Aviation equipment measuring tool digital calibration system and method based on strain effect

Abstract

The invention provides an aviation equipment measuring tool digital calibration system and method based on a strain effect. The aviation equipment measuring tool digital calibration system comprises a control subsystem and a sensing analysis subsystem. The sensing analysis subsystem collects calibration data of the aviation product measuring tool to be calibrated through a strain gauge sensor 1, and after data processing and analysis are conducted, the calibration data are compared with standard data to obtain a verification result and display the verification result. And the control subsystem is used for setting the types of the calibrated aviation products and cooperating with the sensing analysis subsystem to complete calibration work. According to the invention, the digital calibration of most aviation product measuring tools can be realized, the calibration accuracy and efficiency are improved, the dependence on the skills of operators is reduced, and errors in the calibration process are reduced. In addition, the method can also realize long-term monitoring of the aviation product measuring tool, and timely discover and correct tiny changes in the use process, thereby ensuring the safety and reliability of aviation equipment.

Description

Technical Field

[0001] This invention belongs to the field of calibration technology for aviation product measurement tools, and relates to a digital calibration system and method for aviation equipment measurement tools based on strain effect. Background Technology

[0002] Ensuring accuracy is paramount in the testing of aerospace products. This necessitates the use of various aerospace measuring tools, primarily designed for testing high-hardness materials like aerospace aluminum alloys and steels. However, the inherent properties of these materials inevitably cause wear and tear on these measuring tools during testing. When the accumulated wear exceeds a certain threshold, the measuring tools will fail. Unfortunately, in routine testing, the calibration and verification of these measuring tools before use is often neglected, leading to low reliability and an inability to guarantee their compliance.

[0003] Currently, the calibration of measuring tools for aerospace products is typically performed annually or at longer intervals, requiring the tools to be sent to metrology departments for calibration. Furthermore, calibration methods largely rely on mechanical manual operation and visual inspection, which is highly dependent on the operator's condition. Simultaneously, the equipment used for calibrating aerospace measuring tools is itself difficult to guarantee in perfect condition, easily leading to the accumulation of errors during calibration, resulting in low reliability and accuracy.

[0004] Current calibration methods are not only time-consuming but also costly, which is clearly unsuitable for the rapid response and maintenance cycle requirements of aviation equipment. Furthermore, due to the long calibration cycle, minor changes that may occur during the use of aviation product measuring tools cannot be detected and corrected in a timely manner, potentially posing a threat to the safety of aviation equipment. Therefore, developing a digital method capable of real-time monitoring and calibration is particularly important. This new method needs to provide rapid and accurate calibration results, reduce human error, improve the efficiency and reliability of aviation product measuring tools, and thus ensure the quality of aviation equipment testing. Summary of the Invention

[0005] In view of this, the present invention provides a digital calibration system and method for aerospace equipment measuring tools based on strain effects. Utilizing strain effects as the fundamental method, this system uses strain sensors to detect strain changes generated by aerospace product measuring tools during use, thereby calibrating the measuring tools during the aerospace equipment manufacturing process. Advanced digital processing technology converts these strain signals into readable digital signals, enabling real-time calibration of the aerospace product measuring tools. This invention can achieve digital calibration of most aerospace product measuring tools, not only improving calibration accuracy and efficiency but also reducing reliance on operator skills and minimizing errors during the calibration process. Furthermore, this method enables long-term monitoring of aerospace product measuring tools, allowing for timely detection and correction of minor changes during use, thus ensuring the safety and reliability of aerospace equipment.

[0006] The technical solution adopted in this invention is as follows:

[0007] To achieve the above objectives, the present invention provides the following technical solution:

[0008] A digital calibration system for aerospace equipment measurement tools based on strain effect includes a control subsystem and a sensing and analysis subsystem. The sensing and analysis subsystem collects calibration data of the aerospace product measurement tools to be calibrated through strain gauge sensor 1, processes and analyzes the data, compares it with standard data to obtain the verification result and displays it. The control subsystem is used to set the type of aerospace product to be calibrated and works with the sensing and analysis subsystem to complete the calibration work.

