Aerodynamic load loading device and method for compressor blade and medium
By designing a pneumatic load loading device for compressor blades, the problem of difficulty in simulating the non-uniform aerodynamic load on the surface of the blade in the prior art is solved, and the accurate simulation and uniform aerodynamic load are achieved, reducing the cost and cycle of airworthiness verification.
Patent Information
- Application Number
- CN202311579127.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-11-23
- Publication Date
- 2025-05-23
AI Technical Summary
The prior art is difficult to effectively simulate the non-uniform aerodynamic load on the surface of the compressor blades, which makes it difficult for part-level tests to truly reflect the operating environment and cannot be directly used as evidence of airworthiness compliance. Multiple rounds of long-cycle and high-cost machine tests are required.
A pneumatic load loading device is designed, including an adjustable electromagnetic generation module, a load generation module, a load application module and a processor. The electric field is converted into a variable magnetic field through the electromagnetic generation module, and the load output by the load generation module is controlled to achieve uniform loading of the target load.
It realizes accurate simulation of the aerodynamic load on the surface of the blade, can carry out part-level tests such as low cycle fatigue, reduces the work items of the entire machine level verification, and reduces the cycle and cost of airworthiness verification.
Smart Images
Figure CN120028028A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of aerodynamic load structure testing, and in particular to an aerodynamic load loading method, and more specifically to an aerodynamic load loading device, method and medium for compressor blades. Background Art
[0002] Compressor blades are one of the most important components in a compressor. Their main function is to change the speed and direction of the airflow. During the operation of an aircraft engine, flow path components represented by compressor blades are subjected to huge aerodynamic loads and centrifugal loads. When calculating blade loads, it is necessary to consider the aerodynamic loads and mechanical loads borne by the blades. Among them, aerodynamic loads include factors such as airflow static pressure, airflow pressure, and rotational inertia force, while mechanical loads include factors such as centrifugal force, inertia force, and friction force.
[0003] The fatigue life of compressor blades meeting the safety requirements of airworthiness regulations is one of the necessary conditions for aircraft engines to obtain type certificates. Aircraft engine airworthiness regulations also stipulate a series of requirements for the life of flow path parts through clauses such as 33.87 endurance test, 33.88 overtemperature test, and 33.90 initial maintenance inspection. In order to show that the fatigue life of the blades meets the airworthiness requirements, using compressor blades to conduct tests directly on the component test bench is an intuitive and effective compliance verification method.
[0004] However, compressor blades are subjected to relatively complex surface aerodynamic loads during operation. Part-level tests on blades should simulate and restore the complex surface loads. At present, there is a lack of load loading methods at the blade part level in China, especially non-uniform load loading methods. In the life verification of compressor blades, a large number of simulated characteristic test pieces are used as test objects. However, simulated characteristic test pieces are designed based on the characteristic structure and stress distribution of real parts, but because the degree of restoration of their characteristic structures is often not ideal, the life test of simulated characteristic test pieces is difficult to directly use as airworthiness compliance evidence, and most of them are only used for research and development tests. As a result, multiple rounds of long-term, high-cost whole-machine tests are still required to verify the life of parts.
[0005] At present, no researchers in this field have conducted research on the loading of non-uniform aerodynamic loads on blades, nor is there any relevant public information. Therefore, it is difficult to simulate the aerodynamic loads on the surface when conducting low-cycle fatigue part-level tests on blades. If only radial loads are loaded using a fixture, it is difficult to restore the actual operating environment and cannot reflect the impact of surface loads on blade life. Low-cycle fatigue, also known as low-cycle fatigue, refers to the process in which a material gradually accumulates permanent damage within a certain number of cycles under the action of a large-amplitude alternating load.
[0006] In summary, there is an urgent need for a method and device for aerodynamic load loading test on blade surface in this field. The method and device can simulate the aerodynamic load on blade surface, and can reduce the work items of whole machine level verification by carrying out a series of part-level tests such as low cycle fatigue, thereby reducing the cycle and cost of airworthiness verification. Summary of the invention
[0007] A brief summary of one or more aspects is given below to provide a basic understanding of these aspects. This summary is not an exhaustive overview of all conceived aspects, and is neither intended to identify the key or critical elements of all aspects nor to define the scope of any or all aspects. Its only purpose is to give some concepts of one or more aspects in a simplified form as a prelude to a more detailed description given later.
