A CNC machining control method and device for aviation precision components

Abstract

The present application relates to the technical field of numerical control machining, and provides a numerical control machining control method and device for aviation precision components. The method comprises fixing a specimen to be machined on a designated fixture, obtaining a three-dimensional model consisting of the specimen to be machined and the designated fixture; the three-dimensional model comprises a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be machined, and the second virtual model corresponds to the designated fixture; a third virtual model corresponding to the target aviation precision component is nested in the first virtual model; machining control information of the specimen to be machined is generated based on the first virtual model and the third virtual model after nesting; a preset tool is controlled based on the machining control information to process the specimen to be machined, and a target aviation precision component is obtained. The method overcomes the defect of insufficient machining accuracy of complex structures in traditional machining methods.

Description

Technical Field

[0001] The present application relates to the field of CNC machining technology, and in particular to a CNC machining control method and device for aviation precision components. Background Art

[0002] In the field of modern aviation manufacturing, as the performance and reliability requirements of aircraft continue to increase, the manufacturing of precision aviation components has become increasingly important. These components usually have complex spatial surfaces and internal cavity structures, which makes it difficult for traditional processing methods to effectively complete the processing. At present, conventional CNC programming and processing methods are difficult to meet the high-precision processing requirements for complex surfaces and special-shaped structures. Summary of the invention

[0003] The present application provides a method and device for numerical control machining of aviation precision components to solve the problems raised by the above background technology.

[0004] In a first aspect, the present application provides a CNC machining control method for an aviation precision component, comprising:

[0005] After fixing the specimen to be processed on a designated fixture, obtaining a three-dimensional model consisting of the specimen to be processed and the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture;

[0006] The third virtual model corresponding to the target aviation precision component is embedded in the first virtual model; the color of the first virtual model is different from the color of the third virtual model;

[0007] Generate processing control information of the test piece to be processed based on the first virtual model and the third virtual model after being nested;

[0008] Based on the processing control information, a preset tool is controlled to process the test piece to be processed to obtain a target aviation precision component.

[0009] In a possible implementation, the generating the processing control information of the to-be-processed specimen based on the nested first virtual model and the third virtual model includes:

[0010] Performing finite element segmentation processing on the first virtual model to obtain an initial finite element model corresponding to the first virtual model;

[0011] Determine a target finite element unit on the initial finite element model based on the first virtual model and the third virtual model after nesting; wherein the target finite element unit includes a cutting part;

[0012] For each of the target finite element units, obtaining the volume of the cutting portion of the target finite element unit;

[0013] Determine the cutting order of each target finite element unit based on the volume of the cutting part of each target finite element unit, and for each target finite element unit, mark the cutting order of the target finite element unit on the target finite element unit to obtain a target finite element model; the cutting order of each target finite element unit is inversely proportional to its corresponding cutting volume;

[0014] For each of the target finite element units, the target cutting control parameter information of the target finite element unit is generated based on a preset cutting control parameter information generation method, and the cutting control parameter information is labeled based on the cutting order corresponding to the target finite element unit; each labeled cutting control parameter information and the target finite element model constitute the processing control information.

[0015] In a possible implementation, obtaining the volume of the cutting portion of the target finite element unit includes:

[0016] Extracting the target finite element unit in the first virtual model, and extracting the target nesting part nested in the target finite element unit in the third virtual model;

[0017] The difference between the volume of the target finite element unit and the volume of the target nesting portion is determined as the volume of the cutting portion of the target finite element unit.

