A method for mapping and applying aerodynamic loads in the analysis of airfoil sail structures

Abstract

This invention discloses a method for mapping and applying aerodynamic loads in airfoil sail structure analysis, comprising the following steps: 1. Extracting wind pressure at key points on the sail surface of the aerodynamic model based on the sail analysis conditions; 2. Formatting the aerodynamic load data of the sail; 3. Mapping and applying the loads of the sail structure; 4. Verifying the aerodynamic loads of the sail. This invention achieves an effective mapping of loads obtained from CFD analysis to the structural analysis model; at the same time, this method has strong versatility for handling similar problems. The method of this invention provides a reliable method for load mapping between CFD models and structural models with different mesh distributions, and is applicable to both regular and irregular mesh division of the structural model elements.

Description

Technical Field

[0001] This invention belongs to the field of sail-assisted ship design and construction, specifically relating to a method for applying aerodynamic load mapping in marine airfoil sail structure analysis. Background Technology

[0002] Airfoil-shaped sail propulsion systems have become a popular choice for the green development of ocean-going vessels, and a reliable sail structure design directly determines its successful engineering applications. Sail structure design and analysis involves both aerodynamics and structural analysis. The design process typically begins with CFD methods to perform aerodynamic analysis and optimize the aerodynamic shape of the airfoil. Based on this optimized aerodynamic shape, wind pressure loads are obtained. Then, based on the obtained sail shape, the wind pressure loads are applied to the structural model as input for detailed structural design, ultimately determining the component dimensions that meet various mechanical performance requirements. Currently, commercial software cannot directly achieve a close integration of aerodynamic calculations and structural design. In this process, CFD analysis and structural analysis have different focuses and consider different factors, resulting in different computational model characteristics. A typical problem is that the computational model meshes used in CFD analysis and structural analysis are completely different, making it impossible to match the wind pressure loads given in the CFD analysis stage with those used in the structural analysis stage. Consequently, the CFD loads cannot be directly applied to the structural analysis model. As can be seen from the above sail structure design process, wind pressure load, as the design input of the structure design, is the key to ensuring that the structure design meets the mechanical performance requirements. Therefore, it is necessary to use a reasonable and accurate method to map the wind pressure load onto the structural analysis model.

[0003] Wind load mapping requires addressing both accuracy and efficiency. Firstly, considering the mapping algorithm, due to the differences between the CFD computational mesh and the structural computational mesh, interpolation mapping is necessary. Constructing a high-precision interpolation format is a prerequisite for ensuring the accuracy of subsequent structural analysis. Simultaneously, the number of load points during mapping is enormous, and the structural analysis needs to consider loads at various wind directions, resulting in numerous computational scenarios. Therefore, it is essential to develop a reasonable algorithm to improve mapping processing efficiency, thereby reducing the overall solution time for the structural analysis. Summary of the Invention

[0004] To address the above problems, this invention provides a method for mapping and applying aerodynamic loads in the analysis of airfoil sail structures, which achieves an effective mapping of loads obtained from CFD analysis to the structural analysis model; at the same time, this method also has strong versatility in handling similar problems.

[0005] To achieve the above objectives, the present invention provides a method for aerodynamic load mapping application in airfoil sail structure analysis, comprising the following steps:

[0006] Step 1: Extract wind pressure at discrete points on the sail surface of the aerodynamic model based on the sail analysis conditions; the specific process is as follows:

[0007] Step 101: Analyze the working conditions and coordinate system definition;

[0008] Each operating condition includes wind angle of attack (WA), wind speed (WS); L m (WA m WS m ) represents the m-th operating condition;

[0009] Origin o: is the intersection of the axis of width of the sail and the axis of symmetry, located at the lower edge of the sail height;

[0010] The x-axis is along the width axis of the sail, with positive to the right;

[0011] The y-axis, perpendicular to the axis, points towards the convex surface and is positive;

[0012] The z-axis, along the direction of the sail height, is positive upwards;

[0013] Step 102: For each operating condition, perform aerodynamic analysis of the airfoil sail device using aerodynamic analysis software, outputting the pressure distribution on the outer surface of the sail at various wind attack angles. The pressure load output by the aerodynamic analysis software is expressed as a function in coordinates: Operating Condition L m The output format for the sail's outer surface pressure is (P,x,y,z), where P represents the sail's outer surface pressure, and x, y, and z represent the coordinates; operating condition L m The pressure data is recorded in the first database;

