Load input and trimming method based on mass data loading program

Abstract

The application provides a load input and balancing method based on a large batch of data loading procedures, which comprises the following steps: statistics of load positions, inertial forces and active forces are carried out to form a data file; after the data file is processed by the loading procedure, the modeling software Hypermesh is inputted, the batch operation of point creation and load loading is completed by the modeling software Hypermesh, and the loading MPC file containing the point and corresponding load information is automatically generated; the loading MPC file is imported into the finite element analysis software Patran; the load information is calculated by the finite element analysis software Patran to obtain the resultant force and the resultant moment of all loads; whether the total machine resultant force and the total machine resultant moment are balanced is judged; if balanced, it indicates that the load does not need to be balanced; if not balanced, the compensation force or the compensation moment needs to be provided to balance the total machine resultant force or the total machine resultant moment. The application can quickly and accurately input and balance a large batch of load data to be processed, reduces the type overall development cycle and cost, and has good universality.

Description

Technical Field

[0001] This invention belongs to the field of structural design simulation technology, and relates to a load input and balancing method based on a large-scale data loading program. Background Technology

[0002] The structural design of aircraft requires a comprehensive consideration of the trade-off between weight reduction and stiffness improvement. Furthermore, the product's lifecycle dictates the urgency of iterative strength design. Finite element analysis is a crucial component of this strength design process. The accuracy and speed of the analysis are determined by the ability to accurately and quickly apply loads under various operating conditions to the finite element model, while the balance of these loads directly impacts the accuracy of the analysis results.

[0003] Currently, the common method for data input and balancing of load conditions with large loads is as follows: load conditions are filtered according to the load report. The load data of the severe load conditions obtained by the filter usually contain forces in three directions and no less than 60 load positions. Before strength calculation, the load positions are first manually established, and then the load data is manually input into the corresponding load positions to complete the load input. At the same time, the resultant force and resultant moment are manually calculated according to the load positions and corresponding forces provided in the load report. Finally, the resultant force and resultant moment results are used to determine whether the load is balanced, and the load data input and balancing work is completed. The whole process is inefficient, time-consuming, and prone to input and calculation errors, which seriously affect and restrict the subsequent analysis work. Summary of the Invention

[0004] The purpose of this invention is to at least solve one of the problems existing in the prior art.

[0005] Therefore, this invention provides a load input and balancing method based on a large-scale data loading program. By using a self-developed loading program in combination with the modeling software Hypermesh and the finite element analysis software Patran, it is possible to quickly and accurately input and balance the large-scale load data to be processed, which provides a guarantee for improving the accuracy and speed of subsequent finite element analysis, reducing the overall development cycle and cost of the model, and has good versatility.

[0006] The technical solution of the present invention is as follows:

[0007] A load input and balancing method based on a large-scale data loading program, the method is as follows:

[0008] Step 1: Analyze the load report, select a working condition, and statistically analyze the load location, inertial force, and active force of the fuselage for the selected working condition to form data file 1. Data file 1 contains load data for load location, inertial force, and active force.

[0009] Step 2: Process the data file 1 obtained in Step 1 using the loading program, converting it into a data file 2 that can be received by the modeling software Hypermesh. Input the data file 2 into the modeling software Hypermesh, and use the modeling software Hypermesh to create points at the load locations contained in the data file 2. Apply loads to the inertial forces and active forces at the load locations contained in the data file 2. Finally, complete the batch operation of point creation and load application. After the data input is completed, automatically generate a loaded MPC file containing point and corresponding load information.

[0010] Step 3: Import the loaded MPC file into the finite element analysis software Patran; use Patran's load calculation function to calculate the load information and obtain the resultant force and resultant moment of all loads.

[0011] Step 4: Determine whether the resultant force and resultant moment of the entire machine are balanced. If they are balanced, it means that no load balancing is required. If they are not balanced, a compensating force or a compensating moment is required to balance the resultant force or moment and the resultant moment of the entire machine.

