresting hook impact load measuring device based on the strain method according to claim 6, characterized in that: Three strain values ​​are obtained by sticking strain gauges on a hook rod (2) close to a hook head (1) of the arresting hook at three different cross-sectional positions along the axial direction of the hook rod (2).

8. The arresting hook impact load measuring device based on the strain method according to claim 7, characterized in that: At each cross section, two strain gauges are symmetrically pasted up and down along the axial direction of the hook rod (2), and the strain average of the two strain gauges is used as the strain value at the cross section position.

9. The arresting hook impact load measuring device based on the strain method according to claim 6, characterized in that: The ratio acquisition module comprises: The heading direction slope calibration unit is used to apply a tensile force along the axial direction of the arresting hook at the hook head (1) after fixing one end of the arresting hook connected to the aircraft, and calibrate the slope of each strain gauge along the heading direction according to the strain amount of the strain gauge; A vertical direction slope calibration unit is used to fix one end of the arresting hook connected to the aircraft and a hook head (1) away from the aircraft, and then apply an upward pulling force perpendicular to the axis of the arresting hook at the hook head (1), and calibrate the slope of each strain gauge along the vertical direction according to the strain amount of the strain gauge; The lateral direction slope calibration unit is used to fix one end of the arresting hook connected to the aircraft and the hook head (1) away from the aircraft, and then apply a lateral pulling force perpendicular to the axis of the arresting hook at the hook head (1), and calibrate the slope of each strain gauge along the lateral direction according to the strain amount of the strain gauge.

10. The arresting hook impact load measuring device based on the strain method according to claim 6, characterized in that: In the component load calculation module, the component loads in each direction are calculated by the following formula: Among them, F x 、F y 、F z are the component loads along the heading direction, lateral direction, and vertical direction, ε1, ε2, and ε3 are the three strain values ​​fed back by the strain gauge, i x 、i y 、i z are the slopes of the i-th strain gauge along the heading direction, lateral direction, and vertical direction, respectively, j x 、j y 、j z are the slopes of the jth strain gauge along the heading direction, lateral direction, and vertical direction, respectively, k x , k y , k z are the slopes of the kth strain gauge along the heading direction, lateral direction, and vertical direction, respectively.

11. A computer device, characterized in that: The method comprises a processor, a memory and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for measuring the impact load of an arresting hook based on the strain method as described in any one of claims 1 to 5.

12. A readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is used to implement the arresting hook impact load measurement method based on the strain method as described in any one of claims 1 to 5.

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