[0014] Step 103: Sort the database in descending order according to the height value of the pressure coordinate points, and the updated database becomes the second database;

[0015] Step 2: Formatting and processing of sail aerodynamic load data:

[0016] Step 201: Process the z-coordinate of the discrete points. The specific process is as follows:

[0017] Step 201-1: Discretize along the height direction: Divide the sail into n segments along the height direction, and label them as 1, 2, ..., i, ..., n from bottom to top; i represents the i-th height segment;

[0018] Step 201-2: For the i-th segment in the height direction, use a unified Z... i The value represents the discrete points within the segment;

[0019] Step 202: Convert the wind pressure data output by CFD into the format used by the structural analysis software ANSYS APDL; generate the inputPm file;

[0020] Step 3: Mapping and applying loads to the sail structure, including the following steps:

[0021] Step 301: Use ANSYS structural finite element analysis software to establish a structural finite element analysis model and read in the inputPm file generated in step 2;

[0022] Step 302: CFD load mapping processing, the specific steps are as follows:

[0023] Step 302-1: Define an array `prelem` to store the loads applied to the sail elements of the structural finite element analysis model. The data format is (Nu, Pele). The array `prelem` is a J-row, 2-column array, where J is the number of elements to be loaded, Nu is the element number of the structural finite element analysis model, and Pele is the load value of the structural element.

[0024] Step 302-2: For each height segment i, the corresponding height coordinate is Z. i Z is selected on the structural finite element analysis model. i and Z i+1 The sail elements between the selected target elements are taken as i=1,…,n-1; the following operation is performed on the j-th selected target element:

[0025] (1) Extract the center coordinates (x) of the target unit j ,y j ,z j ) and unit number Nu j ;

[0026] (2) The location information of the CFD load interpolation point is obtained using the minimum radius method. The specific steps are as follows:

[0027] Based on the inputPm file, in Z i The position is searched along the circumference of the airfoil sail to find the distance from the center coordinates (x j ,y j ,z j The nearest load points to the left and right of the load point are denoted as A and B, respectively, and the pressure at each load point is denoted as P. A P B The coordinates of the load points are denoted as (x... A ,y A ,z A ), (x B ,y B ,z B );

[0028] In Z i+1 The position is searched along the circumference of the airfoil sail to find the distance from the center coordinates (x j,y j ,z j The nearest load points to the left and right of the load are denoted as C and D, respectively, and the pressure at each load point is denoted as P. C P D The coordinates of the load points are denoted as (x, y, y) C ,y C ,z C ), (x D ,y D ,z D );

[0029] (3) The load value on the target element is calculated using a weighted average method;

[0030] (4) The calculated load value Pele j and the corresponding unit number Nu j Stored in the array prelem;

[0031] Step 303: Select the target element to which the load needs to be applied, and apply the structural load in the ANSYS structural analysis software using the sfe command combined with a loop statement, based on the data information in the array prelem.

[0032] Step 4: Verification of aerodynamic loads on the sail:

[0033] After the load is applied, it is necessary to verify the error between the load from the aerodynamic analysis and the resulting load to confirm the accuracy of the loading process; otherwise, the load discretization gradient in step 201 needs to be further adjusted. z; Reload.

[0034] In the preferred method, the specific operation of step 201-1 is as follows:

[0035] The difference between the maximum and minimum z-values ​​of all discrete points within the height segment i. z needs to be obtained from the aerodynamic analysis software used in step 1, and should be less than or equal to 1 / 200 of the height of the sail model and greater than or equal to 0.0001, in meters.

[0036] In the preferred method, in step 201-2: Z i The value is equal to the weighted average of the z-coordinates of all discrete points within the height range, with 4 significant digits retained after the decimal point. This value is then referred to as the third database.