[0018] In a possible implementation, the method for generating target cutting control parameter information of the target finite element unit based on a preset cutting control parameter information generation method includes:

[0019] Based on the material information of the test piece to be processed, obtaining cutting parameter threshold information in a database; the cutting parameter threshold information includes threshold ranges of multiple cutting parameters;

[0020] For each of the cutting parameters, a preset number of parameter values ​​are extracted within the threshold range of the cutting parameter to obtain a parameter value set of the cutting parameter; wherein the difference between any two adjacent parameter values ​​in the parameter value sequence obtained after arranging the parameter values ​​from small to large is equal;

[0021] Performing a Cartesian product operation on the parameter value sets corresponding to the respective cutting parameters to obtain a plurality of initial cutting control parameter sets;

[0022] For each of the initial cutting control parameter sets, based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, a virtual tool is controlled to perform cutting processing on the target finite element unit, and during the process of the virtual tool performing cutting processing on the target finite element unit, the running trajectory information and posture information of the virtual tool are recorded, and the deformation amount corresponding to the to-be-processed specimen under the initial cutting control parameter set is obtained; wherein the virtual tool corresponds to the tool;

[0023] Determine the initial cutting control parameter set corresponding to the minimum deformation amount as the target cutting control parameter set, and determine the target cutting control parameter set, the running trajectory information corresponding to the target cutting control parameter set, and the posture information corresponding to the target cutting control parameter set as the target cutting control parameter information of the target finite element unit.

[0024] In a possible implementation, obtaining the deformation amount of the to-be-processed specimen corresponding to the initial cutting control parameter set includes:

[0025] Before controlling a virtual tool to perform cutting processing on the target finite element unit based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, respectively acquiring first position information of each of the finite element units;

[0026] After controlling the virtual tool to perform cutting processing on the target finite element unit based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, respectively acquiring second position information of each of the finite element units;

[0027] For each of the finite element units, determining a displacement of the finite element unit based on the first position information and the second position information corresponding to the finite element unit;

[0028] The displacements of the finite element units are added together to obtain the deformation amount of the test piece to be processed corresponding to the initial cutting control parameter set.

[0029] In a possible implementation, the controlling a preset tool based on the processing control information to process the test piece to be processed to obtain a target aviation precision component includes:

[0030] For each of the target finite element units, based on the cutting order and cutting control parameter information corresponding to the target finite element unit, the virtual tool is controlled to cut the corresponding part of the target finite element unit on the first virtual model, and in the process of controlling the virtual tool to cut, the tool is synchronously controlled to cut the corresponding part of the target finite element unit on the specimen to be processed; after the cutting process of the corresponding part of each of the target finite element units on the specimen to be processed is completed, the target aviation precision component is obtained.

[0031] In a second aspect, the present application provides a CNC machining control device for aviation precision components, comprising:

[0032] An acquisition module is used to obtain a three-dimensional model composed of the specimen to be processed and the designated fixture after the specimen to be processed is fixed on the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture;

[0033] A model processing module, used for embedding a third virtual model corresponding to a target aviation precision component into the first virtual model; the color of the first virtual model is different from the color of the third virtual model;

[0034] A generating module, used for generating processing control information of the to-be-processed specimen based on the first virtual model and the third virtual model after being nested;

[0035] The control module is used to control a preset tool to process the test piece to be processed based on the processing control information to obtain a target aviation precision component.

[0036] The present application provides a method and device for numerical control machining of aviation precision components. The method includes: after fixing a specimen to be machined in a designated fixture, obtaining a three-dimensional model composed of the specimen to be machined and the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be machined, and the second virtual model corresponds to the designated fixture; the third virtual model corresponding to the target aviation precision component is nested in the first virtual model; the color of the first virtual model is different from the color of the third virtual model; the machining control information of the specimen to be machined is generated based on the first virtual model and the third virtual model after nesting; the preset tool is controlled to process the specimen to be machined based on the machining control information to obtain the target aviation precision component. The method clearly displays the material area to be removed by nesting the third virtual model corresponding to the target aviation precision component in the first virtual model of the specimen to be machined, and the colors of the first virtual model and the third virtual model are different. This intuitive model superposition method is convenient for accurately locating the machining parts of complex spatial surfaces and inner cavity structures, and overcomes the defect of insufficient machining accuracy of complex structures in traditional machining methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying any creative work.

