An aerofoil profile template batch measurement method, device, equipment and medium

Abstract

This application discloses a method, apparatus, equipment, and medium for batch measurement of aircraft blade profile templates. The method includes the following steps: S1, designing and manufacturing batch clamping template measuring fixtures by collecting relevant parameters of the shape structure, size range, and reference position of standard profile templates; S2, configuring the measuring fixture matrix coordinate system; S3, digital inspection of individual aircraft blade profile templates; S4, batch measurement of aircraft blade profile templates, using loop statements to embed subroutines to achieve batch measurement; S5, setting the measurement result output method and template of the measurement system so that the nominal value, measured value, and deviation value of each coordinate point are automatically output as an EXCEL format measurement report electronic document according to the inspection report template. This application solves the technical problems of existing technologies such as large errors, long time consumption, low efficiency, inability to accurately measure along the normal direction of the profile, inability to evaluate the profile line contour through overall best fitting, and low degree of automation.

Description

Technical Field

[0001] This application relates to the field of measurement technology, and in particular to a method, apparatus, equipment and medium for batch measurement of aircraft blade profile templates. Background Technology

[0002] Aircraft blade profile templates are tooling used to indirectly measure the profile of aero-engine blades. They are achieved by using a set of templates with different cross-sections to measure the spatial profile of the blade. The main verification item for aircraft blade profile templates is line profile accuracy. Depending on the cross-sectional profile of the target blade, each blade profile template drawing number often contains 5-12 individual pieces with different profiles, and the profile measurement of each individual piece involves more than one hundred coordinate points. The effective height of the profile profile of aircraft blade templates is very thin, often only 1 mm, making it inconvenient to use the contact measurement method of a coordinate measuring machine. Generally, non-contact measurement is performed using imaging equipment such as universal tool microscopes. However, existing measurement methods have the following problems: (1) Each piece of the aircraft blade profile template has more than one hundred coordinate points. When measuring with a universal tool microscope, the reference point must be re-measured and positioned for each workpiece, the worktable must be moved to more than one hundred target inspection points, and the inspection results must be recorded manually, which results in movement error. It is time-consuming, easy to cause visual fatigue, and the error of repeated inspection is large.

[0003] (2) Large batch size means that only one single piece can be measured after each alignment, resulting in low measurement efficiency.

[0004] (3) The measurement direction cannot be accurately along the normal of the surface.

[0005] (4) Existing measurement methods cannot evaluate the profile of the surface line through overall best fit.

[0006] (5) The measurement data cannot be automatically transmitted to the digital testing system after the measurement report is generated. Summary of the Invention

[0007] This application provides a batch measurement method for aircraft blade profile templates, which solves the technical problems of existing technologies such as large errors, long time consumption, low efficiency, inability to accurately measure along the normal direction of the profile, inability to evaluate the profile line profile through overall best fitting, and low degree of automation.

[0008] This application is achieved through the following solution: A method for batch measurement of aircraft blade profile templates includes the following steps: S1. By collecting relevant parameters such as the shape, size range and reference position of standard profile templates, design and manufacture batch clamping template measuring fixtures to achieve the positioning of aircraft blade profile template arrays; S2. Configure the measurement fixture matrix coordinate system. The auxiliary fixture is designed as a twelve-grid system. Two positioning threaded holes are designed to be fixed on the image measurement system. The X and Y directions of the reference are roughly consistent with the directions of the mechanical coordinate system of the measurement system. S3. Digital inspection of single aircraft blade profile templates, including importing the three-dimensional solid model of the template and the coordinates of the inspection points, controlling the camera of the measurement system to automatically move to the coordinate position of each measuring point for automatic measurement, evaluating the line profile of the profile template based on the measured values ​​of the measuring points, and creating a subroutine at the beginning of the program after the program for a single template is completed and successfully debugged, so that it can be called during batch measurement. S4. Batch measurement of aircraft blade profile templates: Input the component drawing number of each profile template to be measured into the main program, use the file pointer function to store and call the input component drawing number information, and then use loop statements to embed subroutines to realize batch measurement. S5. Set the output method and template for the measurement results of the measurement system so that the nominal value, measured value and deviation value of each coordinate point are automatically output as an electronic document of measurement report in EXCEL format according to the test report template.