[0037] In the preferred embodiment, the data format in step 202 is denoted as:

[0038] inputPm(a+1,1)=Am(1+a,1),Am(2+a,1),…,Am(8+a,1),Am(9+a,1),Am(10+a,1)

[0039] inputPm(a+1,2)=Am(1+a,2),Am(2+a,2),…,Am(8+a,2),Am(9+a,2),Am(10+a,2)

[0040] inputPm(a+1,3)=Am(1+a,3),Am(2+a,3),…,Am(8+a,3),Am(9+a,3),Am(10+a,3)

[0041] inputPm(a+1,4)=Am(1+a,4),Am(2+a,4),…,Am(8+a,4),Am(9+a,4),Am(10+a,4)

[0042] Where a=10*(k'-1), k'=ceil(k / 10), inputPm(a+1,1) is the pressure data, inputPm(a+1,2) is the x-coordinate data, inputPm(a+1,3) is the y-coordinate data, inputPm(a+1,4) is the z-coordinate data, k is the total number of points in the aerodynamic load, and k' is the total number of rows in inputPm.

[0043] In the preferred embodiment, the load value on the target element is calculated using a weighted average method in step 302-2:

[0044] The weight is the center coordinate (x) j ,y j ,z j The distances between the load points A, B, C, and D and the load points are denoted as d. A d B d C d D And denote the values ​​of load points A, B, C, and D as P. A P B P C P D Then the load value on this unit is:

[0045]

[0046] Where, distance d A d B d C d D Calculated from the coordinates of the load point and the coordinates of the element center point:

[0047]

[0048]

[0049]

[0050] .

[0051] In the preferred method, the specific process of step 4 is as follows:

[0052] Step 401: Set the reference point for aerodynamic load verification: Take the mast support point at the bottom of the sail as the reference point;

[0053] Step 402: In the CFD software, extract the forces in three directions at the reference point;

[0054] Step 403: In the structural finite element analysis software, extract the forces in three directions at the reference point;

[0055] Step 404: Compare the results calculated in steps 402 and 403. If the difference is within 5%, it means that the loading accuracy meets the requirements; otherwise, it is necessary to reset the mesh density, select more detailed target points, and repeat steps 2 and 3.

[0056] The beneficial effects of this invention are as follows:

[0057] 1. The method of the present invention provides a reliable method for load mapping between CFD models and structural models with different mesh distributions, and is applicable to both regular and irregular mesh division of structural model elements.

[0058] 2. The method of this invention processes the z-coordinate of the height mapping point in CFD data, so that during the process of mapping load to the structural model, the load in the vicinity of the height value can be directly selected, avoiding the need to search for all height load points, which greatly improves the load mapping efficiency. Depending on the data dispersion, the efficiency can be improved by 20% to 50%.

[0059] 3. The method of the present invention considers the positional relationship between the target point of the structural model and the CFD load point, uses the minimum radius method to determine the load interpolation point, and considers the positional relationship between the interpolation point and the target point to obtain the load value at the target point by weighted averaging, thereby improving the calculation accuracy.

[0060] 4. This invention comprehensively compares the CFD load with the overall load of the structural model to assess the difference between the load mapping accuracy and the requirements of engineering analysis, thus balancing accuracy and efficiency.

[0061] 5. Considering the load application method, in order to facilitate the extraction of model information such as loading elements or nodes required for the load processing process, and taking into account the complexity of load processing, the APDL language of ANSYS software is used to process the load mapping application; using ANSYS software for structural analysis makes it convenient to handle all calculation tasks in the same software, and has very high engineering applicability. Attached Figure Description

[0062] Figure 1 Schematic diagram of the method for applying aerodynamic load mapping on a sail;

[0063] Figure 2 This is a schematic diagram of the sail coordinate system definition;

[0064] Figure 3 This is a schematic diagram of the load interpolation element search process for the structural model;

[0065] Figure 4 This is a schematic diagram of CFD load mapping applied to the structural model;

[0066] Figure 5 This is an example diagram of the array `prelem`. Detailed Implementation

[0067] like Figure 1 As shown, the present invention provides a method for applying aerodynamic load mapping in the analysis of airfoil sail structures, comprising the following steps:

[0068] Step 1: Extract the aerodynamic loads of the sail obtained from CFD analysis:

[0069] Aerodynamic analysis was conducted using professional aerodynamic analysis software (such as Star CCM+), and the wind pressure at key points on the sail surface of the aerodynamic model was extracted based on the sail analysis conditions.