[0038] Figure 1 A schematic diagram of a flow chart of a method for numerical control machining of aviation precision components provided in an embodiment of the present application;

[0039] Figure 2 A schematic block diagram of the structure of a numerical control machining control device for aviation precision components provided in an embodiment of the present application;

[0040] Figure 3 A schematic block diagram of the structure of a terminal device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] The flowcharts shown in the accompanying drawings are only examples and do not necessarily include all the contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps may also be decomposed, combined or partially merged, so the actual execution order may change according to actual conditions.

[0043] It should also be understood that the terms used in this application specification are only for the purpose of describing specific embodiments and are not intended to limit the application. As used in this application specification and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include plural forms.

[0044] It should be further understood that the term “and / or” used in the specification and appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0045] In conjunction with the accompanying drawings, some embodiments of the present application are described in detail below. In the absence of conflict, the following embodiments and features in the embodiments can be combined with each other.

[0046] See also Figure 1 , Figure 1 A flow chart of a numerical control machining control method for aviation precision components provided in an embodiment of the present application is shown in FIG. Figure 1 As shown, the CNC machining control method for aviation precision components provided in the embodiment of the present application includes steps S1 to S6.

[0047] Step S1, after fixing the specimen to be processed on a designated fixture, obtain a three-dimensional model consisting of the specimen to be processed and the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture.

[0048] Specifically, after the sample to be processed is fixed to the designated fixture, the point cloud data information of the sample to be processed and the designated fixture is obtained by a laser scanner, and a three-dimensional model consisting of the sample to be processed and the designated fixture is constructed based on the point cloud data information. It can be understood that constructing a three-dimensional model consisting of the sample to be processed and the designated fixture can better restore the stress state of the sample to be processed when it is clamped by the designated fixture, which helps to improve the processing accuracy.

[0049] Step S2: embedding a third virtual model corresponding to the target aviation precision component into the first virtual model; the color of the first virtual model is different from the color of the third virtual model.

[0050] It should be noted that, after the third virtual model is nested with the first virtual model, the third virtual model is completely contained in the first virtual model, and there is a tangent point between the third virtual model and the first virtual model's supported surfaces.

[0051] It can be understood that setting the first virtual model and the third virtual model to different colors helps to generate more accurate processing control information in the subsequent processing control information generation process.

[0052] Step S3: generating processing control information of the to-be-processed specimen based on the nested first virtual model and the third virtual model.

[0053] Specifically, step S3 includes the following steps:

[0054] Performing finite element segmentation processing on the first virtual model to obtain an initial finite element model corresponding to the first virtual model;

[0055] Determine a target finite element unit on the initial finite element model based on the first virtual model and the third virtual model after nesting; wherein the target finite element unit includes a cutting part; specifically, based on each of the finite element units, determine whether the shape of the part corresponding to the finite element unit on the first virtual model is the same as the shape of the part corresponding to the finite element unit on the third virtual model; if they are not the same, determine that the finite element unit is the target finite element unit;

[0056] For each of the target finite element units, obtaining the volume of the cutting portion of the target finite element unit;

[0057] The cutting order of each target finite element unit is determined based on the volume of the cutting part of each target finite element unit, and for each target finite element unit, the cutting order of the target finite element unit is marked on the target finite element unit to obtain a target finite element model; the cutting order of each target finite element unit is inversely proportional to its corresponding cutting volume; it can be understood that the larger the cutting volume corresponding to the target finite element unit, the earlier the cutting order of the target finite element unit is; if the larger the cutting volume corresponding to the target finite element unit, the later the cutting order of the target finite element unit is, it is easy to cause the specimen to be processed to be damaged in the later cutting process during the cutting process. The method of this embodiment can reduce the probability of the specimen to be processed being damaged in the later cutting process;

[0058] For each of the target finite element units, the target cutting control parameter information of the target finite element unit is generated based on a preset cutting control parameter information generation method, and the cutting control parameter information is labeled based on the cutting order corresponding to the target finite element unit; each labeled cutting control parameter information and the target finite element model constitute the processing control information.