[0009] Furthermore, in step S1, when designing and manufacturing batch clamping template measuring fixtures: It adopts a twelve-grid magnetic positioning system, with magnetic strips embedded in segments inside the inner frame, which can attract the workpiece to be measured; The fixture is connected and fixed to the composite image measurement system using a high-head screw, and the coordinate system of the fixture is aligned with the original coordinate system of the equipment. The intersections of the measuring fixture's squares are marked with numbers; there are a total of 48 numbers in the twelve-square grid.

[0010] Furthermore, in step S1, the height of the installed magnetic strip is aligned with the bottom surface of the measuring fixture frame; the measuring fixture is made of medium-strength 2A11 aluminum alloy material.

[0011] Furthermore, step S2 specifically includes the following steps: S21. Set the 12 slots of the auxiliary fixture to be equidistant in the X and Y directions, with a spacing of M in the X direction and a spacing of N in the Y direction; S22. First, measure the references of fixtures A and B to establish an initial coordinate system. Then, translate the coordinates in the X and Y directions according to the spacing to obtain the coordinate systems of different slots. Save the current coordinate system as an external coordinate system for use in the main program and template subroutine.

[0012] Furthermore, step S3 specifically includes the following steps: S31. First, create an AutoCAD drawing according to the design drawing, and then create a 3D model from the AutoCAD drawing. The direction and origin of the coordinate system of the 3D model must be consistent with the design drawing. S32. Import the coordinate values ​​of the test points in advance, including extracting the X and Y values ​​of the measurement points on the aviation blade profile template drawing and inputting them into an EXCEL document in sequence. Add a column of Z values ​​and assign them all the value of 0. Then customize it into a Notepad template and change the file extension to .XYZ. S33. The lens of the control measurement system can automatically move to the coordinate position of each measuring point for automatic measurement. The line profile of the template is evaluated based on the measured value of the measuring point. After the program for a single template is completed and successfully debugged, a subroutine is created at the beginning of the program so that it can be called during batch measurement.

[0013] Furthermore, step S33 specifically includes the following steps: S331, Insert Annotation: At the beginning of the measurement program for a single template, add annotation content. Select "Input" as the annotation type. First, enter the keyword for the placement of the template in the slot. When using a matrix fixture for blade calibration templates, it is first uniformly stipulated that all blade basin templates and blade back templates are placed on the left side of the matrix fixture slot, with the profile part entity facing left and the reference entity facing right. If the program annotation specifies that the intersection of the two reference surfaces is to the upper left or lower left, the unique position of the blade standard profile template can be determined. In order to call the corresponding coordinate system of the slot where the template is placed, insert a line in this annotation and enter the slot number where the template is placed. S332. Configure the matrix coordinate system: Use the assignment statement to assign the input slot number to the real number variable, and then call back the external coordinate system corresponding to the real number variable to realize the initial coordinate system of the template without measurement. S333, Model-based measurement point group: Import the 3D solid model and point coordinate text file of the template, measure the template's own datum in the matrix coordinate system, realize the precise coordinate system construction, align the workpiece coordinate system with the model coordinate system, automatically obtain the coordinate position and vector direction of the coordinate point elements in the 3D model, select the point group in the CAD view interface, generate the point group instruction, after the program is executed, the camera of the measurement system can automatically move to the coordinate position of each measuring point for automatic measurement, and the line profile of the surface template can be evaluated based on the measured values ​​of the measuring points; S334. Create a subroutine: After completing and successfully debugging the program for a single template, create a subroutine at the beginning of the program so that it can be called during batch measurement.

[0014] Furthermore, step S4 specifically includes the following steps: S41. Copy blank document: Enter the part number of each test surface template in the main program, use the file pointer function to store and call the entered part number information, create a blank TXT file, copy and paste it to the target location. S42. Write and read information in a file: First, open the blank file copied above, create a file pointer, then write the comment statement containing the part number to the blank file. In the subsequent loop statement, open the file again and read the part number content in the file in sequence as the basis for calling the corresponding subroutine. After processing the file, close the file pointer. S43. Implement batch measurement by embedding subroutines using loop statements: Insert comments in the main program, input the number of parts to be measured in batches, and then assign the input to a variable. Insert a loop statement in the program with the variable as the loop count. Make full use of the PC-DMIS's function of writing and reading information in files, and read the files opened in the program in a loop. Insert flow control pairs in the loop. Each time the loop count is accessed, call the subroutine corresponding to the variable to achieve batch measurement.