[0009] The sensing and analysis subsystem includes a strain gauge sensor 1, a data acquisition module 2, a strain signal conditioning module 3, an embedded strain testing module 4, a microcontroller 8, a controller 10, a host computer 12, an automatic recording and analysis component 19, and an automatic diagnostic component 20. Strain gauge sensor 1 is positioned at the working end of the aerospace product measurement tool to be calibrated. Based on the piezoresistive effect of the metal strain gauge, it detects the working end of the tool and generates a voltage signal, which is sent to data acquisition module 2. Data acquisition module 2 collects various data during the calibration process, including but not limited to sensor measurement data, instrument status information, and environmental parameters. It then transmits the collected data to strain signal conditioning module 3. Strain signal conditioning module 3 performs preliminary processing and optimization of the data, converting the analog signal into a digital voltage signal before sending it to embedded strain testing module 4. Embedded strain testing module 4 accurately measures the strain experienced by the aerospace product measurement tool under various operating conditions. Through a built-in high-precision strain sensor, it converts mechanical strain into an electrical signal and analyzes and tests the signal to ensure that the data meets specific testing requirements, providing an accurate data foundation for subsequent analysis and calibration. Microcontroller 8 is associated with the input command device 17 in the control subsystem to set the type of aerospace product measurement tool to be calibrated. Microcontroller 8 is equipped with… The system comprises a standard data source, a calibration process control system, and a data processing system. Based on the type of aerospace product measurement tool being measured, the system selects the calibration process and the standard data source. On one hand, it generates calibration process control commands and sends them to the controller 10. On the other hand, it receives data from the strain test module 4, processes it into electrical signals through the data processing system, and compares them with the standard data signals 6 in the standard data source to obtain calibration results or conclusions. The microcontroller 8 sends the processed data to the host computer 12 and the automatic recording component 19. The host computer 12 receives the processed data from the microcontroller 8 and inputs it into its internal MES system for extended reporting. The automatic recording component 19 automatically records the data and then transmits it to the automatic diagnostic component 20. The automatic diagnostic component 20 incorporates a convolutional neural network-based intelligent algorithm, outputs diagnostic results, and generates decision commands that are sent to the controller 10. The controller 10 executes the calibration process control commands from the microcontroller 8 to drive the motion adjustment component 18 in the drive control subsystem to perform corresponding actions. Simultaneously, it executes the decision commands to drive the alarm 11 in the control subsystem.

[0010] The control subsystem includes a display screen 9, an alarm 11, a start / stop command button 13, a record command button 14, a reset command button 15, a clear command button 16, a command input device 17, a motion adjustment component 18, and a calibration command button 21. Display screen 9, start / stop command button 13, record command button 14, reset command button 15, clear command button 16, input command device 17, and calibration command button 21 are all associated with microcontroller 8. Among them, the input command device 17 has a human-machine interface and is used to select the standard data source 5 according to the type of measurement tool of the aviation product to be calibrated, thereby selecting the appropriate standard data signal 6 as the calibration reference. Start / stop command button 13 is used for power-on and power-off operations, calibration command button 21 is used to start the calibration work, record command button 14 is used to manually record data, reset command button 15 is used to clear the data of a single measurement, and clear command button 16 is used to clear the alarm status. Display screen 9 is used to display the data processed and analyzed by microcontroller 8, comparison results, and related calibration information. Alarm 11 is driven by controller 10 and issues an alarm when the calibration result is unqualified. Motion adjustment component 18 is driven by controller 10 to complete the corresponding action and complete the measurement in conjunction with strain gauge sensor 1.

[0011] The relationship between the relative change in resistance RΔR of the strain gauge sensor 1 and the strain ε can be expressed as RΔR=kε, where k is the sensitivity coefficient of the strain gauge, which is determined by the material and structure of the strain gauge.

[0012] For data acquisition module 2, assuming a resolution of n bits and a full-scale input voltage of V... FS Then the quantized digital quantity D and the input voltage V in The relationship is D = V FS / V in ×2 n To ensure signal quality and accuracy, the data acquisition module 2 needs to amplify, filter, and process the weak electrical signal generated by the strain gauge sensor 1, converting it into a signal form suitable for digital acquisition and processing, thereby improving signal quality and reducing the impact of noise and interference.