[0059] It can be understood that the above-mentioned method of obtaining the processing control information, through finite element segmentation, accurate identification of target finite element units, and optimization of cutting order based on cutting volume, on the one hand, helps to improve the processing accuracy of aviation precision components, and on the other hand, helps to prevent the specimen to be processed from being damaged.

[0060] Wherein, the step of obtaining the volume of the cutting portion of the target finite element unit comprises the following steps:

[0061] Extracting the target finite element unit in the first virtual model, and extracting the target nesting part nested in the target finite element unit in the third virtual model;

[0062] The difference between the volume of the target finite element unit and the volume of the target nesting portion is determined as the volume of the cutting portion of the target finite element unit.

[0063] The method for generating target cutting control parameter information of the target finite element unit based on the preset cutting control parameter information generation method comprises the following steps:

[0064] Based on the material information of the test piece to be processed, the cutting parameter threshold information is obtained in the database; the cutting parameter threshold information includes a plurality of cutting parameter threshold intervals; the cutting parameters include feed speed and spindle speed;

[0065] For each of the cutting parameters, a preset number of parameter values ​​are extracted within the threshold range of the cutting parameter to obtain a parameter value set of the cutting parameter; wherein the difference between any two adjacent parameter values ​​in the parameter value sequence obtained after arranging the parameter values ​​from small to large is equal;

[0066] Cartesian product operation is performed on parameter value sets corresponding to each cutting parameter to obtain multiple initial cutting control parameter sets; wherein the Cartesian product operation refers to extracting all possible ordered pairs of a parameter value from each parameter value set;

[0067] For each of the initial cutting control parameter sets, based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, a virtual tool is controlled to perform cutting processing on the target finite element unit, and during the process of the virtual tool performing cutting processing on the target finite element unit, the running trajectory information and posture information of the virtual tool are recorded, and the deformation amount corresponding to the to-be-processed specimen under the initial cutting control parameter set is obtained; wherein the virtual tool corresponds to the tool;

[0068] Determine the initial cutting control parameter set corresponding to the minimum deformation amount as the target cutting control parameter set, and determine the target cutting control parameter set, the running trajectory information corresponding to the target cutting control parameter set, and the posture information corresponding to the target cutting control parameter set as the target cutting control parameter information of the target finite element unit.

[0069] It can be understood that the above method for generating the target cutting control parameter information of the target finite element unit, on the one hand, ensures that the selected cutting parameters match the material characteristics by obtaining the cutting parameter threshold information related to the material of the specimen to be processed from the database, and on the other hand, ensures the uniform distribution of the parameter values ​​by extracting a preset number of parameter values ​​at equal intervals within the threshold range of the cutting parameters, and generates all possible initial cutting control parameter sets by performing Cartesian product operations on the parameter value sets of each cutting parameter, comprehensively explores the parameter space, and determines that the initial cutting control parameter set corresponding to the minimum deformation amount is the target cutting control parameter set, which helps to reduce the deformation generated during the processing and improve the processing accuracy and processing quality.

[0070] Wherein, the step of obtaining the deformation amount of the test piece to be processed corresponding to the initial cutting control parameter set comprises the following steps:

[0071] Before controlling a virtual tool to perform cutting processing on the target finite element unit based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, respectively acquiring first position information of each of the finite element units;

[0072] After controlling the virtual tool to perform cutting processing on the target finite element unit based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, respectively acquiring second position information of each of the finite element units;

[0073] For each of the finite element units, determining a displacement of the finite element unit based on the first position information and the second position information corresponding to the finite element unit;

[0074] The displacements of the finite element units are added together to obtain the deformation amount of the test piece to be processed corresponding to the initial cutting control parameter set.