[0015] This application also provides a batch measurement device for aircraft blade profile templates, including: The measuring fixture setting module is used to design and manufacture batch clamping measuring fixtures for standard profile templates by collecting relevant parameters such as the shape, size range and reference position of the templates, so as to realize the positioning of the aircraft blade profile template array. The fixture matrix coordinate system configuration module is used to configure the measurement fixture matrix coordinate system. The auxiliary fixture is designed as a twelve-grid fixture, and two positioning threaded holes are designed to be fixed on the image measurement system. The X and Y directions of the reference are roughly consistent with the mechanical coordinate system of the measurement system. The digital inspection module for single aircraft blade profile templates is used for the digital inspection of single aircraft blade profile templates. After importing the three-dimensional solid model of the template and the coordinates of the inspection points, the camera of the control measurement system can automatically move to the coordinate position of each measuring point for automatic measurement. The line profile of the profile template is evaluated based on the measured values ​​of the measuring points. After the program for a single template is completed and successfully debugged, a subroutine is created at the beginning of the program for use in batch measurements. The aviation blade profile template batch measurement module is used for batch measurement of aviation blade profile templates. The main program inputs the component drawing number of each profile template to be measured, uses the file pointer function to store and call the input component drawing number information, and then uses loop statements to embed subroutines to realize batch measurement. The automatic measurement report output module is used to set the output method and template of the measurement results of the measurement system, so that the nominal value, measured value and deviation value of each coordinate point are automatically output as an electronic document of measurement report in EXCEL format according to the test report template.

[0016] This application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aforementioned method for batch measurement of aero-blade profile templates.

[0017] This application also provides a computer program product, including a computer program or computer-executable instructions, which, when executed by a processor, implement the aforementioned method for batch measurement of aircraft blade profile templates.

[0018] Compared with the prior art, this application can produce the following beneficial effects: (a) Develop instructions to achieve fully automated measurement, automatic data collection, automatic processing and analysis, and automatic output of inspection reports for blade profile templates; (b) Profile tolerance can be evaluated through overall best fit, with all surface coordinate points participating in the calculation, which is more in line with the tolerance definition of profile tolerance; (c) The measurement direction of the coordinate points on the profile can be accurately measured along the normal of the profile; (d) The coordinates of the detection points are automatically extracted by the software, eliminating the need for manual input; (e) Enables batch measurement of blade profile templates; (f) After automatically generating the measurement report, the measurement data is transmitted to the digital testing system.

[0019] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0021] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein: Figure 1 This is a flowchart illustrating a preferred embodiment of the method for batch measurement of aircraft blade profile templates in this application. Figure 2 This is a schematic diagram of the preferred embodiment of the aircraft blade template matrix fixture structure of this application; Figure 3 This is a flowchart of the matrix coordinate system programming according to a preferred embodiment of this application; Figure 4 This is a template matrix slot number definition diagram of a preferred embodiment of this application; Figure 5 This is a schematic diagram of a notepad template according to a preferred embodiment of this application; Figure 6 This is a schematic diagram of the preferred embodiment of the present application for automatically extracting the coordinates of measurement points; Figure 7 This is a schematic diagram illustrating the added input type annotation content of a preferred embodiment of this application; Figure 8 This is a schematic diagram of the configuration matrix coordinate system of a preferred embodiment of this application; Figure 9 This is a schematic diagram of the creation subroutine of a preferred embodiment of this application; Figure 10 This is a schematic diagram of the single-piece measurement process of the profile template according to a preferred embodiment of this application; Figure 11 This is a schematic diagram illustrating the copying of a blank document to a target path according to a preferred embodiment of this application; Figure 12 This is a schematic diagram illustrating the application of a subroutine in a preferred embodiment of this application; Figure 13 This is a schematic diagram of the module of the batch measurement device for aircraft blade profile templates according to a preferred embodiment of this application; Figure 14 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application; Figure 15 This is a schematic diagram of the internal structure of a computer device according to a preferred embodiment of this application. Detailed Implementation

[0022] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0023] It should be noted that the executing entity in this embodiment can be a computing service system with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone, or a batch measurement device for aircraft blade profile templates capable of performing the above functions. The following description uses an aircraft blade profile template batch measurement device as the executing entity to illustrate this embodiment and the subsequent embodiments.

