A method and system for optimizing rudder wing structure under high overload environment

Abstract

The present invention discloses a method and system for optimizing a rudder wing structure under a high overload environment, and relates to the technical field of rudder wing structure optimization design. The method comprises: determining the airfoil shape and plane shape of the rudder wing structure; calculating the rudder wing area of ​​the rudder wing structure; designing a three-dimensional steering gear structure and constructing a numerical simulation model; simulating and analyzing the three-dimensional steering gear model under a high overload environment in a simulated chamber to obtain an equivalent stress distribution diagram, identifying the abnormal deformation position and the corresponding maximum stress value and its structural unit in the distribution diagram; constructing an agent model according to sample data, and determining the final optimization scheme based on an optimization algorithm. The method effectively solves the problem of the difficulty of numerical simulation of the steering gear system under a high overload environment, and designs a rudder wing structure that meets both flight aerodynamic performance and structural strength.

Description

Technical Field

[0001] The present invention generally relates to the technical field of rudder wing structure optimization design, and specifically relates to a rudder wing structure optimization method and system under high overload environment. Background Art

[0002] At present, the load analysis of the servo system mostly considers the load in the correction state, that is, the effect of the air resistance moment on the rudder surface in the correction state. The air resistance moment is composed of inertia moment, damping moment, hinge moment, etc., while there is less analysis on the guided artillery shell launching stage.

[0003] During the actual in-bore firing process, the guided projectile is subjected to extremely large acceleration, and the overload can reach or exceed 20,000g, where g is the acceleration of gravity on the earth's surface. Considering that the electric servo is located inside the projectile, in order to ensure that it is not damaged by huge pressure during the firing process, it is necessary to conduct a numerical analysis of its in-bore firing strength. Among them, the airfoil and plane shape of the rudder wing structure of the servo system directly affect the aerodynamic performance, structural strength and overall efficiency of the rudder wing structure itself. The traditional design method of the rudder wing structure often focuses on the performance analysis under static or single load, which is difficult to fully reflect the comprehensive impact of high overload and aerodynamic characteristics. Therefore, we propose a rudder wing structure optimization method and system for high overload environment to solve the above problems. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide a method and system for optimizing the rudder wing structure in a high overload environment, which can improve the structural strength of the rudder wing and meet the flight aerodynamic performance.

[0005] In a first aspect, the present invention provides a method for optimizing a rudder wing structure under a high overload environment, comprising the following steps:

[0006] Acquiring the rudder wing characteristics of the physical electric servo, and determining the airfoil shape and the plane shape of the rudder wing structure according to the rudder wing characteristics;

[0007] According to the control moment equation, the rudder wing area of ​​the rudder wing structure is calculated; and according to the proportional relationship between the lift value of the rudder wing structure and the rudder wing area, the important design parameters of the rudder wing structure are determined; the important design parameters at least include: aspect ratio, root-tip ratio and relative thickness;

[0008] A three-dimensional steering gear model is constructed according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional steering gear model includes multiple structures, and the structures at least include: a servo motor, a housing, a rudder wing structure, a speed reduction mechanism, a control mechanism, and a rudder wing locking and unlocking mechanism;

[0009] Based on the structural composition of the three-dimensional steering gear model, the three-dimensional steering gear model is meshed to obtain a plurality of structural units, and corresponding structural material parameters are assigned to each of the structural units; each of the structural units corresponds to a structure in the three-dimensional steering gear model;

[0010] The three-dimensional steering gear model is simulated and analyzed under a high overload environment in a simulated chamber to obtain an equivalent stress distribution diagram of the rudder wing structure, and the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram are identified;

[0011] When the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, an optimization proxy model is constructed according to sample data; the sample data is the airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure obtained in the three-dimensional steering gear model;

[0012] According to the optimization proxy model, final optimization data are determined; the final optimization data include: optimized airfoil shape, optimized plane shape, optimized rudder wing area and optimized important design parameters.

[0013] The technical solution provided by the present invention also includes the following steps:

[0014] Based on the final optimization data, construct an optimized three-dimensional steering gear model;

[0015] Under a plurality of simulation working conditions formed by combinations of different attack angles and different Mach numbers, the three-dimensional steering gear model and the optimized three-dimensional steering gear model are simulated respectively, and a plurality of first aerodynamic characteristic data of the three-dimensional steering gear model and a plurality of second aerodynamic characteristic data of the optimized three-dimensional steering gear model are calculated;

[0016] When the second aerodynamic characteristic data under each simulated working condition is greater than or equal to the first aerodynamic characteristic data, it is determined that the final optimized data meets the requirements.

