Complex curved surface gradient pressure static test load loading method and device, computer equipment and medium

Abstract

The embodiment of the invention provides a loading method and device for a gradient pressure static test load of a complex curved surface, computer equipment and a medium, and the method comprises the following steps: obtaining geometric model data and gradient pressure distribution data of a to-be-tested complex curved surface; dividing the complex curved surface into a plurality of loading partitions, generating partition definition data, and determining loading point quantity data for each loading partition; performing finite element analysis based on various data, and calculating and outputting partition resultant force data; calculating coordinates of a pressure center based on the gradient pressure distribution data and the geometric model data corresponding to the loading partition, and taking the coordinates of the pressure center as theoretical action point position data of the loading partition; and performing secondary static equivalent processing, generating executable loading scheme data of the loading partition, and integrating the executable loading scheme data. The gradual change pressure intensity of each partition is equivalent to a resultant force through finite element calculation, the accurate load size and direction are obtained, and the loading error is reduced.

Description

Technical Field

[0001] This invention relates to the field of aircraft load technology, and in particular to a method, apparatus, computer equipment, and medium for loading a static load for a complex curved surface with gradually varying pressure. Background Technology

[0002] In static strength tests of aircraft structures, the limiting loads for some structures are given as gradually varying pressures along the flight direction. In structural strength tests, the common loading method is to attach adhesive tape to the surface of the test specimen and apply loads using a combination of levers. For pressure-bearing curved surfaces, a common loading method is to attach tension / compression pads or wooden blocks to the surface of the test specimen and apply loads using a combination of levers. However, because the tested structure is a complex curved surface, and the pressure at each point is the normal direction of the surface, load calculations are very complex. Therefore, a load handling method is needed to treat the gradually varying loads as nodal loads before designing the loading lever system, so that the load conditions of the aircraft structure can be as close as possible to the original test requirements.

[0003] The conventional approach to handling gradually varying pressure on curved surfaces is to divide the surface into several regions, roughly calculate the average of the gradually varying pressure in each region to approximate a uniformly distributed pressure, and then multiply the area by the uniformly distributed pressure to obtain the total load. A load direction and point of application are then estimated before proceeding with lever design. However, this calculation method is extremely difficult for complex curved surfaces, and the uncertainty of the load direction and point of application leads to significant errors in the subsequent loading system design. Summary of the Invention

[0004] In view of this, embodiments of the present invention provide a method for applying gradually varying pressure static test loads on complex curved surfaces, to solve the technical problem of complex load calculations when the aircraft structure is a complex curved surface in the prior art. The method includes: Obtain the geometric model data of the complex curved surface to be tested and the corresponding gradual pressure distribution data of the geometric model data; Based on the geometric model data and the physical constraints of the experimental loading, the complex surface is divided into multiple loading partitions, partition definition data is generated, and the number of loading points for each loading partition is determined. Based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, finite element analysis is performed to calculate and output the resultant force data of each loading partition, wherein the resultant force data includes the resultant force vector and the resultant moment. For each loading zone, based on the gradual pressure distribution data and the geometric model data corresponding to the loading zone, the coordinates of the pressure center of the loading zone are calculated, and the coordinates of the pressure center are used as the theoretical point of action location data of the loading zone. For each loading partition, based on the corresponding resultant force data of the partition and the theoretical point of application location data, a secondary static equivalent processing is performed to generate executable loading scheme data for the loading partition. The executable loading scheme data includes the spatial locations of multiple physical loading points and the load vectors assigned to the physical loading points. The executable loading scheme data of all the loading partitions are integrated. This embodiment of the invention also provides a loading device for a static load test with gradually varying pressure on complex curved surfaces, to solve the technical problem of complex load calculation when the aircraft structure has a complex curved surface in the prior art. The device includes: The parameter acquisition module is used to acquire the geometric model data of the complex curved surface to be tested and the corresponding gradual pressure distribution data of the geometric model data; The surface partitioning module is used to divide the complex surface into multiple loading partitions based on the geometric model data and the physical constraints of the experimental loading, generate partition definition data, and determine the number of loading points for each loading partition. The finite element calculation and load extraction module is used to perform finite element analysis based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, calculate and output the partition resultant force data of each loading partition, wherein the partition resultant force data includes resultant force vector and resultant moment; The application point analysis module is used to calculate the coordinates of the pressure center of each loading partition based on the gradual pressure distribution data and the geometric model data corresponding to the loading partition, and use the coordinates of the pressure center as the theoretical application point location data of the loading partition. The resultant force secondary load processing module is used to perform secondary static equivalent processing on each loading partition based on the corresponding resultant force data of the partition and the theoretical point of application location data, to generate executable loading scheme data for the loading partition. The executable loading scheme data includes the spatial location of multiple physical loading points and the load vector allocated to the physical loading points. The data integration module is used to integrate the executable loading scheme data of all the loading partitions.