[0024] like Figure 1 As shown, to address the aforementioned technical problems, a preferred embodiment of this application provides a method for batch measurement of aircraft blade profile templates, comprising the following steps: S1. By collecting relevant parameters such as the external structure, dimensional range, and reference position of standard templates, design and manufacture batch-sized template-type measuring fixtures (see...). Figure 2 This enables the positioning of aircraft blade profile template arrays. S2. Configure the measurement fixture matrix coordinate system. The auxiliary fixture is designed as a twelve-grid system. Two positioning threaded holes are designed to be fixed on the image measurement system. The X and Y directions of the reference are roughly consistent with the directions of the mechanical coordinate system of the measurement system. S3. Digital inspection of single aircraft blade profile templates, including importing the three-dimensional solid model of the template and the coordinates of the inspection points, controlling the camera of the measurement system to automatically move to the coordinate position of each measuring point for automatic measurement, evaluating the line profile of the profile template based on the measured values ​​of the measuring points, and creating a subroutine at the beginning of the program after the program for a single template is completed and successfully debugged, so that it can be called during batch measurement. S4. Batch measurement of aircraft blade profile templates: Input the component drawing number of each profile template to be measured into the main program, use the file pointer function to store and call the input component drawing number information, and then use loop statements to embed subroutines to realize batch measurement. S5. Set the output method and template for the measurement results of the measurement system so that the nominal value, measured value and deviation value of each coordinate point are automatically output as an electronic document of measurement report in EXCEL format according to the test report template.

[0025] Compared with existing technologies, the batch measurement method for aero-blade profile templates in this embodiment can produce the following beneficial effects: (a) the development instructions realize fully automatic measurement, automatic data collection, automatic processing and analysis, and automatic output of inspection reports for blade profile templates; (b) the profile can be evaluated through overall best fit, with all profile coordinate points participating in the calculation, which is more in line with the tolerance definition of profile; (c) the measurement direction of the profile coordinate points can be accurately measured along the normal of the profile; (d) the coordinate values ​​of the inspection points are automatically extracted by software, without the need for manual input; (e) batch measurement of blade profile templates can be realized; (f) after automatically generating the measurement report, the measurement data is transmitted to the digital inspection system.

[0026] Preferably, in step S1, when designing and manufacturing batch clamping template measuring fixtures: It adopts a twelve-grid magnetic positioning system, with magnetic strips embedded in segments inside the inner frame, which can attract the workpiece to be measured; The high-head screw is connected and fixed to the composite image measurement system, and the coordinate system of the fixture is aligned with the original coordinate system of the equipment. The matrix coordinate system is saved by measuring the reference of the auxiliary fixture. When measuring the template, the initial positioning of the batch templates can be established by calling the coordinate system of the corresponding slot in the matrix. Then, the precise positioning is achieved by measuring the reference of the template itself through a loop program. The matrix fixture is mainly used for positioning. To facilitate subsequent measurements by placing it according to the programming and calling the coordinate system of the corresponding position, the intersection points of the measuring fixture's squares are marked with numbers. There are a total of 48 numbers in the twelve-square grid.

[0027] Preferably, in step S1, the height of the magnetic strip is aligned with the bottom surface of the measuring fixture frame, and the height of the magnetic strip is as close to the bottom surface as possible to prevent the sample being measured from being attracted to the worktable and suspended in mid-air.

[0028] Preferably, since the image measurement system in the measurement scheme has a glass worktable, the measurement fixture is made of medium-strength 2A11 aluminum alloy to reduce its weight.

[0029] This fixture is only used to establish the initial coordinate system; the final reference for template measurement is constructed from the template's own reference surface. This array positioning device enables fully automated batch measurement of template-type tooling in a single operation.