[0008] Taking into account the defects and difficulties in the prior art, this application proposes a loading test method for aerodynamic loads on the surface of compressor blades. With the help of this loading method, the problem of difficulty in loading non-uniform aerodynamic loads on the blade surface in the part-level test of aerodynamic loads can be solved. This will enable a series of part-level tests such as low-cycle fatigue to be carried out smoothly, reduce the work items for verification at the whole machine level, reduce the cycle and cost of airworthiness verification, and provide strong technical support for multiple durability airworthiness tests.
[0009] According to a first aspect of the present application, an aerodynamic load applying device for a compressor blade is described.
[0010] The aerodynamic load loading device includes: an adjustable electromagnetic generating module, a load generating module, a load applying module and a processor, wherein the adjustable electromagnetic generating module is configured to convert an electric field into a variable magnetic field to control the distance between the adjustable electromagnetic generating module and the load generating module, the load generating module is configured to generate and output an output load, and control the distance between the adjustable electromagnetic generating module and the load applying module so that the output load is equal to a target load, the load applying module is configured to apply the target load to the blade, thereby achieving the loading of the target load, and the processor is configured to control the adjustable electromagnetic generating module, the load generating module and the load applying module so that the output load is equal to the target load.
[0011] According to a preferred embodiment of the present application, the load generating module includes: a precession screw, configured to adjust the precession distance of the load generating module; a load-bearing chassis, configured to carry the load generating module; a sliding vane distance meter, configured to measure the distance between the load generating module and an adjustable electromagnetic generating module to adjust the precession distance; a directional wheel, configured to adjust the precession of the load generating module based on the precession distance; a permanent magnet, configured to move toward the electromagnetic generating module under the drive of the precession screw; and a load transfer rod, configured to transfer the output load to the load application module.
[0012] According to a preferred embodiment of the present application, the adjustable electromagnetic generation module includes an adjustable disc electromagnet, which is configured to generate a variable magnetic field that repel the permanent magnet so as to control the distance between the permanent magnet and the load generation module.
[0013] According to a preferred embodiment of the present application, the load application module includes: an upper pad, configured to receive the output load from the load generating module; a spring group, configured to absorb and transmit the output load; a lower pad; configured to receive the output load from the spring group; a pressure sensor gasket, configured to measure the output load and transmit it to the processor for feedback control; and a heat-resistant gasket having elasticity to be configured for uniform loading of the output load.
[0014] According to a preferred embodiment of the present application, the load application module is further configured to: apply target loads corresponding to corresponding unit grids to the corresponding unit networks respectively based on the unit grid division of the blade.
[0015] According to a second aspect of the present application, an aerodynamic load loading method for compressor blades is disclosed, which is implemented by using the aerodynamic load loading device as described above.
[0016] The method comprises the following steps:
[0017] Step S1: converting the electric field into a variable magnetic field via the adjustable electromagnetic generating module to control the distance between the adjustable electromagnetic generating module and the load generating module;
[0018] Step S2: generating and outputting an output load via the load generation module;
[0019] Step S3: controlling the distance between the adjustable electromagnetic generating module and the load generating module so that the output load is equal to the target load;
[0020] Step S4: applying the target load to the blade via the load applying module, thereby achieving the loading of the target load, wherein
[0021] The processor controls the above steps S1 to S4 to achieve the loading of the target load.
[0022] According to a preferred embodiment of the present application, step S2 further includes: transferring the output load to the load applying module via a load transfer rod of the load generating module.
[0023] According to a preferred embodiment of the present application, step S3 also includes: adjusting the precession distance of the load generating module via the precession screw of the load generating module; measuring the distance between the load generating module and the adjustable electromagnetic generating module via the sliding vane rangefinder of the load generating module to adjust the precession distance; adjusting the precession of the load generating module based on the precession distance via the directional wheel of the load generating module; and moving the permanent magnet of the load generating module toward the electromagnetic generating module driven by the precession screw.
[0024] According to a preferred embodiment of the present application, step S1 further includes: generating a variable magnetic field that repel the permanent magnet via the adjustable electromagnetic generating module to control the distance between the permanent magnet and the load generating module.
[0025] According to a preferred embodiment of the present application, step S4 further includes: applying target loads corresponding to corresponding unit grids to the corresponding unit networks based on the unit grid division of the blade.
[0026] According to a third aspect of the present application, a computer-readable storage medium having stored thereon a computer program including instructions for causing the pneumatic load loading device as described above to perform the steps of the pneumatic load loading method as described above is described.