[0013] Furthermore, the motion adjustment component 18 can be designed according to the applicable aviation product measuring tool, or multiple motion adjustment components 18 can be designed together to realize that one device is applicable to multiple aviation product measuring tools.

[0014] Furthermore, the standard data source mounted on the microcontroller 8 is formed by acquiring reference data through the data acquisition module 2.

[0015] Furthermore, the indicator alarm 11 includes both a light alarm and a sound alarm, which can be selected as needed, and preferably both light and sound methods are used simultaneously.

[0016] A digital calibration method for aerospace equipment measurement tools based on strain effects, implemented using the aforementioned digital calibration system, includes the following steps:

[0017] Step S1: Enter the command. Power on the digital calibration system by operating the start / stop command button 13; use the command input device 17 to select the calibration mode, set the calibration parameters, specify the calibration point or calibration sequence according to the type of measuring tool of the aviation product to be calibrated, and select the calibration standard data signal 6 as the calibration reference.

[0018] Step S2: Perform the transmission action. Place the strain gauge sensor 1 on the working end of the aerospace product measuring tool to be calibrated; operate the calibration command button 21 to start the calibration work. The microcontroller 8 generates a calibration process control command according to the settings of the input command device 17 and sends it to the controller 10. The controller 10 executes the command and drives the motion adjustment component 18 to perform precise movement. The strain gauge sensor 1 is used to perform measurement to complete the calibration of the aerospace product measuring tool.

[0019] Step S3: Data Acquisition. The strain gauge sensor 1 generates a voltage signal and sends it to the data acquisition module 2. The data acquisition module 2 collects various data during the calibration process, including but not limited to sensor measurement data, instrument status information, and environmental parameters. The data acquisition module 2 then transmits the collected data to the strain signal conditioning module 3.

[0020] Step S4: Strain signal conditioning. The strain signal conditioning module 3 performs preliminary processing and optimization on the data, converting the analog signal into a digital voltage signal before sending it to the embedded strain testing module 4.

[0021] Step S5: Embedded Strain Testing. The embedded strain testing module 4 can accurately measure the strain experienced by aerospace product measuring tools under various working conditions. Through the built-in high-precision strain sensor, it converts mechanical strain into electrical signals and analyzes and tests the signals to ensure that the data meets specific testing requirements, providing an accurate data foundation for subsequent analysis and calibration.

[0022] Step S6: Data Processing and Comparison. The microcontroller 8 receives data from the strain test module 4, processes it into electrical signals through the data processing system, and compares it with the standard data signal 6 from the standard data source to identify and analyze differences, including measured values, error values, and repeatability. The data processing system performs data analysis, calculates statistical parameters such as average, standard deviation, and variance, plots error curves, and analyzes the data distribution pattern to determine whether the calibrated instrument meets the specified accuracy requirements, thus obtaining calibration results or conclusions. The microcontroller 8 sends the processed data to the host computer 12 for MES system entry and simultaneously sends it to the display screen 9 for result display.

[0023] Step S7: Execute automatic control. The microcontroller 8 performs preprocessing such as filtering and noise reduction on the data to eliminate interference and errors in the measurement process. Then, it calculates various calibration parameters of the aviation product measuring tool and finally makes a decision, which is sent to the automatic recording component 19. The automatic recording component 19 automatically records the data and then transmits it to the automatic diagnostic component 20. The automatic diagnostic component 20 outputs the diagnostic results and forms a decision command, which is sent to the controller 10. The controller 10 executes the decision command. If the diagnostic result is unqualified, the alarm 11 is activated to issue a warning.

[0024] Step S8: After completing one calibration, operate the reset command button 15 to clear the previous measurement data and perform another measurement to reduce calibration error; if the alarm 11 is activated, operate the clear command button 16 to deactivate it.