[0030] Preferably, the designed auxiliary fixture is a twelve-grid design, with two positioning threaded holes for fixing to the image measurement system. The X and Y directions of the reference are approximately aligned with the mechanical coordinate system of the measurement system. The 12 slots of the auxiliary fixture are equidistant in the X and Y directions, with a spacing of M in the X direction and N in the Y direction. Step S2 specifically includes the following steps: S21. Set the 12 slots of the auxiliary fixture to be equidistant in the X and Y directions, with a spacing of M in the X direction and a spacing of N in the Y direction; S22. First, measure the references A and B of the fixture to establish an initial coordinate system. Then, translate the coordinates in the X and Y directions according to the spacing to obtain the coordinate systems for different slots. Save the current coordinate system as an external coordinate system for use in the main program and template subroutines. The process of programming the fixture matrix coordinate system is as follows: Figure 3 As shown, when developing the measurement program, each slot number of the matrix fixture was uniformly defined, and each slot corresponds to a different initial coordinate system. The configuration of the 12 slot numbers of the matrix fixture is shown in Figure 4. An annotation window is set up to capture the slot number of the aerospace blade profile template. An assignment statement is used to assign the input slot number to a real number variable, and then the corresponding external coordinate system is called back, thus achieving the acquisition of the template's initial coordinate system without measurement. Preferably, step S3 specifically includes the following steps: S31. First, create an AutoCAD drawing according to the design drawing, and then create a 3D model from the AutoCAD drawing. The direction and origin of the coordinate system of the 3D model must be consistent with the design drawing. After importing the 3D solid model of the template and the coordinates of the inspection points, the coordinate position and vector direction of the coordinate point elements in the 3D model can be automatically obtained, realizing the automatic measurement of the imported coordinate point elements, eliminating vector errors, and accurately establishing a workpiece coordinate system consistent with the template model. S32. Import the coordinate values ​​of the inspection points in advance, including extracting the X and Y values ​​of the measurement points from the aircraft blade profile template drawing and inputting them sequentially into an Excel document. Add a separate column for Z values ​​and assign a uniform value of 0. Then, customize the template into a notepad file (see...). Figure 5Change the file extension to .XYZ and add a line of uppercase English phrases “XYZIJK METRICS” to the first line of the Notepad file; automatically pick coordinate points. If the standard sample being measured has a CAD design drawing, the coordinate points can be extracted using TeamDesigner software (e.g., Figure 6 (As shown). Each standard template requires an average of 120 coordinate data points to be entered. Through research on automatic coordinate point picking technology, the tedious process of manually entering the coordinate values ​​of each measuring point on the drawing is eliminated, as well as the risk of input errors. The extracted coordinate points are also processed in the same way as above, with a column of Z values ​​added and uniformly assigned a value of 0. Then, they are customized into a notepad template, and the file extension is changed to .XYZ. S33. The lens of the control measurement system can automatically move to the coordinate position of each measuring point for automatic measurement. The line profile of the template is evaluated based on the measured value of the measuring point. After the program for a single template is completed and successfully debugged, a subroutine is created at the beginning of the program so that it can be called during batch measurement.

[0031] Preferably, step S33 specifically includes the following steps: S331. Insert Annotation: At the beginning of the measurement program for a single template, add annotation content. Select "Input" as the annotation type. First, enter the keyword for the template's placement in the slot. When using a matrix fixture for blade calibration templates, it is uniformly stipulated that all blade base templates and blade back templates should be placed on the left side of the matrix fixture slot, with the profile portion facing left and the reference portion facing right. If the program annotation specifies that the intersection of the two reference surfaces faces the upper left or lower left, the unique position of the blade standard profile template can be determined. To call the corresponding coordinate system of the placed slot, insert a line in this annotation and enter the slot number where the template is placed (see...). Figure 7 ); S332. Configure the matrix coordinate system: Use an assignment statement to assign the input slot number to a real number variable, and then call back the external coordinate system corresponding to that real number variable to achieve the initial coordinate system of the template without measurement (see...). Figure 8 ); S333, Model-based measurement point group: Import the 3D solid model and point coordinate text file of the template, measure the template's own datum in the matrix coordinate system, realize the precise coordinate system construction, align the workpiece coordinate system with the model coordinate system, automatically obtain the coordinate position and vector direction of the coordinate point elements in the 3D model, select the point group in the CAD view interface, generate the point group instruction, after the program is executed, the camera of the measurement system can automatically move to the coordinate position of each measuring point for automatic measurement, and the line profile of the surface template can be evaluated based on the measured values ​​of the measuring points; S334. Creating Subroutines: After successfully compiling and debugging the program for a single template, create a subroutine at the beginning of the program for use during batch measurements (see...). Figure 9 and Figure 10 ).

[0032] Preferably, step S4 specifically includes the following steps: S41. Copy Blank Document: Enter the component drawing numbers of each test surface template in the main program, use the file pointer function to store and retrieve the entered component drawing number information, create a blank TXT file, copy and paste it to the target location (see...). Figure 11 ); S42. Write and read information in a file: First, open the blank file copied above, create a file pointer, then write the comment statement containing the part number to the blank file. In the subsequent loop statement, open the file again and read the part number content in the file in sequence as the basis for calling the corresponding subroutine. After processing the file, close the file pointer. S43. Implementing batch measurement using embedded subroutines in loop statements: Insert comments in the main program, input the number of parts to be measured in batches, and then assign the input to a variable. Insert a loop statement in the program with this variable as the loop count. Fully utilize the PC-DMIS's ability to write and read information from files, and loop through the files opened in the program. Insert flow control pairs in the loop, and call the subroutine corresponding to the variable each time the loop count is accessed, thus achieving batch measurement (see...). Figure 12 ).