[0017] According to the technical solution provided by the present invention, the aspect ratio is the ratio of the span of the rudder wing structure to the average geometric chord length, the root-tip ratio is the ratio of the wing root chord length to the wingtip chord length of the rudder wing structure, and the relative thickness is the ratio of the maximum thickness of the rudder wing structure to the chord length.

[0018] According to the technical solution provided by the present invention, the sample data includes a plurality of test sample data and a plurality of verification sample data;

[0019] Building an optimization proxy model based on sample data includes the following steps:

[0020] Based on the Latin hypercube sampling method, extracting a plurality of test sample data and a plurality of verification sample data from the three-dimensional steering gear model;

[0021] Constructing a plurality of different types of initial proxy models according to the test sample data and the verification sample data;

[0022] The determination coefficient of each of the initial proxy models is calculated, and the initial proxy model corresponding to the determination coefficient closest to the preset coefficient is selected as the optimized proxy model.

[0023] According to the technical solution provided by the present invention, the determination coefficient of each initial proxy model is calculated according to the following formula:

[0024] ;

[0025] in, is the coefficient of determination, is the i-th actual value of the initial surrogate model, is the predicted value of the initial surrogate model, is the average of the sum of the actual values ​​of the initial proxy model, and n is the total number of actual values ​​or preset values ​​in the initial proxy model.

[0026] According to the technical solution provided by the present invention, the rudder wing area of ​​the rudder wing structure is calculated according to the following formula:

[0027] ;

[0028] in, is the rudder wing area, is the operating torque coefficient, is the derivative of the lift coefficient of the rudder with respect to the rudder deflection angle, is the speed retardation coefficient, is the reference length of the operating torque coefficient, is the missile center of mass coordinate, is the pressure center coordinate of the rudder.

[0029] According to the technical solution provided by the present invention, a high overload environment in a simulated chamber is constructed according to the following steps:

[0030] The structural connection mode and constraint conditions of the physical electric servo are obtained; the constraint conditions at least include: ignoring the air resistance at the front end of the shell and the recoil of the barrel, ignoring the temperature-stress field, and ignoring the heat generated by friction;

[0031] Based on the structural connection method and the constraint conditions, a high overload environment is simulated inside the chamber.

[0032] According to the technical solution provided by the present invention, the final optimization data is determined according to the optimization agent model, which specifically includes the following steps:

[0033] The optimization agent model is optimized by multi-objective parameters through a second generation non-inferior sorting genetic algorithm to obtain optimized data; the target parameters at least include: the thickness of the top, middle and bottom of the rudder wing structure and the curvature radius of the left and right sides;

[0034] Inputting the optimized data into the optimization proxy model for re-numerical analysis to obtain an optimized prediction value;

[0035] If the difference between the optimized predicted value and the preset simulation value is less than the preset difference, the final optimized data is determined according to the current optimization agent model.

[0036] In a second aspect, the present invention provides a rudder wing structure optimization system for a high overload environment, which is used to implement the above-mentioned rudder wing structure optimization method for a high overload environment, and the system includes:

[0037] A data acquisition module is used to obtain the rudder characteristics of the physical electric servo;

[0038] A data processing module is used to determine the airfoil shape and plane shape of the rudder wing structure according to the rudder wing characteristics; calculate the rudder wing area of ​​the rudder wing structure according to the control torque equation; and determine the important design parameters of the rudder wing structure according to the proportional relationship between the lift value of the rudder wing structure and the rudder wing area; the important design parameters at least include: aspect ratio, root-tip ratio and relative thickness; construct a three-dimensional steering gear model according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional steering gear model includes multiple structures, and the structures at least include: servo motor, housing, rudder wing structure, speed reduction mechanism, control mechanism, rudder wing locking and unlocking mechanism; based on the structural composition of the three-dimensional steering gear model, the three-dimensional steering gear model is gridded to obtain multiple structural units, and each of the structural units is assigned a corresponding structural material parameters; each of the structural units corresponds to a structure in the three-dimensional steering gear model; the three-dimensional steering gear model is simulated and analyzed under a simulated high overload environment in the chamber to obtain an equivalent stress distribution diagram of the rudder wing structure, and the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram are identified; when the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, an optimization proxy model is constructed according to the sample data; the sample data is the airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure obtained in the three-dimensional steering gear model; according to the optimization proxy model, the final optimization data is determined; the final optimization data includes: the optimized airfoil shape, the optimized plane shape, the optimized rudder wing area and the optimized important design parameters.