[0070] Step 101: Design status for structural analysis of the sail device:

[0071] The design conditions for structural analysis and CFD aerodynamic analysis are clearly defined to facilitate the subsequent load transfer, including the definition of analysis conditions and coordinate system.

[0072] 1) Determine the operating conditions for structural analysis of the sail device, including the angle of attack WA and the wind speed WS, and clarify the operating conditions for aerodynamic analysis. Each operating condition is characterized by the corresponding angle of attack and wind speed.

[0073] The numerical simulation of aerodynamics of the sail should cover the wind angle of attack and wind speed under all typical sail operating conditions. m (WA m WS m ) represents the m-th operating condition;

[0074] 2) such as Figure 2 As shown, the coordinate system for structural analysis of the sail device is clearly defined: During the aerodynamic analysis, the model coordinate system is defined as follows:

[0075] Origin o: is the intersection of the axis of width of the sail and the axis of symmetry, located at the lower edge of the sail height;

[0076] The x-axis is along the width axis of the sail, with positive to the right;

[0077] The y-axis, perpendicular to the axis, points towards the convex surface and is positive;

[0078] The z-axis is along the direction of the sail height, with upwards being positive.

[0079] Step 102: For each operating condition, perform aerodynamic analysis of the airfoil sail device using aerodynamic analysis software, outputting the pressure distribution on the outer surface of the sail under different wind attack angles. The pressure load directly output by the software can be expressed as a function of its coordinates. For a specific analysis condition Lm, the output format of the sail outer surface pressure is (P,x,y,z), where P represents the sail outer surface pressure, and x, y, and z represent the coordinates. Operating condition Lm m The pressure data directly output by the aerodynamic analysis software is denoted as database Am0, which is a k-row, 4-column matrix.

[0080] In this embodiment, the airfoil sail dimensions are 14.8m × 35m (chord length × span), the aerodynamic analysis software used is starccm+, the wind angle of attack is 45°, and the wind speed is 20.8m / s. The pressure distribution on the outer surface of the sail obtained through full-scale analysis is as follows (partial data):

[0081]

[0082] Step 103: Sort the database file Am0 in descending order according to the height value of the pressure coordinate points. The updated database is denoted as Am, and it is still a k-row, 4-column matrix.

[0083] Step 2: Formatting and processing of sail aerodynamic load data:

[0084] Step 201: Considering that scattered points within each height range will have a certain bandwidth in the height direction, which reduces the efficiency of subsequent structural data processing, the z-coordinate of the discrete points is processed to adapt to the batch processing requirements of the data.

[0085] 1) Height-direction discretization: Based on the required calculation accuracy, the sail is divided into n segments along the height direction, which are numbered 1, 2, ..., i, ..., n from bottom to top; i represents the i-th height segment;

[0086] The difference between the maximum and minimum z-values ​​of all discrete points within the height segment i. z needs to be obtained based on the actual situation of the aerodynamic analysis numerical model used in step 1, and should not be greater than 1 / 200 of the height of the sail model, nor less than 0.0001m.

[0087] In this embodiment, the sail height is 35m, and the data points are discrete in the height direction. z is set to 0.001m.

[0088] 2) Data discrete point z-coordinate processing: For the i-th segment in the height direction, use a unified Z-coordinate. i The value represents the discrete points within this segment to improve data processing efficiency; Z i The value is equal to the weighted average of the z-coordinates of all discrete points within that height range, rounded to four decimal places. The resulting matrix is ​​denoted as Am1, and is still a k-row, 4-column matrix.

[0089] Step 202: Convert the wind pressure data output from the CFD to a format usable by the structural analysis software ANSYS APDL. The original load database for the sail is large, and there are strict requirements for the data format when loading loads into ANSYS software; each line of data must contain no more than 10 data points. Process the load file obtained above and save it as a txt file for structural load mapping. The data format is denoted as:

[0090] inputPm(a+1,1)=Am(1+a,1),Am(2+a,1),…,Am(8+a,1),Am(9+a,1),Am(10+a,1)

[0091] inputPm(a+1,2)=Am(1+a,2),Am(2+a,2),…,Am(8+a,2),Am(9+a,2),Am(10+a,2)

[0092] inputPm(a+1,3)=Am(1+a,3),Am(2+a,3),…,Am(8+a,3),Am(9+a,3),Am(10+a,3)

[0093] inputPm(a+1,4)=Am(1+a,4),Am(2+a,4),…,Am(8+a,4),Am(9+a,4),Am(10+a,4)

[0094] Where a=10*(k'-1), k'=ceil(k / 10), inputPm(a+1,1) is the pressure data, inputPm(a+1,2) is the x-coordinate data, inputPm(a+1,3) is the y-coordinate data, inputPm(a+1,4) is the z-coordinate data, k is the total number of points in the aerodynamic load, and k' is the total number of rows in inputPm.