[0027] To achieve the foregoing and related ends, the one or more aspects include the features fully described below and particularly pointed out in the appended claims. The following description and drawings set forth in detail certain illustrative features of the one or more aspects. However, these features are merely indicative of several of the various ways in which the principles of the various aspects may be employed, and this description is intended to cover all such aspects and their equivalents. BRIEF DESCRIPTION OF THE DRAWINGS
[0028] In order to understand in detail the manner in which the above-stated features of the present application are used, a more specific description of the above briefly summarized contents may be made with reference to various aspects, some of which are illustrated in the accompanying drawings. However, it should be noted that the accompanying drawings illustrate only certain typical aspects of the present application and should not be considered to limit its scope, as the present description may allow for other equally effective aspects.
[0029] In the attached picture:
[0030] Figure 1 is a schematic structural diagram illustrating a compressor blade aerodynamic load loading device according to a specific embodiment of the present application;
[0031] Figure 2Is the explanation Figure 1 A schematic diagram of the detailed structure of the compressor blade aerodynamic load loading device shown in ; and
[0032] Figure 3 The flowchart illustrates a method for applying aerodynamic loads to compressor blades according to a specific embodiment of the present application. DETAILED DESCRIPTION
[0033] The detailed description set forth below in conjunction with the accompanying drawings is intended as a description of various configurations and is not intended to represent the only configurations in which the concepts described herein may be practiced. This detailed description includes specific details to provide a thorough understanding of the various concepts. However, it will be apparent to those skilled in the art that these concepts may be practiced without these specific details. In some instances, well-known components are shown in block diagram form in order to avoid diluting such concepts.
[0034] It is to be understood that other embodiments would be apparent based on the present disclosure, and that system, structural, process, or mechanical changes may be made without departing from the scope of the present disclosure.
[0035] As mentioned above, the existing aerodynamic load loading scheme only uses test pieces, which is difficult to truly simulate the load conditions on the blade surface. Therefore, it is difficult to directly use it as evidence of airworthiness compliance. Subsequent rounds of long-term, high-cost whole-machine tests are still required to verify the life of parts. The present application specifically proposes an improved aerodynamic load loading device and method for compressor blades. The loading device and method can solve the problem that the non-uniformly distributed aerodynamic load on the blade surface is difficult to load in part-level tests, and the structure is relatively simple, easy to implement, and has good practicality.
[0036] Note that although the following Figures 1 to 3 The operations described in the present invention are presented in a particular order and / or as being performed by example components, but it should be understood that the order of these actions and the components performing the actions may vary depending on the implementation. In addition, it should be understood that the following actions or functions may be performed by a specially programmed processor, a processor executing specially programmed software or computer-readable media, or by any other combination of hardware components and / or software components capable of performing the described actions or functions.
[0037] Figure 1 The structure of the compressor blade aerodynamic load loading device according to a specific embodiment of the present application is explained in Figure 2 It explains how Figure 1 Detailed architecture of the compressor blade aerodynamic load applying device shown in .
[0038] like Figure 1 As shown in , the pneumatic load loading device mainly includes the following components:
[0039] Processor 1, load generation module 2, adjustable electromagnetic generation module 3 and load application module 4. Figure 1 and 2 The detailed uses of the various components of the pneumatic load applying device according to the present application are described in detail.
[0040] As a non-limiting example, the core structure of the electromagnetic generating module 3 may be an adjustable disc electromagnet, which can generate a magnetic field direction that is mutually exclusive with the permanent magnet 26 in the load generating module 2 , thereby controlling the rightward precession of the load generating module 2 .
[0041] The load generating module 2 used in the present application mainly includes: a precession screw 21 , a load-bearing chassis 22 , a sliding vane distance meter 23 , a directional wheel 24 , a wheel axle 25 , a permanent magnet 26 , and a load transfer rod 27 .
[0042] Under the control of the processor 1, the precession distance of each precession screw 21 of the load generating module 2 can be adjusted, and the precession distance is obtained according to the measurement and solution of the sliding vane distance meter 23. Under the precession of the precession screw 21, a load is generated and the load-bearing chassis 22 and the permanent magnet 26 are driven to move to the right, as shown in FIG. Figure 1 and 2 as shown in .
[0043] Under the control of the processor 1, the target distance between the permanent magnet 26 and the electromagnetic generating module 3 can be calculated according to the set target load and the repulsive magnetic field strength of the electromagnetic generating module 3. This calculation method is well known in the art, so it will not be described here in detail to avoid affecting the description of the main technical solution.