[0039] It can be seen from the above technical solution that the present invention has at least the following beneficial effects:

[0040] The present invention provides a method for optimizing a rudder wing structure under a high overload environment, which comprises: obtaining the rudder wing characteristics of a physical electric servo, and determining the airfoil shape and the plane shape of the rudder wing structure according to the rudder wing characteristics; calculating the rudder wing area of ​​the rudder wing structure according to a control torque equation; and determining important design parameters of the rudder wing structure according to the proportional relationship between the lift value of the rudder wing structure and the rudder wing area; the important design parameters at least include: aspect ratio, root-tip ratio and relative thickness; constructing a three-dimensional servo model according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional servo model comprises a plurality of structures, and the structures at least include: a servo motor, a housing, a rudder wing structure, a speed reduction mechanism, a control mechanism, and a rudder wing locking and unlocking mechanism; based on the structural composition of the three-dimensional servo model, the three-dimensional servo model is meshed to obtain a plurality of structural units, and each structural unit is assigned corresponding structural material parameters; each structural unit corresponds to a structure in the three-dimensional steering gear model; the three-dimensional steering gear model is simulated and analyzed under a simulated high overload environment in the chamber to obtain the equivalent stress distribution diagram of the rudder-wing structure, and the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram are identified; when the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, an optimization proxy model is constructed according to the sample data; the sample data is the airfoil shape, plane shape, rudder-wing area and important design parameters corresponding to the rudder-wing structure obtained in the three-dimensional steering gear model; according to the optimization proxy model, the final optimization data is determined; the final optimization data includes: the optimized airfoil shape, the optimized plane shape, the optimized rudder-wing area and the optimized important design parameters.

[0041] The present invention builds a three-dimensional steering gear model based on the simplified structure of the physical electric steering gear, and performs simulation analysis on the three-dimensional steering gear model in a simulated high overload environment in the chamber, that is, simulating the extreme impact load that the shell is subjected to during the firing process in the chamber, taking the maximum equivalent stress and mass of the rudder wing structure as the optimization target, constructing an optimization proxy model, and determining the final optimization data. The problem of the difficulty of numerical simulation of the steering gear system in a high overload environment is effectively solved, and based on the final optimization data, a rudder wing structure that meets both flight aerodynamic performance and structural strength is designed. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Other features, objectives and advantages of the present invention will become more apparent from a reading of the detailed description of non-limiting embodiments made with reference to the following accompanying drawings.

[0043] Figure 1 Flow chart of the rudder wing structure optimization method under high overload environment.

[0044] Figure 2 Flowchart for building an optimized surrogate model.

[0045] Figure 3 This is a schematic diagram of a physical electric servo.

[0046] Figure 4 Schematic diagram of the rudder wing structure.

[0047] Figure 5 is the applied acceleration load curve.

[0048] Figure 6 Schematic diagram of the airfoil shape.

[0049] Figure 7 Schematic diagram of the rudder-wing structure optimization system for high overload environments.

[0050] Numbers in the figure: 1. Shell; 2. Rudder wing structure; 3. Rudder wing locking and unlocking mechanism; 4. Control mechanism; 5. Speed ​​reduction mechanism; 6. Servo motor; 7. Data acquisition module; 8. Data processing module. DETAILED DESCRIPTION

[0051] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It should also be noted that, for ease of description, only the parts related to the invention are shown in the accompanying drawings.

[0052] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0053] In order to make the description of the following embodiments clear and concise, a brief introduction to the related technology is first given:

[0054] When flying in the air, the projectile relies on the servo to drive the rudder to deflect to adjust the heading in real time, that is, the servo controller receives the given rudder angle signal sent by the guidance computer, controls the rudder to deflect, thereby changing the flight attitude and navigation trajectory of the projectile, so as to achieve the purpose of projectile flight control and precise guidance. The traditional design method of rudder wing structure often focuses on the performance analysis under static or single load, which is difficult to fully reflect the comprehensive impact of high overload and aerodynamic characteristics.

[0055] In order to make the rudder wing structure optimization method for a high overload environment provided by the embodiment of the present invention clearer and easier to understand, the method is described below in conjunction with the accompanying drawings. Figure 1 As shown in FIG. 1 , the figure is a flow chart of a method for optimizing a rudder wing structure under a high overload environment provided by an embodiment of the present invention, the method comprising:

[0056] S100, obtaining rudder wing characteristics of the physical electric servo, and determining the airfoil shape and the plane shape of the rudder wing structure according to the rudder wing characteristics.