[0033] like Figure 13 As shown, another preferred embodiment of this application also provides a batch measurement device for aircraft blade profile templates, comprising: The measuring fixture setting module is used to design and manufacture batch clamping measuring fixtures for standard profile templates by collecting relevant parameters such as the shape, size range and reference position of the templates, so as to realize the positioning of the aircraft blade profile template array. The fixture matrix coordinate system configuration module is used to configure the measurement fixture matrix coordinate system. The auxiliary fixture is designed as a twelve-grid fixture, and two positioning threaded holes are designed to be fixed on the image measurement system. The X and Y directions of the reference are roughly consistent with the mechanical coordinate system of the measurement system. The digital inspection module for single aircraft blade profile templates is used for the digital inspection of single aircraft blade profile templates. After importing the three-dimensional solid model of the template and the coordinates of the inspection points, the camera of the control measurement system can automatically move to the coordinate position of each measuring point for automatic measurement. The line profile of the profile template is evaluated based on the measured values ​​of the measuring points. After the program for a single template is completed and successfully debugged, a subroutine is created at the beginning of the program for use in batch measurements. The aviation blade profile template batch measurement module is used for batch measurement of aviation blade profile templates. The main program inputs the component drawing number of each profile template to be measured, uses the file pointer function to store and call the input component drawing number information, and then uses loop statements to embed subroutines to realize batch measurement. The automatic measurement report output module is used to set the output method and template of the measurement results of the measurement system, so that the nominal value, measured value and deviation value of each coordinate point are automatically output as an electronic document of measurement report in EXCEL format according to the test report template.

[0034] The batch measurement device for aero-blade profile templates provided in this embodiment adopts the batch measurement method for aero-blade profile templates in the above embodiments, solving the technical problems of large errors, long time consumption, low efficiency, inability to accurately measure along the normal direction of the profile, inability to evaluate the profile line contour through overall best fitting, and low degree of automation in the prior art. Compared with the prior art, the beneficial effects of the batch measurement device for aero-blade profile templates provided in this embodiment are the same as those of the batch measurement method for aero-blade profile templates provided in the above embodiments, and other technical features in the batch measurement device for aero-blade profile templates are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0035] like Figure 14 As shown, a preferred embodiment of this embodiment also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the batch measurement method for aircraft blade profile templates in the above embodiment.

[0036] This embodiment provides an electronic device that employs the batch measurement method for aero-blade profile templates described in the above embodiments. This method addresses the technical problems of existing technologies, such as large errors, long processing times, low efficiency, inaccurate measurement direction along the normal to the profile, inability to evaluate profile line contour through overall best fitting, and low automation. Compared with existing technologies, the electronic device provided in this embodiment has the same beneficial effects as the batch measurement method for aero-blade profile templates described in the above embodiments. Furthermore, other technical features of the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be elaborated upon here.

[0037] like Figure 15 As shown, a preferred embodiment of this invention also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 15As shown, the computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned batch measurement method for aerospace blade profile templates.

[0038] Those skilled in the art will understand that Figure 15 The structure shown is merely a block diagram of a portion of the structure related to the solution of this embodiment, and does not constitute a limitation on the computer device to which the solution of this embodiment is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.

[0039] The computer equipment provided in this application adopts the batch measurement method of aviation blade profile templates in the above embodiments, which solves the technical problems of large errors, long time consumption, low efficiency, inability to accurately measure the direction along the normal of the profile, inability to evaluate the profile line contour through overall best fitting, and low degree of automation in the prior art. Compared with the prior art, the beneficial effects of the computer equipment provided in this embodiment are the same as the beneficial effects of the batch measurement method of aviation blade profile templates provided in the above embodiments, and other technical features in the electronic equipment are the same as the features disclosed in the method of the above embodiments, which will not be repeated here.

[0040] A preferred embodiment of this example also provides a storage medium, which includes a stored program that, when the program is executed, controls the device containing the storage medium to perform the steps of the batch measurement method for aero-blade profile templates in the above-described embodiment.

[0041] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0042] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this embodiment that contribute to the prior art or the technical solution can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this embodiment. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0043] Those skilled in the art will understand that the embodiments of this example can be provided as methods, systems, or computer program products. Therefore, this example can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this example can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that include computer-usable program code. The solutions in this example can be implemented using various computer languages, such as the object-oriented programming language C++ and the embedded programming language C.