[0025] The beneficial effects of this invention are:

[0026] This invention achieves efficient calibration of measuring tools through the coordinated operation of a series of sophisticated electronic components and modules. It not only improves the reliability and accuracy of the measuring tools but also simplifies operation and significantly enhances calibration efficiency. The application of digital calibration technology makes the entire calibration process more automated and intelligent, reducing human intervention and thus improving the consistency and repeatability of calibration results. Furthermore, this invention can monitor the calibration status in real time, promptly detect and correct deviations, ensuring calibration quality.

[0027] In practical applications, this invention significantly improves the calibration accuracy and efficiency of aviation equipment. Compared with traditional calibration methods, this method drastically reduces the calibration time and simplifies the operation process, thereby effectively reducing the possibility of human error. Furthermore, thanks to the application of digital processing technology, the recording and analysis of calibration data become more accurate, facilitating long-term tracking and maintenance. In numerous field tests, this method demonstrated extremely high stability and repeatability, ensuring the consistent performance of aviation equipment under various complex environments. Ultimately, this method not only improves the maintenance efficiency of aviation equipment but also provides a more reliable technical guarantee for aviation safety.

[0028] In the maintenance and repair of aviation equipment, this invention significantly reduces maintenance costs. The automation and digitalization of the calibration process reduces reliance on specialized technicians, thereby effectively reducing labor costs. Simultaneously, the increased calibration efficiency shortens downtime for aviation equipment, directly improving airline operational efficiency. Furthermore, the high stability and repeatability of this method ensures the long-term stable operation of aviation equipment, reducing the failure rate caused by improper calibration, thus lowering maintenance costs and potential safety risks.

[0029] In the aviation industry's increasingly focused-on environmental protection efforts, this invention also demonstrates unique advantages. Due to the precision of the calibration process, it ensures that aviation equipment operates at its optimal performance, thereby effectively reducing fuel consumption and emissions, meeting the current stringent environmental requirements of the aviation industry. In the long term, this method helps promote the sustainable development of the aviation industry and makes a positive contribution to environmental protection. It not only reduces environmental impact but also further improves the economic benefits of airlines by optimizing energy efficiency.

[0030] In conclusion, this invention not only represents technological innovation but also brings significant economic and environmental benefits, marking a major advancement in the field of aviation equipment maintenance. It not only improves the accuracy and efficiency of calibration work but also lays a solid foundation for the future development of the aviation industry by reducing maintenance costs and enhancing environmental performance. With the continuous development and application of digital technology, we have reason to believe that this calibration method will play an even more important role in the future aviation industry, driving the entire industry towards greater efficiency, safety, and environmental friendliness. Attached Figure Description

[0031] Figure 1 This is a schematic diagram illustrating the working principle of a digital calibration system for aerospace equipment measurement tools based on strain effects.

[0032] The components are as follows: 1-Strain gauge sensor; 2-Data acquisition module; 3-Strain signal conditioning module; 4-Embedded strain testing module; 5-Standard data source; 6-Standard data signal; 7-Comparison link; 8-Microcontroller; 9-Display screen; 10-Controller; 11-Alarm; 12-Host computer; 13-Start / Stop command button; 14-Record command button; 15-Reset command button; 16-Clear command button; 17-Input command device; 18-Motion adjustment component; 19-Automatic recording and analysis component; 20-Automatic diagnostic component; 21-Calibration command button. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] A digital calibration system for aerospace equipment measurement tools based on strain effects, such as Figure 1 It includes a control subsystem and a sensing and analysis subsystem.