[0057] It should be noted that the rudder wing characteristics of the physical electric servo refer to the aerodynamic characteristics of different airfoils and plane shapes. Based on the rudder wing characteristics, the airfoil shape and plane shape of the rudder wing structure that meet both aerodynamic performance and structural strength are selected. Figure 6 As shown in the figure, it is a schematic diagram of the airfoil shape. The airfoil shapes of the rudder-wing structure include peak type, Clark Y type, trapezoidal type, S-shaped type, concave type and double arc type, etc. Here, the airfoil shape of the rudder-wing structure is selected as a rectangle, and the plane shape is selected as an arrow cluster shape, so that the formed rudder-wing structure achieves a better balance between mass and aerodynamic performance.

[0058] S200. Calculate the rudder wing area of ​​the rudder wing structure according to the control torque equation; and determine the important design parameters of the rudder wing structure according to the proportional relationship between the lift value of the rudder wing structure and the rudder wing area; the important design parameters include at least: aspect ratio, root-tip ratio and relative thickness.

[0059] It should be noted that the rudder wing area of ​​the rudder wing structure is calculated according to the following formula:

[0060] ;

[0061] in, is the rudder wing area, is the operating torque coefficient, is the derivative of the lift coefficient of the rudder with respect to the rudder deflection angle, is the speed retardation coefficient, is the reference length of the operating torque coefficient, is the missile center of mass coordinate, is the pressure center coordinate of the rudder.

[0062] In addition, the aspect ratio is the ratio of the span of the rudder-wing structure to the average geometric chord length, the root-tip ratio is the ratio of the wing root chord length to the wingtip chord length of the rudder-wing structure, and the relative thickness is the ratio of the maximum thickness of the rudder-wing structure to the chord length.

[0063] In this method, the lift value of the rudder-wing structure refers to the force perpendicular to the direction of the incoming flow that the rudder-wing structure is subjected to when a fluid (such as air or water) flows through the rudder-wing structure. This force enables an object (such as a ship, an airplane, etc.) to change its direction of motion in the fluid or to generate an upward force (such as the lift generated by the wings of an airplane to lift the airplane into the air). The lift value of the rudder-wing structure is proportional to the rudder-wing area, that is, the larger the rudder-wing area of ​​the rudder-wing structure is, the greater the lift value it provides.

[0064] Taking a canard-type guided artillery shell as an example, the rudder wing area of ​​4000mm is calculated based on its control torque equation and tail wing area. 2 The maximum thickness of the rudder wing structure is 4mm, while its average geometric chord length is 33mm, correspondingly, the relative thickness is about 12%. The aspect ratio is about 3.8, its maximum span is 122mm, and the root-tip ratio is about 0.9. Such design data can better withstand flight loads and improve its stability and controllability.

[0065] S300, constructing a three-dimensional servo model according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional servo model includes multiple structures, and the structures at least include: a servo motor, a housing, a rudder wing structure, a speed reduction mechanism, a control mechanism, and a rudder wing locking and unlocking mechanism.

[0066] It should be noted that if Figure 3 As shown in FIG. 1 , the figure is a schematic diagram of a physical electric servo, and the three-dimensional servo model includes multiple structures, which at least include: a servo motor 6, a housing 1, a rudder wing structure 2, a speed reduction mechanism 5, a control mechanism 4, and a rudder wing locking and unlocking mechanism 3. In this method, the six parts of the physical motor servo are divided and simplified according to their importance. Based on the simplified physical electric servo structure and the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure, a three-dimensional servo model is constructed.

[0067] S400, based on the structural composition of the three-dimensional steering gear model, meshing the three-dimensional steering gear model to obtain a plurality of structural units, and assigning corresponding structural material parameters to each structural unit; each structural unit corresponds to a structure in the three-dimensional steering gear model.

[0068] It should be noted that the HyperMesh software can be used to mesh the three-dimensional servo model, analyze different three-dimensional servo models, and select the appropriate mesh type. Here, for example, compared with the tetrahedral mesh, the hexahedral mesh has fewer units, which can reduce the solution time and make it easier to process the three-dimensional servo model on the workstation. Considering the number of nodes and the mesh flow direction, the hexahedral mesh can be selected. As shown in Table 1, the corresponding relationship between the structural unit and the number of meshes.

[0069] Table 1 Correspondence between each structural unit and the number of grids

[0070]

[0071] In addition, the structural material parameters are shown in Table 2, where the material corresponding to the rudder wing structure is aluminum alloy 7075T6, and the material corresponding to the remaining structures is 35CrMnSiA.