[0044] This embodiment is described with reference to flowchart illustrations and / or block diagrams of the method, apparatus (system), and computer program product according to this embodiment. It should be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations. Figure 1 One or more processes and / or boxes Figure 1 A system that specifies functions in one or more boxes.

[0045] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including an instruction set implemented in a process. Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0046] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0047] This embodiment also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the above-described method for batch measurement of aerospace blade profile templates.

[0048] The computer program product provided in this embodiment solves the technical problems of existing technologies, such as large errors, long processing time, low efficiency, inability to accurately measure along the surface normal, inability to evaluate the surface profile through overall best fitting, and low degree of automation. Compared with the prior art, the beneficial effects of the computer program product provided in this embodiment are the same as those of the batch measurement method for aerospace blade surface templates provided in the above embodiments, and will not be repeated here.

[0049] Obviously, those skilled in the art can make various modifications and variations to this embodiment without departing from the spirit and scope of this embodiment. Therefore, if these modifications and variations of this embodiment fall within the scope of the claims of this embodiment and their equivalents, this embodiment is also intended to include these modifications and variations.

Claims

1. A method for batch measurement of aircraft blade profile templates, characterized in that, Including the following steps: S1. By collecting relevant parameters such as the shape, size range and reference position of standard profile templates, design and manufacture batch clamping template measuring fixtures to achieve the positioning of aircraft blade profile template arrays; S2. Configure the measurement fixture matrix coordinate system. The auxiliary fixture is designed as a twelve-grid system. Two positioning threaded holes are designed to be fixed on the image measurement system. The X and Y directions of the reference are roughly consistent with the directions of the mechanical coordinate system of the measurement system. S3. Digital inspection of single aircraft blade profile templates, including importing the three-dimensional solid model of the template and the coordinates of the inspection points, controlling the camera of the measurement system to automatically move to the coordinate position of each measuring point for automatic measurement, evaluating the line profile of the profile template based on the measured values ​​of the measuring points, and creating a subroutine at the beginning of the program after the program for a single template is completed and successfully debugged, so that it can be called during batch measurement. S4. Batch measurement of aircraft blade profile templates: Input the component drawing number of each profile template to be measured into the main program, use the file pointer function to store and call the input component drawing number information, and then use loop statements to embed subroutines to realize batch measurement. S5. Set the output method and template for the measurement results of the measurement system so that the nominal value, measured value and deviation value of each coordinate point are automatically output as an electronic document of measurement report in EXCEL format according to the test report template.

2. The method for batch measurement of aircraft blade profile templates according to claim 1, characterized in that, In step S1, when designing and manufacturing batch clamping template measuring fixtures: It adopts a twelve-grid magnetic positioning system, with magnetic strips embedded in segments inside the inner frame, which can attract the workpiece to be measured; The fixture is connected and fixed to the composite image measurement system using a high-head screw, and the coordinate system of the fixture is aligned with the original coordinate system of the equipment. The intersections of the measuring fixture's squares are marked with numbers; there are a total of 48 numbers in the twelve-square grid.

3. The method for batch measurement of aircraft blade profile templates according to claim 1, characterized in that, In step S1, the height of the installed magnetic strip is aligned with the bottom surface of the measuring fixture frame; the measuring fixture is made of medium-strength 2A11 aluminum alloy.

4. The method for batch measurement of aircraft blade profile templates according to claim 1, characterized in that, Step S2 specifically includes the following steps: S21. Set the 12 slots of the auxiliary fixture to be equidistant in the X and Y directions, with a spacing of M in the X direction and a spacing of N in the Y direction; S22. First, measure the references of fixtures A and B to establish an initial coordinate system. Then, translate the coordinates in the X and Y directions according to the spacing to obtain the coordinate systems of different slots. Save the current coordinate system as an external coordinate system for use in the main program and template subroutine.

5. The method for batch measurement of aircraft blade profile templates according to claim 1, characterized in that, Step S3 specifically includes the following steps: S31. First, create an AutoCAD drawing according to the design drawing, and then create a 3D model from the AutoCAD drawing. The direction and origin of the coordinate system of the 3D model must be consistent with the design drawing. S32. Import the coordinate values ​​of the test points in advance, including extracting the X and Y values ​​of the measurement points on the aviation blade profile template drawing and inputting them into an EXCEL document in sequence. Add a column of Z values ​​and assign them all the value of 0. Then customize it into a Notepad template and change the file extension to .XYZ. S33. The lens of the control measurement system can automatically move to the coordinate position of each measuring point for automatic measurement. The line profile of the template is evaluated based on the measured value of the measuring point. After the program for a single template is completed and successfully debugged, a subroutine is created at the beginning of the program so that it can be called during batch measurement.