[0005] This invention also provides a computer 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 above-mentioned method for loading the static load of the arbitrarily complex curved surface with gradual pressure, thereby solving the technical problem of complex load calculation when the aircraft structure is a complex curved surface in the prior art.

[0006] This invention also provides a computer-readable storage medium storing a computer program that executes the above-described method for loading the static load of a gradually varying pressure on a complex curved surface, thereby solving the technical problem of complex load calculation when the aircraft structure is a complex curved surface in the prior art.

[0007] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least: By using finite element method to calculate the gradual pressure of each zone as an equivalent resultant force, the accurate load magnitude and direction can be obtained, thus reducing loading error. Attached Figure Description

[0008] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0009] Figure 1 This is a flowchart of a method for applying a static load in a complex curved surface with gradually varying pressure, provided by an embodiment of the present invention. Figure 2 This is a schematic diagram of the equivalent resultant force of each loading zone in the loading method for the static load of a complex curved surface with gradually varying pressure provided in the embodiments of the present invention; Figure 3 This is a schematic diagram of the load application method for the static load of a complex curved surface with gradually varying pressure provided in an embodiment of the present invention. Figure 4 This is a schematic diagram of the loading force line after the resultant force secondary load processing of the loading method for the static load of the complex curved surface gradually changing pressure provided in the embodiment of the present invention; Figure 5 This is a structural block diagram of a computer device provided in an embodiment of the present invention; Figure 6 This is a structural block diagram of a loading device for a complex curved surface gradually changing pressure static test load provided in an embodiment of the present invention. Detailed Implementation

[0010] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0011] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0012] In this embodiment of the invention, a method for applying a gradually varying pressure static test load on a complex curved surface is provided, such as... Figure 1 As shown, the method includes: Step S101: Obtain the geometric model data of the complex curved surface to be tested and the corresponding gradual pressure distribution data; Step S102: Based on the geometric model data and the physical constraints of the experimental loading, the complex surface is divided into multiple loading partitions, partition definition data is generated, and the number of loading points for each loading partition is determined. Step S103: Based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, perform finite element analysis, calculate and output the partition resultant force data of each loading partition, wherein the partition resultant force data includes resultant force vector and resultant moment; Step S104: For each loading partition, based on the gradual pressure distribution data and the geometric model data corresponding to the loading partition, calculate the coordinates of the pressure center of the loading partition, and use the coordinates of the pressure center as the theoretical point of action location data of the loading partition; Step S105: For each loading partition, based on the corresponding partition resultant force data and the theoretical point of application location data, perform secondary static equivalent processing to generate executable loading scheme data for the loading partition. The executable loading scheme data includes the spatial locations of multiple physical loading points and the load vectors assigned to the physical loading points. Step S106: Integrate the executable loading scheme data of all the loading partitions.

[0013] In practice, the number of loading points for each loading partition is determined through the following steps: The number of reference loading points is calculated based on the partition area and the preset loading point density benchmark value in the partition definition data; the surface curvature information corresponding to each loading partition in the geometric model data is obtained; the number of reference loading points is corrected based on the surface curvature information, and the number of loading points in loading partitions with surface curvature higher than a preset threshold is adjusted to be greater than the number of reference loading points.