[0035] The sensing and analysis subsystem includes a strain gauge sensor 1, a data acquisition module 2, a strain signal conditioning module 3, an embedded strain testing module 4, a microcontroller 8, a controller 10, a host computer 12, an automatic recording and analysis component 19, and an automatic diagnostic component 20. Strain gauge sensor 1 is positioned at the working end of the aerospace product measurement tool to be calibrated. Based on the piezoresistive effect of the metal strain gauge, it detects the working end of the tool and generates a voltage signal, which is sent to data acquisition module 2. Data acquisition module 2 collects various data during the calibration process, including but not limited to sensor measurement data, instrument status information, and environmental parameters. It then transmits the collected data to strain signal conditioning module 3. Strain signal conditioning module 3 performs preliminary processing and optimization of the data, converting the analog signal into a digital voltage signal before sending it to embedded strain testing module 4. Embedded strain testing module 4 accurately measures the strain experienced by the aerospace product measurement tool under various operating conditions. Through a built-in high-precision strain sensor, it converts mechanical strain into an electrical signal and analyzes and tests the signal to ensure that the data meets specific testing requirements, providing an accurate data foundation for subsequent analysis and calibration. Microcontroller 8 is associated with the input command device 17 in the control subsystem to set the type of aerospace product measurement tool to be calibrated. Microcontroller 8 is equipped with… The system comprises a standard data source, a calibration process control system, and a data processing system. Based on the type of aerospace product measurement tool being measured, the system selects the calibration process and the standard data source. On one hand, it generates calibration process control commands and sends them to the controller 10. On the other hand, it receives data from the strain test module 4, processes it into electrical signals through the data processing system, and compares them with the standard data signals 6 in the standard data source to obtain calibration results or conclusions. The microcontroller 8 sends the processed data to the host computer 12 and the automatic recording component 19. The host computer 12 receives the processed data from the microcontroller 8 and inputs it into its internal MES system for extended reporting. The automatic recording component 19 automatically records the data and then transmits it to the automatic diagnostic component 20. The automatic diagnostic component 20 incorporates a convolutional neural network-based intelligent algorithm, outputs diagnostic results, and generates decision commands that are sent to the controller 10. The controller 10 executes the calibration process control commands from the microcontroller 8 to drive the motion adjustment component 18 in the drive control subsystem to perform corresponding actions. Simultaneously, it executes the decision commands to drive the alarm 11 in the control subsystem.

[0036] The control subsystem includes a display screen 9, an alarm 11, a start / stop command button 13, a record command button 14, a reset command button 15, a clear command button 16, a command input device 17, a motion adjustment component 18, and a calibration command button 21. Display screen 9, start / stop command button 13, record command button 14, reset command button 15, clear command button 16, input command device 17, and calibration command button 21 are all associated with microcontroller 8. Among them, the input command device 17 has a human-machine interface and is used to select the standard data source 5 according to the type of measurement tool of the aviation product to be calibrated, thereby selecting the appropriate standard data signal 6 as the calibration reference. Start / stop command button 13 is used for power-on and power-off operations, calibration command button 21 is used to start the calibration work, record command button 14 is used to manually record data, reset command button 15 is used to clear the data of a single measurement, and clear command button 16 is used to clear the alarm status. Display screen 9 is used to display the data processed and analyzed by microcontroller 8, comparison results, and related calibration information. Alarm 11 is driven by controller 10 and issues an alarm when the calibration result is unqualified. Motion adjustment component 18 is driven by controller 10 to complete the corresponding action and complete the measurement in conjunction with strain gauge sensor 1.

[0037] The relationship between the relative change in resistance RΔR of the strain gauge sensor 1 and the strain ε can be expressed as RΔR=kε, where k is the sensitivity coefficient of the strain gauge, which is determined by the material and structure of the strain gauge. In the digital calibration of aerospace equipment, the signal conversion formula of the strain sensor is usually based on the strain measurement principle. For strain gauge sensors, when the common Wheatstone bridge circuit measures strain, the relationship between the output voltage Uo and the strain ε is: Uo=K×Ui×ε, where Uo is the voltage signal output by the bridge (V), K is the sensitivity coefficient of the strain gauge, which depends on factors such as the material and structure of the strain gauge, Ui is the excitation voltage of the bridge (V), and ε is the strain (με).

[0038] For data acquisition module 2, assuming a resolution of n bits and a full-scale input voltage of V... FS Then the quantized digital quantity D and the input voltage V in The relationship is D = V FS / V in ×2 n To ensure signal quality and accuracy, the data acquisition module 2 needs to amplify, filter, and process the weak electrical signal generated by the strain gauge sensor 1, converting it into a signal form suitable for digital acquisition and processing, thereby improving signal quality and reducing the impact of noise and interference.