[0044] As a non-limiting example, the permanent magnet 26 constrains the movement direction through the wheel axle and the directional wheel made of non-magnetic titanium-aluminum alloy, and further outputs the load to the load application module through the load transfer rod 26 made of non-magnetic titanium-aluminum alloy. The actual distance between the permanent magnet 26 and the electromagnetic generating module 3 is measured by the sliding vane distance meter 23 and fed back to the processor 1 in real time.
[0045] On the basis of calculating the target distance and measuring the actual mutual exclusion distance between the permanent magnet 26 and the electromagnetic generating module 2 by the sliding vane distance meter 23, the distance can be adjusted under the control of the processor 1 so that the load output by the load generating module 2 is equal to the set target load. The load applying module 4 can then apply the target load to the blade, thereby achieving the correct loading of the aerodynamic load of the blade.
[0046] The load applying module 4 used in the present application mainly includes: an upper pad 41 , a spring group 42 , a lower pad 43 , a pressure sensor gasket 44 , and a heat-resistant gasket 45 .
[0047] The upper pad 41 can transmit the output load from the load transfer rod 27 and absorb the potential energy of the output load through the spring group 42, and transmit it to the lower pad 43. The load value output by the pressure sensor gasket 44 is fed back to the processor 1 in real time, and finally the load is applied to the compressor blade through the heat-resistant gasket 45.
[0048] The heat-resistant gasket 45 may have elasticity within a certain range, so that the load can be evenly distributed when the blade has a surface curvature.
[0049] The blade surface aerodynamic load loading device described in the present application can realize automatic calculation, control and monitoring of the load of a unit grid, and multiple groups of blade surface load loading devices can form a detachable parallel blade surface aerodynamic load loading array according to the size and test accuracy of the blade test piece.
[0050] The output load value can be fed back to the processor 1 in real time through the pressure sensor gasket 44. If the fed-back load value (i.e., the output load) is inconsistent with the target load, the processor 1 can adjust the precession distance of each precession screw 21 according to the difference between the fed-back load and the target load so that the output load is equal to the target load, thereby accurately achieving uniform loading of the pneumatic load.
[0051] As described above, the aerodynamic load loading device of the present application can completely solve the problem of difficulty in loading the non-uniformly distributed aerodynamic load on the blade surface in the part-level test. Moreover, the device has a simple structure, low cost, and good practicality.
[0052] Figure 3 A flowchart of a method for applying aerodynamic loads to compressor blades according to a specific embodiment of the present application is explained in FIG. The detailed implementation process of the method for applying aerodynamic loads is described in detail below in conjunction with the above-mentioned aerodynamic load applying device.
[0053] Before executing the startup load loading method of the present application, it is necessary to select a suitable blade surface pneumatic load loading device according to the size of the blade test piece and the test accuracy test requirements to assemble and form a parallel blade surface pneumatic load loading array. Since the heat-resistant gasket 45 of the load application module 4 has a certain elasticity, it can fit well with the blade surface.
[0054] First, at step S1, the electric field is converted into a variable magnetic field by the adjustable electromagnetic generating module 3. The magnetic field is mutually exclusive with the load generating module 2, and can control the movement of the permanent magnet 26 toward the electromagnetic generating module, thereby controlling the distance between the electromagnetic generating module 3 and the load generating module.
[0055] Next, at step S2 , the load generation module 2 can generate and output an output load.
[0056] Next, at step S3, when the output load is inconsistent with the set target load, the output load needs to be adjusted by adjusting the distance between the load generating module 2 and the electromagnetic generating module 3. The ultimate goal is to make the output load equal to the set target load.
[0057] This adjustment is mainly achieved through two aspects.
[0058] First, as mentioned above, the electromagnetic generating module 3 can generate a variable repulsive magnetic field, thereby controlling the movement of the permanent magnet toward the electromagnetic generating module.
[0059] Secondly, the rightward movement (precession distance) of the permanent magnet 26 to the electromagnetic generating module 3 can also be controlled by the precession screw 21. This movement control is performed under the control of the processor 1. When the output load value fed back to the processor by the pressure sensor gasket 44 of the load applying module 4 in real time is not equal to the set target load, the processor 1 can adjust the precession distance of the precession screw 21 according to the difference between the two, and further control the rightward movement of the permanent magnet 26 in combination with the repulsive magnetic field strength of the electromagnetic generating module 3, so as to accurately adjust the output load output by the load generating module 2 so that the output load is equal to the set target load.