[0014] In specific implementation, the following steps are used to perform finite element analysis based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, and to calculate and output the resultant force data of each loading partition: Based on the partition definition data, the geometric model of the corresponding region is discretized into a grid to generate a partitioned grid model; the gradual pressure distribution data is mapped to each surface element of the partitioned grid model, and the nodal force data of each surface element is calculated; within the range of the partition definition data, vector synthesis and moment synthesis are performed on all the nodal force data to calculate the resultant force vector and the resultant moment.

[0015] In specific implementation, the following steps are used to calculate the coordinates of the pressure center of the loading partition based on the gradual pressure distribution data and the geometric model data corresponding to the loading partition: Based on the geometric model data, obtain the surface geometry information corresponding to the loading partition; Based on the surface geometry information and the gradual pressure distribution data, the loading partition is discretized into multiple load micro-elements, and the micro-element area, micro-element center position and micro-element normal direction of each load micro-element are determined. Based on the gradually varying pressure distribution data, calculate the element load vector on each of the load elements; Based on the element load vectors on all the load elements and the corresponding element center positions, the element center positions are taken as the pressure centers, and the coordinates of the pressure centers are calculated.

[0016] In specific implementation, the following steps are used to perform secondary static equivalent processing based on the corresponding partition resultant force data and the theoretical point of application location data to generate executable loading scheme data for the loading partition: Obtain the resultant force data of the loading partition to be processed, the theoretical application point location data, and the feasibility constraints of the loading lever system; establish a static equivalent optimization model, wherein the static equivalent optimization model is used to optimize and decompose the resultant force data of the partition and the theoretical application point location data into multiple physically realizable loading point loads under the condition of satisfying the feasibility constraints; solve the static equivalent optimization model to obtain a set of M load vectors that satisfy all constraints and optimize the objective function, and the candidate loading point locations corresponding to the load vectors; bind the load vectors with the candidate loading point locations, and output them as the executable loading scheme data.

[0017] In practice, the static equivalent optimization model is established through the following steps: Design variables are defined, wherein the design variables are load vectors acting on M candidate loading points within the current loading partition, and M≥2; the vector sum of the M load vectors equals the resultant force vector in the partition resultant force data, and the resultant moment of the M load vectors about the point indicated by the theoretical point of application location data equals the resultant moment in the partition resultant force data is used as the core equality constraint; the magnitude and direction of each load vector satisfying the feasibility constraint condition are used as the inequality constraint; an objective function is defined, wherein the objective function is used to optimize at least one of the load distribution performance index, system energy consumption index, and direction consistency index; a static equivalent optimization model is constructed based on the core equality constraint, the inequality constraint, and the objective function.

[0018] In practice, the model is iterated through the following steps: If solving the static equivalent optimization model fails or the obtained executable loading scheme data does not meet the engineering error requirements, the number M of candidate loading points or the spatial position of the candidate loading points are adjusted, and the static equivalent optimization model is re-established and solved until executable loading scheme data that meets the requirements is obtained.

[0019] This embodiment provides a method for handling the load in a static pressure test with a complex curved surface gradually varying in pressure. The specific steps are as follows: Step 1: Data preparation.

[0020] Acquire digital geometric model data of the complex surface to be tested. This data typically originates from a 3D design model of the aircraft structure and can be in common formats such as STEP or IGES. Simultaneously, acquire the gradually varying pressure distribution data defined on this surface. This gradually varying pressure distribution data is usually a function or data field associated with the geometric model coordinates. For example, pressure P can be expressed as a function along the heading coordinate x: P = f(x), applied perpendicular to the surface normal.

[0021] Step 2: Surface partitioning and planning.

[0022] The complex curved surface is divided into several (N) loading zones. The zoning principle takes into account the following factors: (1) Geometric features: the boundaries are defined along natural features such as curvature change lines and reinforcing ribs; (2) Load gradient: the zone area is appropriately reduced in areas with drastic pressure changes; (3) Engineering feasibility: the size of a single zone should facilitate the subsequent installation of physical loading heads (such as actuator cylinder pads). Figure 2 As shown, an airfoil surface is divided into multiple loading partitions.