[0095] This embodiment has a total of 14613 rows, i.e., k=14613. Further calculation yields the total number of rows k' in inputPm as: k'=ceil(k / 10)=1462

[0096] The pressure data P, after processing, is as follows:

[0097]

[0098] The processed x-coordinate data is as follows:

[0099]

[0100] The processed y-coordinate data is as follows:

[0101]

[0102] The z-coordinate data after processing is as follows:

[0103]

[0104] In step 202, the data is processed using MATLAB and the above file format is output.

[0105] Step 3: Mapping and applying loads to the sail structure:

[0106] Step 301: Use ANSYS structural finite element analysis software to establish a structural finite element analysis model and read in the inputPm file generated in step 2.

[0107] The finite element analysis model of the structure needs to be consistent with the coordinate system of the model used for CFD analysis (otherwise, coordinate transformation is required), and the surface of the sail structure to be loaded should be consistent with the CFD model (otherwise, the effect of its scaling ratio needs to be calculated separately).

[0108] Step 302: CFD Load Mapping Processing: Considering that the mesh size of the actual CFD analysis model is larger or close to that of the structural analysis model, for the same sail model size, one layer of CFD mesh elements will correspond to multiple layers of structural mesh elements. Therefore, data mapping processing is required to map the CFD loads to the structural model. The specific steps are as follows:

[0109] 1) Define an array prelem to store the loads applied to the sail elements of the structural model. The data format is (Nu, Pele).

[0110] The prelem is a J-row, 2-column array, where J is the number of elements to be loaded, Nu is the element number of the structural model, and Pele is the load value of the structural element.

[0111] 2) such as Figure 3 As shown, for each height segment i, the corresponding height coordinate is Z. i In the structural model, Z is chosen. i and Z i+1 The sail elements between these elements are taken as target elements, i=1,…,n-1. For the selected j-th target element, the following operation is performed:

[0112] (1) Extract the center coordinates (x) of the target unit j ,y j ,z j ) and unit number Nu j ;

[0113] (2) The location information of the CFD load interpolation point is obtained using the minimum radius method. The specific steps are as follows:

[0114] Based on the database inputPm, in Z i The position is searched along the circumferential direction of the airfoil sail to find the coordinates (x) of the distance from the center of the cell. j ,y j ,z j The nearest load points to the left and right of the load point are denoted as A and B, respectively, and the pressure at each load point is denoted as P. A P B The coordinates of the load points are denoted as (x, y, y) A ,y A ,z A ), (x B ,y B ,z B );

[0115] In Z i+1 The position is searched along the circumferential direction of the airfoil sail to find the coordinates (x) of the distance from the center of the cell. j ,y j ,z j The nearest load points to the left and right of the load are denoted as C and D, respectively, and the pressure at each load point is denoted as P. C P D The coordinates of the load points are denoted as (x, y, y) C ,y C ,z C ), (xD ,y D ,z D );

[0116] (3) Considering Z i and Z i+1 The load values ​​on the target element were calculated using a weighted average method based on the positional differences between the target element and the CFD load point in the structural model sail surface. The weights were the center coordinates (x, y) of the element. j ,y j ,z j The distances between the load points A, B, C, and D and the load points are denoted as d. A d B d C d D And denote the values ​​of load points A, B, C, and D as P. A P B P C P D Then the load value on this unit is:

[0117]

[0118] Where, distance d A d B d C d D Calculated from the coordinates of the load point and the coordinates of the element center point:

[0119]

[0120]

[0121]

[0122] .

[0123] (4) The calculated element load value Pele j and the corresponding unit number Nu j Stored in the array prelem.