[0075] Step S4: Based on the processing control information, a preset tool is controlled to process the test piece to obtain a target aviation precision component.

[0076] Specifically, for each of the target finite element units, based on the cutting order and cutting control parameter information corresponding to the target finite element unit, the virtual tool is controlled to cut the corresponding part of the target finite element unit on the first virtual model, and in the process of controlling the virtual tool to perform cutting, the tool is synchronously controlled to cut the corresponding part of the target finite element unit on the specimen to be processed; after the cutting process of the corresponding part of each of the target finite element units on the specimen to be processed is completed, the target aviation precision component is obtained.

[0077] The above method for processing the test piece to be processed ensures the real-time and accurate transmission of the processing path and cutting parameter information through virtual and real synchronous processing, thereby improving the processing accuracy and reducing error accumulation.

[0078] The method provided in this embodiment clearly displays the material area that needs to be removed by embedding the third virtual model corresponding to the target aviation precision component into the first virtual model of the specimen to be processed, and the colors of the first virtual model and the third virtual model are different. This intuitive model superposition method facilitates the precise positioning of the processing parts of complex spatial surfaces and inner cavity structures, and overcomes the defect of insufficient processing accuracy of complex structures by traditional processing methods.

[0079] See also Figure 2 , Figure 2 The schematic block diagram of the structure of the numerical control machining control device 100 for aviation precision components provided in the embodiment of the present application is as follows: Figure 2 As shown, the CNC machining control device 100 for aviation precision components provided in the embodiment of the present application includes:

[0080] The acquisition module 110 is used to obtain a three-dimensional model consisting of the specimen to be processed and the designated fixture after the specimen to be processed is fixed on the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture.

[0081] The model processing module 120 is used to embed a third virtual model corresponding to the target aviation precision component into the first virtual model; the color of the first virtual model is different from the color of the third virtual model.

[0082] The generating module 130 is used to generate the processing control information of the to-be-processed specimen based on the first virtual model and the third virtual model after being nested.

[0083] The control module 140 is used to control a preset tool to process the test piece to be processed based on the processing control information to obtain a target aviation precision component.

[0084] It should be noted that technicians in the relevant technical field can clearly understand that for the convenience and simplicity of description, the specific working process of the above-described device and each module can refer to the process in the aforementioned CNC machining control method embodiment of aviation precision components, and will not be repeated here.

[0085] The CNC machining control device 100 for aviation precision components provided in the above embodiment can be implemented in the form of a computer program. The computer program can be used in Figure 3 The system is run on the terminal device 200 shown.

[0086] See also Figure 3 , Figure 3 The present invention provides a schematic block diagram of the structure of a terminal device 200 according to an embodiment of the present application. The terminal device 200 includes a processor 201 and a memory 202. The processor 201 and the memory 202 are connected via a device bus 203, wherein the memory 202 may include a non-volatile storage medium and an internal memory.

[0087] The non-volatile storage medium can store a computer program. The computer program includes program instructions, and when the program instructions are executed by the processor 201, the processor 201 can execute any of the above-mentioned numerical control machining control methods for aviation precision components.

[0088] The processor 201 is used to provide computing and control capabilities to support the operation of the entire terminal device 200.

[0089] The internal memory provides an environment for the operation of the computer program in the non-volatile storage medium. When the computer program is executed by the processor 201, the processor 201 can execute any of the above-mentioned CNC machining control methods for aviation precision components.

[0090] Those skilled in the art will understand that Figure 3 The structure shown in the figure is only a block diagram of a partial structure related to the scheme of the present application, and does not constitute a limitation on the terminal device 200 involved in the scheme of the present application. The specific terminal device 200 may include more or fewer components than shown in the figure, or combine certain components, or have a different component arrangement.

[0091] It should be understood that the processor 201 may be a central processing unit (CPU), and the processor 201 may also be other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. Among them, the general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc.