[0072] Table 2 Structural material parameters

[0073]

[0074] S500, performing simulation analysis on the three-dimensional steering gear model under a high overload environment in a simulated chamber, obtaining an equivalent stress distribution diagram of the rudder wing structure, and identifying the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram.

[0075] It should be noted that the high overload environment in the chamber is simulated according to the following steps:

[0076] The structural connection mode and constraint conditions of the physical electric servo are obtained; the constraint conditions at least include: ignoring the air resistance at the front end of the projectile and the recoil of the barrel, ignoring the temperature-stress field, and ignoring the heat generated by friction;

[0077] Based on the structural connection method and constraint conditions, a high overload environment simulated inside the chamber is built.

[0078] To ensure that the 3D servo model can accurately reflect the stress of the actual structure, in the simulated high overload environment in the chamber, according to the use scenario of the electric servo and the process of firing the shell in the chamber, the corresponding acceleration load is applied to the bottom of the electric servo. The applied acceleration load curve is as follows: Figure 5 As shown, in this method, it is assumed that the temperature range, humidity conditions, etc. during the operation of the electric servo are not considered for the time being, so as to avoid the influence of these environmental factors on the structural performance.

[0079] Based on the above simulation analysis, the abnormal deformation position and the corresponding maximum stress value and the structural unit in the equivalent stress distribution diagram are identified, that is, according to the equivalent stress distribution diagram, the deformation of the rudder wing structure under the acceleration load is analyzed to find out whether there is an abnormal deformation position, that is, a position of large deformation or abnormal deformation. Then, a stress failure judgment is performed, and the maximum stress value is compared with the yield strength or tensile strength of the structural material parameter to determine whether the rudder wing structure has stress failure. If the rudder wing structure has not stress failure, it indicates that the selection of various parameters of the current rudder wing structure is no problem and does not need to be optimized. If stress failure occurs, step S600 is executed.

[0080] S600, when the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, construct an optimization proxy model according to the sample data; the sample data is the airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure obtained in the three-dimensional rudder model.

[0081] Here, if the maximum stress value is greater than the yield strength of the structural unit at the abnormal deformation position, it indicates that the rudder wing structure has stress failure. The current selection of various parameters of the rudder wing structure (airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure) has deviations and needs to be optimized. That is, based on the sample data obtained from the three-dimensional steering gear model, an optimization proxy model is constructed.

[0082] It should be noted that the sample data includes multiple test sample data and multiple verification sample data;

[0083] like Figure 2 As shown, an optimization agent model is constructed based on sample data, which specifically includes the following steps:

[0084] S601. Based on the Latin hypercube sampling method, extract a plurality of test sample data and a plurality of verification sample data from the three-dimensional steering gear model.

[0085] The purpose of using the Latin hypercube sampling method for the experiment is to ensure that as much design space as possible can be covered under limited resources and to obtain information useful for optimization. Here, the number of test sample data is, for example, 60, and the number of validation sample data is, for example, 15. The test sample data is used for the experiment, and the validation sample data is used to validate the initial proxy model.

[0086] S602: Construct a plurality of different types of initial proxy models based on the test sample data and the verification sample data.

[0087] Here, different types of initial proxy models are, for example, response surface models, Kriging models, and the like.

[0088] S603, calculating the determination coefficient of each initial proxy model, and selecting the initial proxy model corresponding to the determination coefficient closest to the preset coefficient as the optimized proxy model.

[0089] The coefficient of determination of each initial proxy model is calculated according to the following formula:

[0090] ;

[0091] in, is the coefficient of determination, is the i-th actual value of the initial surrogate model, is the predicted value of the initial surrogate model, is the average of the sum of the actual values ​​of the initial proxy model, and n is the total number of actual values ​​or preset values ​​in the initial proxy model.

[0092] Here, the preset coefficient is 1. The determination coefficient is an important indicator to measure the similarity between the prediction results of the initial proxy model and the actual results. The determination coefficient is usually used to evaluate the fitting accuracy and prediction ability of the proxy model. When the determination coefficient is closer to 1, it means that the prediction results of the initial proxy model are closer to the actual results and the fitting accuracy is higher. By comparing the determination coefficient, the Kriging proxy model is selected.

[0093] S700, determining final optimization data according to the optimization proxy model; the final optimization data includes: optimized airfoil shape, optimized plane shape, optimized rudder wing area, and optimized important design parameters.