[0124] In this embodiment, the number of units J on the outer surface of the sail is 44458. An example of the calculated array `prelem` is shown below (the schematic representations are the initial and final parts of the array). The first column represents the unit number, and the second column represents the pressure value, such as... Figure 5 As shown.

[0125] Step 303: Select the element to be loaded, and apply the structural load in the ANSYS structural analysis software using the sfe command combined with a loop statement, based on the data information in the prelem array.

[0126] The final load after loading in this embodiment is as follows: Figure 4 As shown:

[0127] Step 4: Verification of aerodynamic loads on the sail:

[0128] After the load is applied, it is necessary to verify the error between the load from the aerodynamic analysis and the resulting load to confirm the accuracy of the loading process; otherwise, the load discretization gradient in step 201 needs to be further adjusted. z, reload.

[0129] Step 401: Set the reference point for aerodynamic load verification: Take the mast support point at the bottom of the sail as the reference point;

[0130] Step 402: In the CFD software, extract the forces in three directions at the reference point;

[0131] Step 403: In the structural analysis software, extract the forces in three directions at the reference point;

[0132] Step 404: Compare the results calculated in steps 402 and 403. If the difference is within 5%, it means that the loading accuracy meets the requirements; otherwise, it is necessary to reset the mesh density, select more detailed target points, and repeat steps 2 and 3.

[0133] After the calculation in this embodiment is completed, the load at the center of the bottom of the sail blade is extracted. The comparison between the support reaction force of the CFD software and the structural model is shown in the table below, which meets the accuracy requirements.

[0134]

[0135] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A method for applying aerodynamic force load mapping in the analysis of a wing sail structure, characterized by, Comprising the following steps: Step 1: based on the sail analysis working condition extraction aerodynamic force model sail surface discrete point wind pressure; The specific process is as follows: Step 101: analysis of working condition and coordinate system definition; Each working condition includes a wind attack angle WA, a wind speed WS; L m (WA m , WS m ) represents the mth working condition; The origin of coordinates o: take the intersection of the sail width axis and the symmetry axis, located at the lower edge of the sail height; X axis, along the sail width axis direction, right for positive; Y axis, perpendicular to the axis direction, pointing to the convex surface for positive; Z axis, along the height direction of the sail, upward for positive; Step 102: For each working condition, the aerodynamic force analysis software is used to analyze the aerodynamic force of the wing sail device, and the pressure distribution on the outer surface of the sail at each wind attack angle is output. The pressure load output by the aerodynamic force analysis software is expressed as a function of the coordinates: working condition L m , the output format of the pressure of the outer surface of the sail is (P, x, y, z), P represents the pressure of the outer surface of the sail, and x, y and z represent coordinates; the pressure data of working condition L m is recorded in the first database; Step 103: according to the height value of the pressure coordinate point, the database is arranged in descending order, and the updated database becomes the second database; Step 2: format processing of sail aerodynamic load data: Step 201: processing of z coordinate of discrete points, the specific process is as follows: Step 201-1: height direction discretization: divide the sail into n sections along the height direction, from bottom to top, marked as 1, 2, …, i, …, n; I represents the i-th height section; Step 201-2: For the i-th segment in the height direction, use a uniform Z i value to represent the discrete points in the segment. Step 202: convert the wind pressure data output by CFD into the format used by ANSYS APDL, the structural analysis software; Generate inputPm file; Step 3: mapping processing and application of sail structure load, comprising the following steps: Step 301: using ANSYS structural finite element analysis software, establish a structural finite element analysis model, read in the inputPm file generated in step 2; Step 302: CFD load mapping processing, the specific steps are as follows: Step 302-1: define the array prelem, which is used to store the load applied to the sail surface element of the structural finite element analysis model, with data format (Nu, Pele); The array prelem is a J row and 2 column array, J is the number of units that need to be loaded, Nu is the unit number of the structural finite element analysis model, and Pele is the load value of the structural unit; Step 302-2: For each height segment i, the corresponding height coordinate is Z i , i = 1, …, n-1; for the selected jth target element, the following operations are performed: i i+1 between Zand Z , i = 1, …, n-1; for the selected jth target element, the following operations are performed: (1) Extract the center coordinates (x j ,y j ,z j ) and the cell number Nu j of the target cell; (2) the minimum radius method is used to obtain the position information of the CFD load interpolation point, the specific steps are as follows: Based on the inputPm file, in the Z i position along the wing sail surface circumferential search, looking for the left and right position of the center coordinates (x j ,y j ,z j ) closest to the load point, CFD load point number is recorded as A, B, load point at the pressure is recorded as P A , P B , load point at the coordinate value is recorded as (x A ,y A ,z A ), (x B ,y B ,z B ); In Z i+1 Position along the wing sail surface circumferential search, looking for the left and right position of the nearest load point from the center coordinates (x j ,y j ,z j ), CFD load point number is recorded as C, D, respectively, the pressure at the load point is recorded as P C , P D , the coordinate value at the load point is recorded as (x C ,y C ,z C ), (x D ,y D ,z D ) ; (3) the load value on the target element is calculated by weighted average method; (4) the calculated load value Pele j and the corresponding cell number Nu j are stored in the array prelem; Step 303: select the target element that needs to be loaded, and apply the structural load in ANSYS structural analysis software by using sfe command combined with loop statement according to the data information in the array prelem; Step 4: verification of sail aerodynamic load: After the load is loaded, it is necessary to confirm the error between the load and the result of the aerodynamic force analysis to confirm the accuracy of the loading process; otherwise, the load discrete gradient in step 201 needs to be further adjusted z; reload.