[0023] For each loaded partition i (i=1,2,…,N), based on its area S i Based on the preset loading point density benchmark value ρ (e.g., 1 point / 0.01 square meters), the number of loading points M is initially estimated. i =ceil(ρ* Si). Simultaneously, fine-tuning is performed based on the average curvature of the partition, appropriately increasing the number of points in areas with high curvature, ultimately determining the initial number of loading points M. i .

[0024] Step 3: Extract the resultant force of each partition using finite element analysis.

[0025] Import the geometric model and the gradually varying pressure distribution data into the finite element analysis software. For example... Figure 3 As shown, the geometric model is meshed (usually using shell elements), and the gradually varying pressure load is precisely applied to the corresponding surface elements. Displacement boundary conditions are set at the appropriate locations on the model based on the experimental support conditions.

[0026] Perform a linear static analysis. After the analysis, for each loading zone defined in step 2, perform a "free body cut" or use a script to extract all nodal reactions acting on the surface of that zone. Perform vector synthesis on these nodal forces to obtain the resultant force data for that zone, including a resultant force vector F. i (F ix , F iy, F iz ) and a resultant moment vector M about the global coordinate origin. i .

[0027] Step 4: Calculate the zone pressure center (theoretical point of application).

[0028] For each partition, a theoretically optimal single-point loading location, i.e., the pressure center, needs to be found. This point is the point of application of the resultant force of the distributed pressure, such that the effect produced when the resultant force vector passes through this point is completely equivalent to the original distributed pressure (i.e., the moment about any point is the same).

[0029] The partitioned surface is discretized into a large number of infinitesimal elements. For the j-th infinitesimal element, its area is dA. j The center point coordinates are rj The normal vector is n j The pressure at that location is P. j The force acting on this infinitesimal element is dF. j = P j ×n j ×dA j Coordinates of the pressure center r cop Solve using the following formula: r cop = (Σ( r j ×dF j ) ) / (ΣdF j ) The above formula is a vector operation and needs to be solved according to each coordinate direction.

[0030] The obtained r cop This is the theoretical point of action location for this partition. This point of action may not coincide with the geometric centroid of the partition.

[0031] Step 5: Secondary static equivalent treatment and optimization.

[0032] Since the theoretical point of application may be located inside the structure or in a location where it is inconvenient to install the loading device, and the load at a single loading point may be too large, exceeding the capacity of a single actuator, it is necessary to perform a resultant secondary load treatment.

[0033] The core of the resultant force secondary load processing is to maintain the resultant force of the original partition (F) i M i Under the premise of complete static equivalence, the single resultant force is decomposed into multiple (M) i (1) Physically achievable loading point loads. For example... Figure 4 As shown, a resultant force is equivalent to two actual loading point loads.

[0034] The resultant secondary load processing includes the following steps: 5.1 Input and Constraint Definitions.

[0035] Input the resultant force data of the partition (F) i M i ), theoretical point of action position r cop And the feasibility constraints of the physical loading system. Constraints include: the feasible spatial area of ​​the loading points (avoiding structural features, fixtures, etc.); the magnitude range of the load at each loading point [F]. min , F max ]; Load direction constraint (e.g., if the actuator can only apply force axially, then the load direction must be parallel to the actuator mounting axis).

[0036] 5.2 Establish a static equivalent optimization model.

[0037] 5.2.1 Determine the design variables.

[0038] Setting M i The spatial location P of each loading point i_ k(k=1 to M i (can be preset or used as a variable within the feasible region) and its corresponding load vector F i_ k.

[0039] 5.2.2 Determine the core equality constraints (static equivalence conditions).

[0040] ΣF i_ k= F i (That is, the resultant force vector sum is equal); Σ( (P i_ k - r cop )×F i_ k) = 0 (the resultant moment about the theoretical point of application is zero); 5.2.3 Determine inequality constraints.

[0041] ||F i_ k|| ∈ [F min [, Fmax]; That is, F i_ The direction of k satisfies the direction constraint.

[0042] 5.2.4 Determine the objective function.