[0094] For example, shape optimization, which focuses on changing the plane shape of the rudder wing structure, sets targets on aspects such as thickness and curvature radius. These targets are usually closely related to the performance indicators of the rudder wing. This experiment takes reducing the mass of the rudder wing and its maximum equivalent stress as the target response, and selects five parameters that have a significant impact on the optimization target from the design parameters of the rudder wing as optimization variables. These parameters include the thickness of the top, middle and bottom of the rudder wing and the curvature radius of the left and right sides.

[0095] It should be noted that the final optimization data is determined according to the optimization agent model, which specifically includes the following steps:

[0096] The optimization agent model is optimized by multi-objective parameters through the second generation non-inferior sorting genetic algorithm to obtain the optimized data; Figure 4 As shown, the target parameters include at least: the upper, middle and lower thicknesses of the rudder wing structure and the curvature radii on the left and right sides; the upper, middle and lower thicknesses of the rudder wing structure refer to the thickness of the rudder wing structure close to its upper edge, the thickness of the central area of ​​the rudder wing structure, and the thickness of the rudder wing structure close to its lower edge, respectively.

[0097] Input the optimized data into the optimization agent model for re-numerical analysis to obtain the optimized prediction value;

[0098] If the difference between the optimized predicted value and the preset simulation value is less than the preset difference, the final optimized data is determined according to the current optimization agent model.

[0099] Here, the preset simulation value and the preset difference value can be set according to actual needs.

[0100] For example, after selecting the Kriging proxy model, the parameters in the Kriging proxy model are optimized to ensure that the Kriging model can accurately reflect the actual situation. It is mainly to adjust, verify and calibrate the parameters of the Kriging model, and use the NSGA-Ⅱ multi-objective optimization algorithm to evaluate the accuracy of the Kriging model by comparing the prediction results of the proxy model with the high-precision numerical simulation results. After obtaining the optimization results, these optimization results are compared with the actual situation or high-precision numerical simulation results to evaluate the reliability of the optimization results.

[0101] Furthermore, the method performs simulation analysis on the previous rudder wing structure and the optimized rudder wing structure under different attack angles and different Mach numbers, and obtains their aerodynamic characteristics and then performs before-and-after comparison verification; specifically, the method includes the following steps:

[0102] Based on the final optimization data, build the optimized three-dimensional servo model;

[0103] Under multiple simulation working conditions formed by different combinations of attack angles and different Mach numbers, the three-dimensional steering gear model and the optimized three-dimensional steering gear model are simulated respectively, and multiple first aerodynamic characteristic data of the three-dimensional steering gear model and multiple second aerodynamic characteristic data of the optimized three-dimensional steering gear model are calculated;

[0104] When the second aerodynamic characteristic data under each simulated working condition is greater than or equal to the first aerodynamic characteristic data, it is determined that the final optimized data meets the requirements.

[0105] Among them, in the simulation process of the three-dimensional servo model and the optimized three-dimensional servo model, the geometric area involved in the calculation is first determined, and the corresponding geometric area is discretized, and the appropriate grid shape is selected, and some parts are encrypted. This model is encrypted for the rudder and tail parts of the rudder wing structure, and the grid shape is mainly hexahedron. (1) The viscosity model adopts the SST k-omega model; (2) The material of the calculation area is air, and the ideal gas model is selected, and the viscosity adopts the three-coefficient Salander model; (3) The outer boundary of the calculation geometric area adopts the pressure far field boundary condition, the reference pressure is 0, and the far field static pressure is 101325 Pa; set multiple different attack angles and Mach number combinations to form multiple simulation conditions to simulate the various conditions that the projectile may encounter in actual flight. Comparing the aerodynamic characteristics data of the rudder wing structure before and after optimization, it can be seen that the optimized rudder wing structure shows better performance in terms of torque coefficient, making it easier for the projectile to achieve attitude adjustment and trajectory correction during flight. Moreover, there are significant improvements in lift coefficient, drag coefficient, etc. The lift-to-drag ratio is improved, which can generate greater lift, and help the projectile maintain better stability and control accuracy during flight. It can be judged that the final optimized data meets the requirements, and the physical structure manufactured with the optimized data meets both flight aerodynamic performance and structural strength.

[0106] The present invention builds a three-dimensional steering gear model based on the simplified structure of the physical electric steering gear, and performs simulation analysis on the three-dimensional steering gear model in a simulated high overload environment in the chamber, that is, simulating the extreme impact load that the shell is subjected to during the firing process in the chamber, taking the maximum equivalent stress and mass of the rudder wing structure as the optimization target, constructing an optimization proxy model, and determining the final optimization data. The problem of the difficulty of numerical simulation of the steering gear system in a high overload environment is effectively solved, and based on the final optimization data, a rudder wing structure that meets both flight aerodynamic performance and structural strength is designed.