[0039] The formula for measuring strain using a strain gauge bridge in embedded strain testing module 4 is as follows: (When the Wheatstone bridge is balanced, Uo = 0; when unbalanced, it is used to calculate the output voltage.) When a strain gauge is connected to the bridge, the relationship between the strain ε and the bridge output voltage Uo (assuming the strain gauge sensitivity coefficient is K and the excitation voltage is Ui) is: Uo = K × Ui × ε. If we consider the signal conditioning circuit (e.g., amplification factor A) and analog-to-digital conversion (ADC resolution N, etc.) in the embedded system, the formula for deducing the strain ε from the acquired digital quantity D (ADC output) might be: ε = A × N × K × UiD, where R1, R2, R3, and R4 are the four bridge arm resistors; Ui is the bridge excitation voltage; K is the strain gauge sensitivity coefficient; Uo is the bridge output voltage; A is the signal conditioning amplification factor; N is the ADC resolution (e.g., for a 12-bit ADC, N = 2^12 = 4096); D is the digital quantity acquired by the ADC; and ε is the strain value. In practical applications, accurate derivation and adjustment are required based on the specific embedded system hardware configuration and calibration requirements.

[0040] The motion adjustment component 18 is designed according to the applicable aviation product measurement tool. Multiple motion adjustment components 18 can also be designed in combination to achieve a single device applicable to various aviation product measurement tools. In this embodiment, the motion adjustment component 18 is equipped with an electric telescopic device, which is driven by the controller 10 to extend and retract to achieve the appropriate calibration position, facilitating data acquisition. In other embodiments, the motion adjustment component 18 can also employ a servo motor, driven by the controller 10 for forward and reverse rotation.

[0041] The standard data source mounted on the microcontroller 8 is formed by acquiring reference data through the data acquisition module 2.

[0042] The indicator alarm 11 includes two types: a light alarm and a sound alarm. The appropriate method can be selected as needed, and it is preferable to use both light and sound methods simultaneously.

[0043] A digital calibration method for aerospace equipment measurement tools based on strain effects, implemented using the aforementioned digital calibration system, includes the following steps:

[0044] Step S1: Enter the command. Power on the digital calibration system by operating the start / stop command button 13; use the command input device 17 to select the calibration mode, set the calibration parameters, specify the calibration point or calibration sequence according to the type of measuring tool of the aviation product to be calibrated, and select the calibration standard data signal 6 as the calibration reference.

[0045] Step S2: Perform the transmission action. Place the strain gauge sensor 1 onto the working end of the aerospace product measuring tool to be calibrated; operate the calibration command button 21 to start the calibration process. The microcontroller 8, according to the settings of the input command device 17, generates a calibration process control command and sends it to the controller 10. The controller 10 executes the command and drives the motion adjustment component 18 to perform precise movement. Measurements are taken using the strain gauge sensor 1 to complete the calibration of the aerospace product measuring tool.

[0046] Step S3: Data Acquisition. The strain gauge sensor 1 generates a voltage signal and sends it to the data acquisition module 2. The data acquisition module 2 collects various data during the calibration process, including but not limited to sensor measurement data, instrument status information, and environmental parameters. The data acquisition module 2 then transmits the collected data to the strain signal conditioning module 3.

[0047] Step S4: Strain signal conditioning. The strain signal conditioning module 3 performs preliminary processing and optimization on the data, converting the analog signal into a digital voltage signal before sending it to the embedded strain testing module 4.

[0048] Step S5: Embedded Strain Testing. The embedded strain testing module 4 can accurately measure the strain experienced by aerospace product measuring tools under various working conditions. Through the built-in high-precision strain sensor, it converts mechanical strain into electrical signals and analyzes and tests the signals to ensure that the data meets specific testing requirements, providing an accurate data foundation for subsequent analysis and calibration.

[0049] Step S6: Data Processing and Comparison. The microcontroller 8 receives data from the strain test module 4, processes it into electrical signals through the data processing system, and compares it with the standard data signal 6 from the standard data source to identify and analyze differences, including measured values, error values, and repeatability. The data processing system performs data analysis, calculates statistical parameters such as average, standard deviation, and variance, plots error curves, and analyzes the data distribution pattern to determine whether the calibrated instrument meets the specified accuracy requirements, thus obtaining calibration results or conclusions. The microcontroller 8 sends the processed data to the host computer 12 for MES system entry and simultaneously sends it to the display screen 9 for result display.