[0043] It can be defined as minimizing the variance of the load size at each loading point (to make the load distribution most uniform), or minimizing the sum of the moduli of the loads at each loading point (to minimize the system energy consumption).

[0044] 5.2.5 Model Solving and Output.

[0045] The above model is solved using mathematical optimization algorithms (such as sequential quadratic programming and genetic algorithms). The solution results in a set of optimal loading point positions {P}. i_ 1, P i_ 2, …, P i _M i} and its corresponding load vector {F i _1, F i _2, …,F i _M i This information is then bound to generate the executable loading scheme data for that partition.

[0046] 5.2.6 Iterative adjustment.

[0047] If the initial solution fails (no solution) or the result is unsatisfactory (e.g., a certain load is too large), M can be adjusted. iAdjust the preset loading point or fine-tune the feasible area, and re-optimize until a satisfactory solution is obtained.

[0048] Step 6: Integration and Output.

[0049] Repeat step 5 until all executable loading scheme data for all N partitions have been generated. Integrate all data to generate a complete overall loading scheme. The scheme can be output in the form of a list or a visual chart, listing the three-dimensional coordinates and load vector (magnitude and direction) of each physical loading point, serving as the direct basis for subsequent design of the loading lever system, arrangement of actuators, and compilation of control commands.

[0050] In this embodiment, a computer device is provided, such as... Figure 5 As shown, it includes a memory 501, a processor 502, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the above-mentioned method for loading the static load of the arbitrary complex curved surface with gradual pressure.

[0051] Specifically, the computer device can be a computer terminal, a server, or a similar computing device.

[0052] In this embodiment, a computer-readable storage medium is provided, which stores a computer program that performs the above-described method for loading the static load of a complex curved surface with gradually varying pressure.

[0053] Specifically, computer-readable storage media include both permanent and non-permanent, removable and non-removable media, which can store information using any method or technology. Information can be computer-readable instructions, data structures, modules of programs, or other data. Examples of computer-readable storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transferable medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media do not include transient media, such as modulated data signals and carrier waves.

[0054] Based on the same inventive concept, this invention also provides a loading device for a static load of gradually varying pressure on a complex curved surface, as described in the following embodiments. Since the principle of the loading device for the static load of gradually varying pressure on a complex curved surface is similar to the loading method for the static load of gradually varying pressure on a complex curved surface, the implementation of the loading device for the static load of gradually varying pressure on a complex curved surface can refer to the implementation of the loading method for the static load of gradually varying pressure on a complex curved surface, and will not be repeated. As used below, the terms "unit" or "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0055] Figure 6 This is a structural block diagram of a loading device for a complex curved surface gradually varying pressure static test load according to an embodiment of the present invention, such as... Figure 6 As shown, it includes: parameter acquisition module 601, surface partitioning module 602, finite element calculation and load extraction module 603, point of application analysis module 604, resultant force secondary load processing module 605, and data integration module 606. The structure is described below.

[0056] The parameter acquisition module 601 is used to acquire the geometric model data of the complex curved surface to be tested and the gradual pressure distribution data corresponding to the geometric model data; The surface partitioning module 602 is used to divide the complex surface into multiple loading partitions based on the geometric model data and the physical constraints of the experimental loading, generate partition definition data, and determine the number of loading points for each loading partition. The finite element calculation and load extraction module 603 is used to perform finite element analysis based on the geometric model data, the partition definition data, the gradual pressure distribution data and the preset boundary condition data, calculate and output the partition resultant force data of each loading partition, wherein the partition resultant force data includes resultant force vector and resultant moment; The application point analysis module 604 is used to calculate the coordinates of the pressure center of each loading partition based on the gradual pressure distribution data and the geometric model data corresponding to the loading partition, and use the coordinates of the pressure center as the theoretical application point location data of the loading partition. The resultant force secondary load processing module 605 is used to perform secondary static equivalent processing on each loading partition based on the corresponding resultant force data of the partition and the theoretical point of application location data, to generate executable loading scheme data for the loading partition. The executable loading scheme data includes the spatial location of multiple physical loading points and the load vector allocated to the physical loading points. The data integration module 606 is used to integrate the executable loading scheme data of all the loading partitions.