[0107] like Figure 7 As shown, the present invention also provides a rudder wing structure optimization system for a high overload environment, which is used to implement the above-mentioned rudder wing structure optimization method for a high overload environment. The system includes:

[0108] The data acquisition module 7 is used to obtain the rudder wing characteristics of the physical electric servo;

[0109] The data processing module 8 is used to determine the airfoil shape and plane shape of the rudder wing structure according to the rudder wing characteristics; calculate the rudder wing area of ​​the rudder wing structure according to the control torque equation; and determine the important design parameters of the rudder wing structure according to the proportional relationship between the lift value of the rudder wing structure and the rudder wing area; the important design parameters at least include: aspect ratio, root-tip ratio and relative thickness; construct a three-dimensional steering gear model according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional steering gear model includes multiple structures, and the structure at least includes: servo motor, housing, rudder wing structure, speed reduction mechanism, control mechanism, rudder wing locking and unlocking mechanism; based on the structural composition of the three-dimensional steering gear model, the three-dimensional steering gear model is meshed to obtain multiple structural units, and each structural unit is assigned a corresponding structural material parameters; each structural unit corresponds to a structure in the three-dimensional steering gear model; the three-dimensional steering gear model is simulated and analyzed under a simulated high overload environment in the bore to obtain the equivalent stress distribution diagram of the rudder wing structure, and the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram are identified; when the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, an optimization proxy model is constructed according to the sample data; the sample data is the airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure obtained in the three-dimensional steering gear model; according to the optimization proxy model, the final optimization data is determined; the final optimization data includes: the optimized airfoil shape, the optimized plane shape, the optimized rudder wing area and the optimized important design parameters.

[0110] The above description is only a preferred embodiment of the present invention and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present invention is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with the technical features with similar functions disclosed in the present invention (but not limited to) to form a technical solution.

Claims

1. A method for optimizing the rudder wing structure under high overload conditions, characterized in that: The following steps are involved: Acquiring the rudder wing characteristics of the physical electric servo, and determining the airfoil shape and the plane shape of the rudder wing structure according to the rudder wing characteristics; Calculating the rudder wing area of ​​the rudder wing structure according to the control torque equation; and determining important design parameters of the rudder wing structure according to the proportional relationship between the lift value of the rudder wing structure and the area of ​​the rudder wing; The important design parameters include at least: aspect ratio, root-to-tip ratio and relative thickness; A three-dimensional steering gear model is constructed according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional steering gear model includes multiple structures, and the structures at least include: a servo motor, a housing, a rudder wing structure, a speed reduction mechanism, a control mechanism, and a rudder wing locking and unlocking mechanism; Based on the structural composition of the three-dimensional steering gear model, the three-dimensional steering gear model is meshed to obtain a plurality of structural units, and corresponding structural material parameters are assigned to each of the structural units; each of the structural units corresponds to a structure in the three-dimensional steering gear model; The three-dimensional steering gear model is simulated and analyzed under a high overload environment in a simulated chamber to obtain an equivalent stress distribution diagram of the rudder wing structure, and the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram are identified; When the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, an optimization proxy model is constructed according to sample data; the sample data is the airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure obtained in the three-dimensional steering gear model; According to the optimization proxy model, final optimization data are determined; the final optimization data include: optimized airfoil shape, optimized plane shape, optimized rudder wing area and optimized important design parameters.

2. The method for optimizing the rudder wing structure under high overload environment according to claim 1, characterized in that: The following steps are also included: Based on the final optimization data, construct an optimized three-dimensional steering gear model; Under a plurality of simulation working conditions formed by combinations of different attack angles and different Mach numbers, the three-dimensional steering gear model and the optimized three-dimensional steering gear model are simulated respectively, and a plurality of first aerodynamic characteristic data of the three-dimensional steering gear model and a plurality of second aerodynamic characteristic data of the optimized three-dimensional steering gear model are calculated; When the second aerodynamic characteristic data under each simulated working condition is greater than or equal to the first aerodynamic characteristic data, it is determined that the final optimized data meets the requirements.

3. The method for optimizing the rudder wing structure under high overload environment according to claim 1, characterized in that: The aspect ratio is the ratio of the span of the rudder wing structure to the average geometric chord length, the root-tip ratio is the ratio of the wing root chord length to the wing tip chord length of the rudder wing structure, and the relative thickness is the ratio of the maximum thickness of the rudder wing structure to the chord length.