[0092] In some embodiments, the processor 201 is used to run a computer program stored in the memory to implement the following steps:

[0093] After fixing the specimen to be processed on a designated fixture, obtaining a three-dimensional model consisting of the specimen to be processed and the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture;

[0094] The third virtual model corresponding to the target aviation precision component is embedded in the first virtual model; the color of the first virtual model is different from the color of the third virtual model;

[0095] Generate processing control information of the test piece to be processed based on the first virtual model and the third virtual model after being nested;

[0096] Based on the processing control information, a preset tool is controlled to process the test piece to be processed to obtain a target aviation precision component.

[0097] It should be noted that technicians in the relevant field can clearly understand that for the convenience and simplicity of description, the specific working process of the terminal device 200 described above can refer to the process of the aforementioned CNC machining control method for aviation precision components, and will not be repeated here.

[0098] An embodiment of the present application also provides a computer-readable storage medium, which stores a computer program. When the computer program is executed by one or more processors, the one or more processors implement the CNC machining control method for aviation precision components as provided in the embodiment of the present application.

[0099] The computer-readable storage medium may be an internal storage unit of the terminal device 200 in the aforementioned embodiment, such as a hard disk or memory of the terminal device 200. The computer-readable storage medium may also be an external storage device of the terminal device 200, such as a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, a flash card (Flash Card), etc. equipped with the terminal device 200.

[0100] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed in the present application, and these modifications or replacements should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A CNC machining control method for aviation precision components, characterized in that: include: After fixing the specimen to be processed on a designated fixture, obtaining a three-dimensional model consisting of the specimen to be processed and the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture; The third virtual model corresponding to the target aviation precision component is embedded in the first virtual model; the color of the first virtual model is different from the color of the third virtual model; Generate processing control information of the test piece to be processed based on the first virtual model and the third virtual model after being nested; Controlling a preset tool based on the processing control information to process the test piece to be processed to obtain a target aviation precision component; The step of generating processing control information of the test piece to be processed based on the nested first virtual model and the third virtual model includes: Performing finite element segmentation processing on the first virtual model to obtain an initial finite element model corresponding to the first virtual model; Determine a target finite element unit on the initial finite element model based on the first virtual model and the third virtual model after nesting; wherein the target finite element unit includes a cutting part; For each of the target finite element units, obtaining the volume of the cutting portion of the target finite element unit; Determine the cutting order of each target finite element unit based on the volume of the cutting part of each target finite element unit, and for each target finite element unit, mark the cutting order of the target finite element unit on the target finite element unit to obtain a target finite element model; the cutting order of each target finite element unit is inversely proportional to its corresponding cutting volume; For each of the target finite element units, the target cutting control parameter information of the target finite element unit is generated based on a preset cutting control parameter information generation method, and the cutting control parameter information is labeled based on the cutting order corresponding to the target finite element unit; the cutting control parameter information after each labeling and the target finite element model constitute the processing control information.

2. The CNC machining control method for aviation precision components according to claim 1, characterized in that: The obtaining of the volume of the cutting portion of the target finite element unit includes: Extracting the target finite element unit in the first virtual model, and extracting the target nesting part nested in the target finite element unit in the third virtual model; The difference between the volume of the target finite element unit and the volume of the target nesting portion is determined as the volume of the cutting portion of the target finite element unit.