[0012] Furthermore, in step two, when creating load locations in batches:

[0013] Based on the load location, fill in the X, Y, Z coordinates of the points to be created and the reference coordinate system into the Excel spreadsheet;

[0014] Create a txt document, copy the information from the Excel spreadsheet into the txt document, and then change the file extension of the txt document to tcl to create a tcl file.

[0015] In the modeling software Hypermesh, open File→Run→Tcl / Tk Script in sequence, and run the tcl file to create a batch of load locations for the inertial load data in Hypermesh.

[0016] Furthermore, when creating points in batches, the points are numbered, starting from 1.

[0017] Furthermore, in step two, when loading the load in batches:

[0018] The point number, inertial forces in the X, Y, and Z directions, and reference coordinate system are entered into the table of the loading program. The table includes basic information about the point and load, as well as program execution statements. The basic information about the point and load includes the point number, load information in the three directions, resultant force information, and coordinate system information. The program execution statements include the program's start statement, end statement, and operations for selecting points, creating forces, and normalizing the coordinate system. Through the program execution statements, the position of the point is matched one-to-one with the load at the point position, thus achieving point-load matching.

[0019] Create a second txt document, copy the data from the table in the data loading program into the second txt document, and modify the format in the second txt document;

[0020] Change the file extension of the second txt document to tcl, creating a second tcl file;

[0021] In the modeling software Hypermesh, open File→Run→Tcl / Tk Script in sequence, and run the tcl file to perform batch load loading on the inertial forces of the inertial load data in the modeling software Hypermesh;

[0022] Create beam elements that connect all points in the modeling software Hypermesh, i.e., load the MPC file. The loaded MPC file contains all points and the corresponding load information.

[0023] Furthermore, when modifying the format of the second txt document, open the second txt document with UE software and modify the format as follows:

[0024] ① Edit the document and delete the tab character: In the UE software, press Ctrl+R to enter the replace function, and replace "^t" with "space";

[0025] ② Delete redundant consecutive spaces: Use the replace function to replace "space" "space" with "space";

[0026] ③ Command line break: Use the replace function to replace "space*" with "^p*" to complete the line break.

[0027] Furthermore, in step three, the calculation of the resultant force and resultant moment of all loads includes: the calculation of the resultant force and resultant moment of the active forces, and the calculation of the resultant force and resultant moment of the inertial forces;

[0028] The resultant force of the active forces includes: the resultant force Fzx in the X direction, the resultant force Fzy in the Y direction, and the resultant force Fzz in the Z direction;

[0029] The resultant torque of the active force includes: the resultant torque Mzy in the Y direction of the active force and the resultant torque Mzz in the Z direction of the active force;

[0030] The resultant force of inertial forces includes: the resultant force Fgy in the Y direction of inertial forces and the resultant force Fgz in the Z direction of inertial forces;

[0031] The resultant torque of inertial forces includes: the resultant torque Mgy in the Y direction of the inertial forces and the resultant torque Mgz in the Z direction of the inertial forces.

[0032] Furthermore, in step four, based on the calculation results of the resultant force and resultant torque in step three, it is determined whether the forces and torques in the three directions of the entire machine are balanced:

[0033] If the resultant force in the X direction of the entire machine is Fgx + Fzx = 0 N, the resultant force in the Y direction of the entire machine is Fgy + Fzy = 0 N, and the resultant force in the Z direction of the entire machine is Fgz + Fzz = 0 N, it means that the resultant forces in the X, Y, and Z directions of the entire machine are all in balance; otherwise, it means that they are unbalanced. For the unbalanced resultant forces, a compensating force is provided to balance them until the resultant forces in all three directions of the entire machine are in balance.

[0034] The resultant torque in the Y direction of the entire machine is mgy + Mzy = b N*m.

[0035] The resultant torque in the Z direction of the entire machine is Mgz + Mzz = cN*m. If the absolute values ​​of b and c are less than 10, it means that the resultant torque in the Y direction and the resultant torque in the Z direction of the entire machine are balanced. Otherwise, it means that they are unbalanced. For the unbalanced resultant torque, a compensating torque is provided to balance it until the resultant torque in the Y direction and the Z direction of the entire machine are balanced.