4. The method for optimizing the rudder wing structure under high overload environment according to claim 1, characterized in that: The sample data includes a plurality of test sample data and a plurality of verification sample data; Building an optimization proxy model based on sample data includes the following steps: Based on the Latin hypercube sampling method, extracting a plurality of test sample data and a plurality of verification sample data from the three-dimensional steering gear model; Constructing a plurality of different types of initial proxy models according to the test sample data and the verification sample data; The determination coefficient of each of the initial proxy models is calculated, and the initial proxy model corresponding to the determination coefficient closest to the preset coefficient is selected as the optimized proxy model.

5. The method for optimizing the rudder wing structure under high overload conditions according to claim 4, characterized in that: The determination coefficient of each initial proxy model is calculated according to the following formula: ； in, is the coefficient of determination, is the i-th actual value of the initial surrogate model, is the predicted value of the initial surrogate model, is the average of the sum of the actual values ​​of the initial proxy model, and n is the total number of actual values ​​or preset values ​​in the initial proxy model.

6. The method for optimizing the rudder wing structure under high overload environment according to claim 1, characterized in that: The rudder wing area of ​​the rudder wing structure is calculated according to the following formula: ； in, is the rudder wing area, is the operating torque coefficient, is the derivative of the lift coefficient of the rudder with respect to the rudder deflection angle, is the speed retardation coefficient, is the reference length of the operating torque coefficient, is the missile center of mass coordinate, is the pressure center coordinate of the rudder.

7. The method for optimizing the rudder wing structure under high overload environment according to claim 1, characterized in that: Follow the steps below to build a simulated high overload environment in the chamber: The structural connection mode and constraint conditions of the physical electric servo are obtained; the constraint conditions at least include: ignoring the air resistance at the front end of the shell and the recoil of the barrel, ignoring the temperature-stress field, and ignoring the heat generated by friction; Based on the structural connection method and the constraint conditions, a high overload environment is simulated inside the chamber.

8. The method for optimizing the rudder wing structure under high overload conditions according to claim 1, characterized in that: According to the optimization agent model, final optimization data is determined, which specifically includes the following steps: The optimization agent model is optimized by multi-objective parameters through a second generation non-inferior sorting genetic algorithm to obtain optimized data; the target parameters at least include: the thickness of the top, middle and bottom of the rudder wing structure and the curvature radius of the left and right sides; Inputting the optimized data into the optimization proxy model for re-numerical analysis to obtain an optimized prediction value; If the difference between the optimized predicted value and the preset simulation value is less than the preset difference, the final optimized data is determined according to the current optimization agent model.

9. A rudder wing structure optimization system for a high overload environment, used to implement a rudder wing structure optimization method for a high overload environment as described in any one of claims 1 to 8, characterized in that: The system comprises: A data acquisition module is used to obtain the rudder characteristics of the physical electric servo; A data processing module is used to determine the airfoil shape and plane shape of the rudder wing structure according to the rudder wing characteristics; calculate the rudder wing area of ​​the rudder wing structure according to the control torque equation; and determine the important design parameters of the rudder wing structure according to the proportional relationship between the lift value of the rudder wing structure and the rudder wing area; the important design parameters at least include: aspect ratio, root-tip ratio and relative thickness; construct a three-dimensional steering gear model according to the airfoil shape, plane shape, rudder wing area and important design parameters of the rudder wing structure; the three-dimensional steering gear model includes multiple structures, and the structures at least include: servo motor, housing, rudder wing structure, speed reduction mechanism, control mechanism, rudder wing locking and unlocking mechanism; based on the structural composition of the three-dimensional steering gear model, the three-dimensional steering gear model is gridded to obtain multiple structural units, and each of the structural units is assigned a corresponding structural material parameters; each of the structural units corresponds to a structure in the three-dimensional steering gear model; the three-dimensional steering gear model is simulated and analyzed under a simulated high overload environment in the chamber to obtain an equivalent stress distribution diagram of the rudder wing structure, and the abnormal deformation position and the corresponding maximum stress value and the structural unit to which it belongs in the equivalent stress distribution diagram are identified; when the maximum stress value is greater than the yield strength of the structural unit to which the abnormal deformation position belongs, an optimization proxy model is constructed according to the sample data; the sample data is the airfoil shape, plane shape, rudder wing area and important design parameters corresponding to the rudder wing structure obtained in the three-dimensional steering gear model; according to the optimization proxy model, the final optimization data is determined; the final optimization data includes: the optimized airfoil shape, the optimized plane shape, the optimized rudder wing area and the optimized important design parameters.

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