[0060] Finally, in step S4, the output load (which is equal to the target load at this time) can be applied to the unit grid of the blade through the load application module, thereby achieving uniform loading of the target load.
[0061] This aerodynamic load loading method can solve the problem of difficulty in loading non-uniform loads on the blade surface in part-level tests, and can realize automatic calculation, control and monitoring of loads on unit grids. In addition, this method has high accuracy, is simple and easy to use, and has good practicality.
[0062] Furthermore, multiple sets of blade surface load loading devices can form a detachable parallel blade surface aerodynamic load loading array according to the size and test accuracy of the blade test piece, so that it can be used repeatedly, greatly reducing the production cost.
[0063] As a non-limiting example, the unit grid size used in this application can be designed according to the size and test accuracy of the blade test piece. The size of the unit grid does not affect the implementation of the main technical solution of this application. For example, a series of blade surface load loading devices with different unit grid sizes can be designed and manufactured, such as 2mm*2mm, 3mm*3mm, 5mm*5mm, 10mm*10mm, etc., and a combination of grids of different sizes can be selected according to the load setting distribution of the blade to achieve the effect of improving the local load accuracy.
[0064] The heat-resistant gasket used in the present application can withstand a long-term working environment of up to 700 degrees Celsius and has good adaptability and practicality.
[0065] According to various aspects, elements, or any part of elements, or any combination of elements of the present disclosure, a "processing system" including one or more processors can be implemented. Examples of processors include: microprocessors, microcontrollers, digital signal processors (DSPs), field programmable gate arrays (FPGAs), programmable logic devices (PLDs), state machines, gated logic, discrete hardware circuits, and other suitable hardware configured to perform various functionalities described throughout the present disclosure. One or more processors in a processing system can execute software. Software should be broadly interpreted as meaning instructions, instruction sets, codes, code segments, program codes, programs, subroutines, software modules, applications, software applications, software packages, routines, subroutines, objects, executables, threads of execution, procedures, functions, etc., whether it is described in software, firmware, middleware, microcode, hardware description language, or other terms. Software may reside on a computer-readable medium. The computer-readable medium may be a non-transient computer-readable medium. As examples, non-transitory computer-readable media include: magnetic storage devices (e.g., hard disks, floppy disks, magnetic strips), optical disks (e.g., compact disks (CDs), digital versatile disks (DVDs)), smart cards, flash memory devices (e.g., memory cards, memory sticks, key drives), random access memory (RAM), read-only memory (ROM), programmable ROM (PROM), erasable PROM (EPROM), electrically erasable PROM (EEPROM), registers, removable disks, and any other suitable medium for storing software and / or instructions that can be accessed and read by a computer. As examples, computer-readable media may also include carrier waves, transmission lines, and any other suitable medium for transmitting software and / or instructions that can be accessed and read by a computer. The computer-readable medium may reside in the processing system, be external to the processing system, or be distributed across multiple entities including the processing system. The computer-readable medium may be implemented in a computer program product. As examples, a computer program product may include a computer-readable medium in packaging materials. Those skilled in the art will recognize how to best implement the described functionality presented throughout this disclosure depending on the specific application and the overall design constraints imposed on the overall system.
[0066] It should be understood that the specific order or hierarchy of steps in the disclosed methods is an illustration of an exemplary process. Based on design preferences, it should be understood that the specific order or hierarchy of steps in the methods or methodologies described herein may be rearranged. The attached method claims present elements of the various steps in a sample order and are not meant to be limited to the specific order or hierarchy presented unless specifically stated herein.
[0067] The previous description is provided to enable any person skilled in the art to practice the various aspects described herein. Various modifications to these aspects will be readily apparent to those skilled in the art, and the universal principles defined herein may be applied to other aspects. Therefore, the claims are not intended to be limited to the various aspects shown herein, but should be granted the full scope consistent with the language of the claims, wherein the singular reference to the element is not intended to mean "there is and only one" (unless specifically stated) but "one or more". Unless specifically stated otherwise, the term "some" refers to one or more. The phrase "at least one" quoting a list of items refers to any combination of these items, including a single member. As an example, "at least one of a, b or c" is intended to cover: at least one a; at least one b; at least one c; at least one a and at least one b; at least one a and at least one c; at least one b and at least one c; and at least one a, at least one b and at least one c. The elements of the various aspects described throughout this disclosure are all structurally and functionally equivalent schemes currently or hereafter known to those of ordinary skill in the art, and are expressly incorporated herein by reference, and are intended to be covered by the claims. Moreover, nothing disclosed herein is intended to be dedicated to the public regardless of whether such disclosure is explicitly recited in the claims.