2. The method of claim 1, wherein the method is applied to the airfoil wing sail structure analysis. The specific operation of step 201-1 is: The difference between the maximum and minimum z values of all discrete points within the highly segmented i z is obtained from the aerodynamic analysis software used in step 1, less than or equal to 200th of the height of the sail model, greater than or equal to 0.0001, unit m.

3. The method of claim 1, wherein the air load is applied to the airfoil of the wing sail structure by using a load mapping method. In step 201-2: Z i The value is equal to the weighted average of the individual discrete point z-coordinates in the height range, rounded to 4 significant digits, which is then recorded as the third database.

4. The method of claim 1, wherein the air load is applied to the airfoil of the wing sail structure. The data format in step 202 is: inputPm(a+1,1)=Am(1+a,1),Am(2+a,1),…,Am(8+a,1),Am(9+a,1),Am(10+a,1) inputPm(a+1,2)=Am(1+a,2),Am(2+a,2),…,Am(8+a,2),Am(9+a,2),Am(10+a,2) inputPm(a+1,3)=Am(1+a,3),Am(2+a,3),…,Am(8+a,3),Am(9+a,3),Am(10+a,3) inputPm(a+1,4)=Am(1+a,4),Am(2+a,4),…,Am(8+a,4),Am(9+a,4),Am(10+a,4) Wherein, a=10*(k'-1), k'=ceil(k / 10), inputPm(a+1,1) is pressure data, inputPm(a+1,2) is x coordinate data, inputPm(a+1,3) is y coordinate data, inputPm(a+1,4) is z coordinate data, k is the total number of points in the aerodynamic load, k' is the total number of rows of inputPm.

5. The method of claim 1, wherein the air load mapping is applied to the airfoil shape of the wing sail structure. The load value on the target unit is calculated in step 302-2 by using the weighted average method: The weight is the distance between the central coordinates (x j ,y j ,z j ) and the positions of the load points A, B, C, and D, respectively denoted as d A , d B , d C , and d D . The values of the load points A, B, C, and D are denoted as P A , P B , P C , and P D . The load value on the unit is: where the distance d A , d B , d C , d D is calculated from the coordinates of the load point and the coordinates of the center point of the element. 。 6. The method of claim 1, wherein the air load is applied to the airfoil of the wing sail structure. The specific process of step 4 is as follows: Step 401: Set the reference point for aerodynamic load verification: take the mast support point at the bottom end of the sail as the reference point; Step 402: In the CFD software, extract the forces in three directions at the reference point; Step 403: In the structural finite element analysis software, extract the forces in three directions at the reference point; Step 404: Compare the results calculated in steps 402 and 403. If the difference is within 5%, it means that the loading accuracy meets the requirements; otherwise, the grid density needs to be re-set, a more detailed target point needs to be selected, and the steps 2 and 3 process needs to be repeated.

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