6. The method for batch measurement of aircraft blade profile templates according to claim 5, characterized in that, Step S33 specifically includes the following steps: S331. Inserting Comments: At the beginning of the measurement program for a single template, add comments. Select "Input" as the comment type. First, enter the keyword for the placement of the template in the slot. When using a matrix fixture for blade calibration templates, it is first stipulated that all blade basin templates and blade back templates should be placed on the left side of the matrix fixture slot, with the profile part facing left and the reference part facing right. If the program comments specify that the intersection of the two reference surfaces is facing the upper left or lower left, the unique position of the blade standard profile template can be determined. In order to call the coordinate system of the slot where the template is placed, insert a line in this comment and enter the slot number where the template is placed. S332. Configure the matrix coordinate system: Use the assignment statement to assign the input slot number to the real number variable, and then call back the external coordinate system corresponding to the real number variable to realize the initial coordinate system of the template without measurement. S333, Model-based measurement point group: Import the 3D solid model and point coordinate text file of the template, measure the template's own datum in the matrix coordinate system, realize the precise coordinate system construction, align the workpiece coordinate system with the model coordinate system, automatically obtain the coordinate position and vector direction of the coordinate point elements in the 3D model, select the point group in the CAD view interface, generate the point group instruction, after the program is executed, the camera of the measurement system can automatically move to the coordinate position of each measuring point for automatic measurement, and the line profile of the surface template can be evaluated based on the measured values ​​of the measuring points; S334. Create a subroutine: After completing and successfully debugging the program for a single template, create a subroutine at the beginning of the program so that it can be called during batch measurement.

7. The method for batch measurement of aircraft blade profile templates according to claim 1, characterized in that, Step S4 specifically includes the following steps: S41. Copy blank document: Enter the part number of each test surface template in the main program, use the file pointer function to store and call the entered part number information, create a blank TXT file, copy and paste it to the target location. S42. Write and read information in a file: First, open the blank file copied above, create a file pointer, then write the comment statement containing the part number to the blank file. In the subsequent loop statement, open the file again and read the part number content in the file in sequence as the basis for calling the corresponding subroutine. After processing the file, close the file pointer. S43. Implement batch measurement by embedding subroutines using loop statements: Insert comments in the main program, input the number of parts to be measured in batches, and then assign the input to a variable. Insert a loop statement in the program with the variable as the loop count. Make full use of the PC-DMIS's function of writing and reading information in files, and read the files opened in the program in a loop. Insert flow control pairs in the loop. Each time the loop count is accessed, call the subroutine corresponding to the variable to achieve batch measurement.

8. A batch measurement device for aircraft blade profile templates, characterized in that, include: The measuring fixture setting module is used to design and manufacture batch clamping measuring fixtures for standard profile templates by collecting relevant parameters such as the shape, size range and reference position of the templates, so as to realize the positioning of the aircraft blade profile template array. The fixture matrix coordinate system configuration module is used to configure the measurement fixture matrix coordinate system. The auxiliary fixture is designed as a twelve-grid fixture, and two positioning threaded holes are designed to be fixed on the image measurement system. The X and Y directions of the reference are roughly consistent with the mechanical coordinate system of the measurement system. The digital inspection module for single aircraft blade profile templates is used for the digital inspection of single aircraft blade profile templates. After importing the three-dimensional solid model of the template and the coordinates of the inspection points, the camera of the control measurement system can automatically move to the coordinate position of each measuring point for automatic measurement. The line profile of the profile template is evaluated based on the measured values ​​of the measuring points. After the program for a single template is completed and successfully debugged, a subroutine is created at the beginning of the program for use in batch measurements. The aviation blade profile template batch measurement module is used for batch measurement of aviation blade profile templates. The main program inputs the component drawing number of each profile template to be measured, uses the file pointer function to store and call the input component drawing number information, and then uses loop statements to embed subroutines to realize batch measurement. The automatic measurement report output module is used to set the output method and template of the measurement results of the measurement system, so that the nominal value, measured value and deviation value of each coordinate point are automatically output as an electronic document of measurement report in EXCEL format according to the test report template.

9. An electronic device, the electronic device comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, when the processor executes the computer program, it implements a batch measurement method for aircraft blade profile templates as described in any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the batch measurement method for aircraft blade profile templates as described in any one of claims 1 to 7.

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