[0057] In one embodiment, the surface partitioning module includes: The reference loading point calculation unit is used to calculate the number of reference loading points based on the partition area and the preset loading point density reference value in the partition definition data. The curvature acquisition unit is used to acquire the surface curvature information corresponding to each loading partition in the geometric model data; The reference point unit is used to correct the number of reference loading points based on the surface curvature information, and to adjust the number of loading points in the loading partition where the surface curvature is higher than a preset threshold to be greater than the number of reference loading points.

[0058] In one embodiment, the finite element calculation and load extraction module includes: The partitioned mesh generation unit is used to discretize the geometric model of the corresponding region according to the partition definition data to generate a partitioned mesh model; The nodal force calculation unit is used to map the gradual pressure distribution data to each surface element of the partitioned mesh model and calculate the nodal force data of each surface element. The resultant force vector moment calculation unit is used to perform vector synthesis and moment synthesis on all the nodal force data within the range of the partition definition data, and calculate the resultant force vector and the resultant moment.

[0059] In one embodiment, the point of action analysis module includes: A geometric information acquisition unit is used to acquire the surface geometric information corresponding to the loading partition based on the geometric model data; The load micro-element discrete unit is used to discretize the loading partition into multiple load micro-elements based on the surface geometry information and the gradual pressure distribution data, and to determine the micro-element area, micro-element center position and micro-element normal direction of each load micro-element. The load vector calculation unit is used to calculate the element load vector on each of the load elements based on the gradually changing pressure distribution data. The coordinate calculation unit is used to calculate the coordinates of the pressure center by taking the center position of the micro-element as the pressure center based on the micro-element load vector on all the load micro-elements and the center position of the micro-element corresponding to the load vector.

[0060] In one embodiment, the resultant secondary load processing module includes: The data acquisition unit is used to acquire the resultant force data of the loading partition to be processed, the theoretical point of application location data, and the feasibility constraints of the loading lever system. The model building unit is used to establish a static equivalent optimization model, wherein the static equivalent optimization model is used to optimize and decompose the partition resultant force data and theoretical application point location data into multiple physically realizable loading point loads under the condition of satisfying the feasibility constraints. The scheme output unit is used to solve the static equivalent optimization model to obtain a set of M load vectors that satisfy all constraints and make the objective function optimal, and the candidate loading point positions corresponding to the load vectors. After binding the load vectors with the candidate loading point positions, the output is the executable loading scheme data.

[0061] In one embodiment, the model building unit is further configured to set design variables, wherein the design variables are load vectors acting on M candidate loading points within the current loading partition, and M≥2; the core equality constraint is defined as the sum of the M load vectors being equal to the resultant force vector in the partition resultant force data, and the resultant moment of the M load vectors about the point indicated by the theoretical point of application location data being equal to the resultant moment in the partition resultant force data; the feasibility constraint condition is defined as the inequality constraint for the magnitude and direction of each load vector; an objective function is defined, wherein the objective function is used to optimize at least one of the load distribution performance index, system energy consumption index, and direction consistency index; and a static equivalent optimization model is constructed based on the core equality constraint, the inequality constraint, and the objective function.

[0062] In one embodiment, the resultant secondary load processing module further includes an iteration unit.

[0063] In one embodiment, the iteration unit is further configured to adjust the number M of candidate loading points or the spatial position of the candidate loading points if solving the static equivalent optimization model fails or the obtained executable loading scheme data does not meet the engineering error requirements, and to re-establish and solve the static equivalent optimization model until executable loading scheme data that meets the requirements is obtained.