Claims
1. An aerodynamic load loading device for compressor blades, It is characterized in that The pneumatic load loading device includes: an adjustable electromagnetic generating module, a load generating module, a load applying module and a processor. in, The adjustable electromagnetic generating module is configured to convert an electric field into a variable magnetic field to control the distance between the adjustable electromagnetic generating module and the load generating module. The load generation module is configured to generate and output an output load, and to make the output load equal to the target load by controlling the distance between the load generation module and the adjustable electromagnetic generation module. The load applying module is configured to apply the target load to the blade, thereby achieving the loading of the target load, and The processor is configured to control the adjustable electromagnetic generation module, the load generation module, and the load application module so that the output load is equal to a target load.
2. The pneumatic load applying device according to claim 1, It is characterized in that The load generation module comprises: a precession screw configured to adjust the precession distance of the load generating module; a load-bearing chassis configured to carry the load generating module; A sliding vane rangefinder configured to measure the distance to the adjustable electromagnetic generating module to adjust the precession distance; a directional wheel configured to adjust the precession of the load generating module based on the precession distance; a permanent magnet, configured to move toward the electromagnetic generating module under the drive of the precession screw; and A load transfer rod is configured to transfer the output load to the load application module.
3. The pneumatic load applying device according to claim 2, It is characterized in that The adjustable electromagnetic generation module includes an adjustable disc electromagnet, which is configured to generate a variable magnetic field that repel the permanent magnet so as to control the distance between the disc electromagnet and the load generation module.
4. A pneumatic load applying device as claimed in any one of claims 1 to 3, It is characterized in that The load application module comprises: an upper pad configured to receive the output load from the load generating module; a spring assembly configured to absorb and transmit the output load; A lower pad; configured to receive the output load from the spring group; a pressure sensor pad configured to measure the output load and transmit it to the processor for feedback control; and The heat-resistant gasket has elasticity and is configured to uniformly load the output load.
5. A pneumatic load applying device as claimed in any one of claims 1 to 3, It is characterized in that The load application module is further configured to: Based on the unit mesh division of the blade, target loads corresponding to corresponding unit meshes are applied to the corresponding unit meshes respectively.
6. A method for applying an aerodynamic load to a compressor blade using the aerodynamic load applying device according to any one of claims 1 to 5, It is characterized in that The method comprises the following steps: Step S1: converting the electric field into a variable magnetic field via the adjustable electromagnetic generating module to control the distance between the adjustable electromagnetic generating module and the load generating module; Step S2: generating and outputting an output load via the load generation module; Step S3: controlling the distance between the adjustable electromagnetic generating module and the load generating module so that the output load is equal to the target load; Step S4: applying the target load to the blade via the load applying module, thereby achieving the loading of the target load, wherein The processor controls steps S1 to S4 to achieve the loading of the target load.
7. The pneumatic load loading method according to claim 6, It is characterized in that The step S2 further comprises: The output load is transmitted to the load applying module via the load transmitting rod of the load generating module.
8. The pneumatic load loading method according to claim 6, It is characterized in that The step S3 further comprises: adjusting the precession distance of the load generating module via the precession screw of the load generating module; Measuring the distance between the load generation module and the adjustable electromagnetic generation module via a sliding vane distance meter of the load generation module to adjust the precession distance; adjusting the precession of the load generation module based on the precession distance via a directional wheel of the load generation module; and The permanent magnet of the load generation module moves toward the electromagnetic generation module under the drive of the precession screw.
9. The pneumatic load loading method according to claim 8, It is characterized in that The step S1 further comprises: The adjustable electromagnetic generating module generates a variable magnetic field that repel the permanent magnet to control the distance between the permanent magnet and the load generating module.
10. The pneumatic loading method according to any one of claims 6 to 9, It is characterized in that The step S4 further comprises: Based on the unit mesh division of the blade, target loads corresponding to corresponding unit meshes are applied to the corresponding unit meshes respectively.
11. A computer-readable storage medium having stored thereon a computer program including instructions for causing the pneumatic load loading device according to any one of claims 1 to 5 to perform the steps of the pneumatic load loading method according to any one of claims 6 to 10.