3. The CNC machining control method for aviation precision components according to claim 1, characterized in that: The method for generating target cutting control parameter information of the target finite element unit based on a preset cutting control parameter information generation method comprises: Acquiring cutting parameter threshold information in a database based on the material information of the test piece to be processed; the cutting parameter threshold information includes threshold ranges of multiple cutting parameters; For each of the cutting parameters, a preset number of parameter values ​​are extracted within the threshold range of the cutting parameter to obtain a parameter value set of the cutting parameter; wherein the difference between any two adjacent parameter values ​​in the parameter value sequence obtained after arranging the parameter values ​​from small to large is equal; Performing a Cartesian product operation on the parameter value sets corresponding to the respective cutting parameters to obtain a plurality of initial cutting control parameter sets; For each of the initial cutting control parameter sets, based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, a virtual tool is controlled to perform cutting processing on the target finite element unit, and during the process of the virtual tool performing cutting processing on the target finite element unit, the running trajectory information and posture information of the virtual tool are recorded, and the deformation amount corresponding to the to-be-processed specimen under the initial cutting control parameter set is obtained; wherein the virtual tool corresponds to the tool; Determine the initial cutting control parameter set corresponding to the minimum deformation amount as the target cutting control parameter set, and determine the target cutting control parameter set, the running trajectory information corresponding to the target cutting control parameter set, and the posture information corresponding to the target cutting control parameter set as the target cutting control parameter information of the target finite element unit.

4. The CNC machining control method for aviation precision components according to claim 3, characterized in that: The step of obtaining the deformation amount of the test piece to be processed corresponding to the initial cutting control parameter set includes: Before controlling a virtual tool to perform cutting processing on the target finite element unit based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, respectively acquiring first position information of each of the finite element units; After controlling the virtual tool to perform cutting processing on the target finite element unit based on the initial cutting control parameter set and the target nested position of the third virtual model on the target finite element unit, respectively acquiring second position information of each of the finite element units; For each of the finite element units, determining a displacement of the finite element unit based on the first position information and the second position information corresponding to the finite element unit; The displacements of the finite element units are added together to obtain the deformation amount of the test piece to be processed corresponding to the initial cutting control parameter set.

5. The CNC machining control method for aviation precision components according to claim 1, characterized in that: The method of controlling a preset tool based on the processing control information to process the test piece to be processed to obtain a target aviation precision component includes: For each of the target finite element units, based on the cutting order and cutting control parameter information corresponding to the target finite element unit, the virtual tool is controlled to cut the corresponding part of the target finite element unit on the first virtual model, and in the process of controlling the virtual tool to perform cutting, the tool is synchronously controlled to cut the corresponding part of the target finite element unit on the specimen to be processed; after the cutting process of the corresponding part of each of the target finite element units on the specimen to be processed is completed, the target aviation precision component is obtained.

6. A numerical control machining control device for aviation precision components, characterized in that: include: An acquisition module is used to obtain a three-dimensional model composed of the specimen to be processed and the designated fixture after the specimen to be processed is fixed on the designated fixture; the three-dimensional model includes a first virtual model and a second virtual model, the first virtual model corresponds to the specimen to be processed, and the second virtual model corresponds to the designated fixture; A model processing module, used for embedding a third virtual model corresponding to a target aviation precision component into the first virtual model; the color of the first virtual model is different from the color of the third virtual model; A generating module, used for generating processing control information of the to-be-processed specimen based on the first virtual model and the third virtual model after being nested; A control module, used for controlling a preset tool to process the test piece to be processed based on the processing control information to obtain a target aviation precision component; The step of generating processing control information of the test piece to be processed based on the nested first virtual model and the third virtual model includes: Performing finite element segmentation processing on the first virtual model to obtain an initial finite element model corresponding to the first virtual model; Determine a target finite element unit on the initial finite element model based on the first virtual model and the third virtual model after nesting; wherein the target finite element unit includes a cutting part; For each of the target finite element units, obtaining the volume of the cutting portion of the target finite element unit; Determine the cutting order of each target finite element unit based on the volume of the cutting part of each target finite element unit, and for each target finite element unit, mark the cutting order of the target finite element unit on the target finite element unit to obtain a target finite element model; the cutting order of each target finite element unit is inversely proportional to its corresponding cutting volume; For each of the target finite element units, the target cutting control parameter information of the target finite element unit is generated based on a preset cutting control parameter information generation method, and the cutting control parameter information is labeled based on the cutting order corresponding to the target finite element unit; the cutting control parameter information after each labeling and the target finite element model constitute the processing control information.

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