[0050] Step S7: Execute automatic control. The microcontroller 8 performs preprocessing such as filtering and noise reduction on the data to eliminate interference and errors in the measurement process. Then, it calculates various calibration parameters of the aviation product measuring tool and finally makes a decision, which is sent to the automatic recording component 19. The automatic recording component 19 automatically records the data and then transmits it to the automatic diagnostic component 20. The automatic diagnostic component 20 outputs the diagnostic results and forms a decision command, which is sent to the controller 10. The controller 10 executes the decision command. If the diagnostic result is unqualified, the alarm 11 is activated to issue a warning.

[0051] Step S8: After completing one calibration, operate the reset command button 15 to clear the previous measurement data and perform another measurement to reduce calibration error; if the alarm 11 is activated, operate the clear command button 16 to deactivate it.

[0052] The above description is only a partial embodiment of the present invention and does not limit the implementation and protection scope of the present invention. Any improvements and modifications made by those skilled in the art based on the disclosure of the present invention without departing from the scope of the present invention should be within the protection scope of the present invention.

Claims

1. A digital calibration system for aerospace equipment measurement tools based on strain effects, characterized in that, It includes a control subsystem and a sensing and analysis subsystem; the sensing and analysis subsystem collects calibration data of the measuring tool of the aviation product to be calibrated through strain gauge sensor (1), performs data processing and analysis, compares it with standard data to obtain the verification result and displays it; The control subsystem is used to set the type of aviation product to be calibrated and works with the sensor analysis subsystem to complete the calibration.

2. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 1, characterized in that, The sensing and analysis subsystem includes a strain gauge sensor (1), a data acquisition module (2), a strain signal conditioning module (3), an embedded strain testing module (4), a microcontroller (8), a controller (10), and an automatic diagnostic component (20). The strain gauge sensor (1) is placed on the working end of the measuring tool for the aerospace product to be calibrated. Based on the piezoresistive effect of the metal strain gauge, it detects the working end of the measuring tool and generates a voltage signal, which is sent to the data acquisition module (2). The data acquisition module (2) collects various data during the calibration process and transmits them to the strain signal conditioning module (3). The strain signal conditioning module (3) converts the analog signal into a digital voltage signal and sends it to the embedded strain testing module (4). The embedded strain testing module (4) converts the mechanical strain into an electrical signal and performs analysis and testing. The microcontroller (8) is connected to the input command device (17) in the control subsystem. The microcontroller (8) is equipped with a standard data source, a calibration process control system, and a data processing system to set the type of aviation product measurement tool to be calibrated. According to the set type of aviation product measurement tool, the calibration process and standard data source are selected. On the one hand, a calibration process control command is generated and sent to the controller (10). On the other hand, the data from the embedded strain test module (4) is received, processed into an electrical signal by the data processing system, and compared with the standard data signal (6) in the standard data source to obtain the calibration result or conclusion data, which is then transmitted to the automatic diagnostic component (20). The automatic diagnostic component (20) has a built-in intelligent algorithm based on a convolutional neural network, outputs the diagnostic result and generates a decision command to be sent to the controller (10). The controller (10) executes the calibration process control command of the microcontroller (8) to drive the motion adjustment component (18) in the drive control subsystem to perform corresponding actions. The control subsystem includes a display screen (9), a start / stop command button (13), a record command button (14), a reset command button (15), a command input device (17), a motion adjustment component (18), and a calibration command button (21). The display screen (9), start / stop command button (13), record command button (14), reset command button (15), command input device (17), and calibration command button (21) are all associated with a microcontroller (8). The command input device (17) has a human-machine interface and is used to input commands according to the type of measuring tool for the aviation product to be calibrated. The standard data source selection 5 is used to select the appropriate standard data signal (6) as the calibration reference; the start / stop command button (13) is used for power-on and power-off operations, the calibration command button (21) is used to start the calibration work, the record command button (14) is used to manually record data, and the reset command button (15) is used to eliminate the measurement data; the display screen (9) is used to display the data processed and analyzed by the microcontroller (8), the comparison results, and related calibration information; the motion adjustment component (18) is driven by the controller (10) to complete the corresponding action and cooperate with the strain gauge sensor (1) to complete the measurement.

3. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 2, characterized in that, The motion adjustment component (18) is designed according to the applicable aviation product measuring tool, or multiple motion adjustment components (18) can be designed together to realize that one device is applicable to multiple aviation product measuring tools.

4. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 2, characterized in that, The standard data source mounted in the microcontroller (8) is formed by collecting the reference data through the data acquisition module (2).

5. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 2, characterized in that, The sensor analysis subsystem also includes an automatic recording and analysis component (19) for automatically recording the data processed by the microcontroller (8).

6. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 2, characterized in that, The sensor analysis subsystem also includes a host computer (12) for receiving data processed by the microcontroller (8) and inputting it into the MES system built into it for extended reporting.

7. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 2, characterized in that, The control subsystem also includes an alarm (11) and a clear command button (16). The alarm (11) is driven by the controller (10) and issues a warning alarm when the calibration result is unqualified. The clear command button (16) is used to clear the warning alarm state.

8. The digital calibration system for aerospace equipment measurement tools based on strain effect according to claim 7, characterized in that, The indicator alarm (11) includes two types: light alarm and sound alarm, which can be selected as needed.

9. A digital calibration method for aerospace equipment measuring tools based on strain effects, implemented using the digital calibration system described in any one of claims 1-8, characterized in that, Includes the following steps: Step S1: Enter the command; operate the start / stop command button (13) to power on the digital calibration system; use the command input device (17) to select the calibration mode, set the calibration parameters, specify the calibration point or calibration sequence according to the type of measurement tool of the aviation product to be calibrated, and select the calibration standard data signal (6) as the calibration reference; Step S2: Perform transmission action; place the strain gauge sensor (1) on the working end of the measuring tool for the aerospace product to be calibrated; operate the calibration command button (21) to start the calibration work, the microcontroller (8) forms a calibration process control command according to the settings of the input command device (17) and sends it to the controller (10), the controller (10) executes the command and drives the motion adjustment component (18) to perform precise movement, and uses the strain gauge sensor (1) to perform measurement to complete the calibration of the measuring tool for the aerospace product; Step S3: Data acquisition; The strain gauge sensor (1) generates a voltage signal and sends it to the data acquisition module (2). The data acquisition module (2) acquires various data during the calibration process, including but not limited to sensor measurement data, instrument status information, and environmental parameters. The data acquisition module (2) then transmits the acquired data to the strain signal conditioning module (3). Step S4: Strain signal conditioning; The strain signal conditioning module (3) performs preliminary processing and optimization on the data, converts the analog signal into a digital voltage signal, and sends it to the embedded strain test module (4); Step S5: Embedded strain test; The embedded strain testing module (4) converts mechanical strain into electrical signals and analyzes and tests the signals; Step S6: Data processing and comparison; The microcontroller (8) receives the data from the strain test module 4, processes it into an electrical signal through the data processing system, and compares it with the standard data signal (6) in the standard data source to obtain the calibration result or conclusion data; The microcontroller (8) sends the processed data to the host computer (12) for MES system reporting, and sends it to the display screen (9) for result display; Step S7: Execute automatic control; the microcontroller (8) finally makes a decision and sends it to the automatic recording component 19. The automatic recording component 19 automatically records the data and then passes it to the automatic diagnosis component (20); the automatic diagnosis component (20) outputs the diagnosis result and forms a decision instruction to send to the controller (10). The controller (10) executes the decision instruction. Step S8: After completing one calibration, operate the reset command button (15) to clear the previous measurement data and perform another measurement to reduce calibration error.

10. A digital calibration method for aerospace equipment measurement tools based on strain effect according to claim 9, characterized in that, In step S7, if the diagnostic result is unqualified, the controller (10) drives the alarm (11) to issue a warning alarm, and the warning alarm is cleared by operating the clear command button (16).

Images