[0036] By applying the above technical solution, the present invention has the following beneficial effects:

[0037] (1) This invention addresses the practical problems of low work efficiency and easy input or calculation errors caused by large load data volume, manual input, and complex balancing calculation processes. It provides a load input and balancing method based on a large-scale data loading program. The method utilizes the loading program and the creation of loading points and loading MPCs for the selected loads. It leverages the secondary development functions of the modeling software Hypermesh to perform batch operations for point creation and force loading, thereby realizing the input of load data. Beam elements connecting all loading points are created in Hypermesh. The created beam elements and their contained load locations and corresponding forces are imported into the finite element analysis software Patran. Patran's load calculation function is used to calculate the imported load data, obtaining the resultant force and resultant moment of all loads to determine whether the load is balanced under the working condition. Therefore, this invention utilizes a self-developed loading program combined with the modeling software Hypermesh and the finite element analysis software Patran to propose a specific method for large-scale load input and balancing. This method completes a crucial step in strength analysis—the rapid and accurate application of analysis inputs. It ensures the accuracy and speed of subsequent finite element analysis and has been successfully applied to the strength analysis process of multiple UAV models under development. It can quickly and accurately input and balance the large batches of load data required for processing, significantly improving work efficiency, avoiding unnecessary cycle repetitions caused by errors, ensuring the accuracy and speed of subsequent finite element analysis, reducing the overall development cycle and cost of the model, and demonstrating good versatility.

[0038] (2) The large amount of load data that needs to be balanced in this invention includes the main power and inertial force of the fuselage. The inertial force usually includes three directions, each containing at least 60 load positions. Under this data scale, manual input is not only inefficient but also prone to input errors. Therefore, this invention utilizes the loading program and the creation of loading points and loading MPC of the selected loads, and uses the secondary development function of the modeling software Hypermesh to perform batch operations of point creation and force loading to realize the input of load data, thus solving the problem that manual input is not only inefficient but also prone to input errors.

[0039] (3) When balancing the load for a selected working condition, this invention requires balancing the three-directional forces and three-directional moments of a large amount of load data. The balancing calculation process involves a large amount of data and is complex. Manual calculation is not only time-consuming but also prone to errors. Therefore, this invention imports the created MPC and its contained load positions and corresponding forces into the finite element analysis software Patran. Patran's load calculation function is used to calculate the imported load data to obtain the resultant force and resultant moment of all loads, so as to determine whether the load is balanced under the working condition. This solves the problems of large amount of data, complex calculation process, long cycle and easy error in manual calculation during the balancing calculation process. Attached Figure Description

[0040] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0041] Figure 1 This is a flowchart of the present invention;

[0042] Figure 2 This is a graph showing the inertial force load data for the YZW working condition in Example 2;

[0043] Figure 3 This is a graph showing the active force load data for the YZW working condition in Example 2;

[0044] Figure 4 This is a schematic diagram of the batch creation of load locations in Example 2;

[0045] Figure 5 This is a schematic diagram of the points corresponding to the load positions in Example 2;

[0046] Figure 6 This is a table diagram illustrating the loading program in Example 2;

[0047] Figure 7 This is a schematic diagram of the modified program in Example 2;

[0048] Figure 8 This is a schematic diagram of the load applied in Example 2;

[0049] Figure 9 This is a schematic diagram illustrating the creation and loading of the MPC file in Example 2;

[0050] Figure 10 This is a schematic diagram illustrating the import of an MPC file into Patran in Example 2;

[0051] Figure 11 This is a schematic diagram of the balancing of inertial forces and torques in Example 2. Detailed Implementation

[0052] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0053] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0054] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0055] Example 1:

[0056] This embodiment provides a load input and balancing method based on a large-scale data loading program. See Appendix. Figure 1 The method is as follows:

[0057] Step 1, Filtering load data:

[0058] Data analysis was performed on the load report to identify the most severe load conditions. Then, one of these conditions was selected, and the load locations, inertial forces, and active forces of the fuselage under the selected severe condition were statistically analyzed to form Data File 1. Data File 1 contains inertial load data and active load data. The inertial load data includes the inertial load locations and their corresponding inertial forces, and the active load data includes the active load locations and their corresponding active forces.