[0064] The embodiments of the present invention achieve the following technical effects: This invention introduces finite element analysis as the core calculation tool to solve a digital model with a realistic gradual pressure distribution. This method can accurately calculate the vector sum of all distributed pressures on each partition, directly outputting a high-precision resultant force vector (magnitude and direction). This avoids the systematic errors caused by manual estimation of area, average pressure, and subjective judgment of direction. The finite element analysis yields a real resultant force based on rigorous mathematical and physical principles, laying a reliable data foundation for all subsequent processing and reducing loading errors from the source. This invention uses a specialized pressure center calculation process to solve for the theoretically optimal point of application that makes the resultant moment zero, based on the actual situation of the distributed load. The entire process follows mechanical principles, ensuring that even for asymmetrical or unevenly loaded partitions, the most consistent force application position with the real load effect can be found, eliminating hidden bending moment errors caused by misjudgment of the point of application, and making the static equivalence of the load more accurate. Based on the secondary static equivalence processing, this invention reconstructs the accurate resultant force and theoretical point of application obtained from the above calculation in an optimized model that considers all physical constraints (such as actuator force value, stroke, direction, and spatial interference). By solving this model, the precise but potentially unapplicable resultant force is decomposed into multiple physically fully realizable discrete loading point loads. Under the premise of strictly ensuring static equivalence with the original distributed load, engineering constraints are incorporated to ensure that the final loading scheme is not only accurate but also directly applicable to construction drawing design and equipment. This improves processing efficiency and the repeatability of results, reduces reliance on engineers' experience, and makes the challenging task of handling complex curved surface loads more standardized and efficient.

[0065] Obviously, those skilled in the art should understand that the modules or steps of the above-described embodiments of the present invention can be implemented using general-purpose computing devices. They can be centralized on a single computing device or distributed across a network of multiple computing devices. Optionally, they can be implemented using computer-executable program code, thereby storing them in a storage device for execution by a computing device. In some cases, the steps shown or described can be performed in a different order than those presented here, or they can be fabricated as separate integrated circuit modules, or multiple modules or steps can be fabricated as a single integrated circuit module. Thus, the embodiments of the present invention are not limited to any particular hardware and software combination.

[0066] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for applying a gradually varying pressure static test load on a complex curved surface, characterized in that, include: Obtain the geometric model data of the complex curved surface to be tested and the corresponding gradual pressure distribution data of the geometric model data; Based on the geometric model data and the physical constraints of the experimental loading, the complex surface is divided into multiple loading partitions, partition definition data is generated, and the number of loading points for each loading partition is determined. Based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, finite element analysis is performed to calculate and output the resultant force data of each loading partition, wherein the resultant force data includes the resultant force vector and the resultant moment. For each loading zone, based on the gradual pressure distribution data and the geometric model data corresponding to the loading zone, the coordinates of the pressure center of the loading zone are calculated, and the coordinates of the pressure center are used as the theoretical point of action location data of the loading zone. For each loading partition, based on the corresponding resultant force data of the partition and the theoretical point of application location data, a secondary static equivalent processing is performed to generate executable loading scheme data for the loading partition. The executable loading scheme data includes the spatial locations of multiple physical loading points and the load vectors assigned to the physical loading points. Integrate the executable loading scheme data of all the aforementioned loading partitions.

2. The method for applying the static load of a complex curved surface with gradually varying pressure as described in claim 1, characterized in that, Determine the number of load points for each load partition, including: The number of reference loading points is calculated based on the partition area and the preset loading point density benchmark value in the partition definition data. Obtain the surface curvature information corresponding to each loading partition in the geometric model data; The number of reference loading points is corrected based on the surface curvature information, and the number of loading points in the loading partitions where the surface curvature is higher than a preset threshold is adjusted to be greater than the number of reference loading points.

3. The method for applying the gradually varying pressure static test load on a complex curved surface as described in claim 1, characterized in that, Based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, finite element analysis is performed to calculate and output the resultant force data of each loading partition, including: Based on the partition definition data, the geometric model of the corresponding region is discretized into a grid to generate a partitioned grid model; The gradual pressure distribution data is mapped to each surface element of the partitioned mesh model, and the nodal force data of each surface element is calculated. Within the scope of the partition definition data, vector synthesis and moment synthesis are performed on all the nodal force data to calculate the resultant force vector and the resultant moment.

4. The method for applying the gradually varying pressure static test load on a complex curved surface as described in claim 1, characterized in that, Based on the gradually varying pressure distribution data and the geometric model data corresponding to the loading partition, the coordinates of the pressure center of the loading partition are calculated, including: Based on the geometric model data, obtain the surface geometry information corresponding to the loading partition; Based on the surface geometry information and the gradual pressure distribution data, the loading partition is discretized into multiple load micro-elements, and the micro-element area, micro-element center position and micro-element normal direction of each load micro-element are determined. Based on the gradually varying pressure distribution data, calculate the element load vector on each of the load elements; Based on the element load vectors on all the load elements and the corresponding element center positions, the element center positions are taken as the pressure centers, and the coordinates of the pressure centers are calculated.

5. The method for applying the static load of a complex curved surface with gradually varying pressure as described in claim 1, characterized in that, Based on the corresponding resultant force data of the partition and the theoretical point of application location data, a secondary static equivalent processing is performed to generate executable loading scheme data for the loading partition, including: Obtain the resultant force data of the loading partition to be processed, the theoretical point of application location data, and the feasibility constraints of the loading lever system; A static equivalent optimization model is established, wherein the static equivalent optimization model is used to optimize and decompose the resultant force data of the partition and the theoretical application point location data into multiple physically realizable loading point loads under the condition of satisfying the feasibility constraints. Solve the static equivalent optimization model to obtain a set of M load vectors that satisfy all constraints and optimize the objective function, and the candidate loading point positions corresponding to the load vectors. After binding the load vectors with the candidate loading point positions, output the executable loading scheme data.

6. The method for applying the gradually varying pressure static test load on a complex curved surface as described in claim 5, characterized in that, Establish a static equivalent optimization model, including: Define design variables, wherein the design variables are load vectors acting on M candidate loading points within the current loading partition, and M≥2; The core equation constraint is that the vector sum of the M load vectors is equal to the resultant force vector in the partition resultant force data, and the resultant moment of the M load vectors about the point indicated by the theoretical point of application location data is equal to the resultant moment in the partition resultant force data. The magnitude and direction of each load vector satisfy the aforementioned feasibility constraints as inequality constraints. Define an objective function, wherein the objective function is used to optimize at least one of the following indicators: load distribution performance index, system energy consumption index, and directional consistency index; A static equivalent optimization model is constructed based on the core equality constraints, the inequality constraints, and the objective function.

7. The method for applying the gradually varying pressure static test load on a complex curved surface as described in claim 5, characterized in that, Also includes: If solving the static equivalent optimization model fails or the obtained executable loading scheme data does not meet the engineering error requirements, the number M of candidate loading points or the spatial position of the candidate loading points are adjusted, and the static equivalent optimization model is re-established and solved until executable loading scheme data that meets the requirements is obtained.

8. A loading device for a static load test of a complex curved surface with gradually varying pressure, characterized in that, include: The parameter acquisition module is used to acquire the geometric model data of the complex curved surface to be tested and the corresponding gradual pressure distribution data of the geometric model data; The surface partitioning module is used to divide the complex surface into multiple loading partitions based on the geometric model data and the physical constraints of the experimental loading, generate partition definition data, and determine the number of loading points for each loading partition. The finite element calculation and load extraction module is used to perform finite element analysis based on the geometric model data, the partition definition data, the gradual pressure distribution data, and the preset boundary condition data, calculate and output the partition resultant force data of each loading partition, wherein the partition resultant force data includes resultant force vector and resultant moment; The application point analysis module is used to calculate the coordinates of the pressure center of each loading partition based on the gradual pressure distribution data and the geometric model data corresponding to the loading partition, and use the coordinates of the pressure center as the theoretical application point location data of the loading partition. The resultant force secondary load processing module is used to perform secondary static equivalent processing on each loading partition based on the corresponding resultant force data of the partition and the theoretical point of application location data, to generate executable loading scheme data for the loading partition. The executable loading scheme data includes the spatial location of multiple physical loading points and the load vector allocated to the physical loading points. The data integration module is used to integrate the executable loading scheme data of all the loading partitions.

9. A computer 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 the loading method for the static test load of the complex curved surface with gradual pressure as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that performs the loading method for a complex surface gradually changing pressure static test load according to any one of claims 1 to 7.

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