[0059] Step 2, Inputting load data:

[0060] The loading program processes the data file obtained in step one into a data file two that can be received by the modeling software Hypermesh. The data file two is then input into the modeling software Hypermesh. The secondary development function of the modeling software Hypermesh is used to create points for the load locations contained in the data file two, and loads are applied to the inertial forces and active forces at the load locations contained in the data file two. Finally, the batch operation of point creation and load application is completed. After the data input is completed, a loading MPC file containing point and corresponding load information is automatically generated.

[0061] Step 3, Calculation of resultant force and resultant moment:

[0062] Import the loaded MPC file containing point and corresponding load information into the finite element analysis software Patran; use the load calculation function of Patran to calculate the load information imported in step three to obtain the resultant force and resultant moment of all loads.

[0063] Step 4, balancing forces and moments:

[0064] Determine whether the resultant force and resultant moment of the entire machine are balanced. If they are balanced, it means that no load balancing is required. If they are unbalanced, a compensating force or a compensating moment is required to balance the resultant force or moment and the resultant moment of the entire machine.

[0065] Example 2:

[0066] Based on Example 1, this embodiment performs load input and balancing of a large-scale data loading procedure for a certain type of aircraft's load report. The specific steps are as follows:

[0067] In step one, the load reports of a certain type of aircraft are filtered, and the severe right turn (YZW) condition during the landing of the aircraft is selected. Let the reverse heading of the aircraft be the X direction, the vertical upward direction of the fuselage be the Y direction, and the Z direction be determined by the right-hand rule.

[0068] Figure 2 The inertial load data for the YZW load condition are shown in the figure. X represents the load location, and the unit is mm. Figure 1It can be seen that there are a total of 68 load locations, covering the entire cross-section of the fuselage; GNNx, GNNy, and GNNz represent the inertial forces in three directions at each load location, in N;

[0069] Figure 3 The active load data for the YZW working condition are shown in the figure. X represents the load location in mm, and Rx, Ry, and Rz represent the main driving force at each load location in N.

[0070] In step two, by Figure 2 , Figure 3 It is known that the inertial load data has 68 load locations, each with inertial forces in three directions, resulting in a large data volume. In contrast, the active load data has only 2 load locations, resulting in a smaller data volume. Therefore, the input and balancing method proposed in Example 1 is used to process the inertial load data.

[0071] Step 2-1, Batch create load locations:

[0072] like Figure 4 As shown, based on the load position of the inertial load data, fill the X, Y, Z coordinates of the point to be created and the reference coordinate system into an Excel spreadsheet. Create a new TXT document (named in English), copy the information from the Excel spreadsheet into the TXT document, and then change the file extension of the TXT document to tcl to form a tcl file.

[0073] In the modeling software Hypermesh, open File→Run→Tcl / Tk Script in sequence, and run the tcl file to create batch points for the load locations of the inertial load data in Hypermesh; the created points corresponding to the load locations are as follows. Figure 5 As shown; when creating points in batches, the points are numbered, with the point numbering starting from 1 by default.

[0074] Step 2-2, Batch loading of loads:

[0075] like Figure 6 As shown, fill in the point number, the inertial forces in the X, Y, and Z directions, and the reference coordinate system into the table of the loading program. Figure 6 The table is a long, horizontal table. To facilitate viewing the table data, this embodiment will... Figure 6The table is divided into four tables, which can be combined into a complete loading program table in top-down order. The tables include basic information about points and loads, as well as program execution statements. The program execution statements are the white background portion of the tables, including the program's start and end statements, and operations such as selecting points, creating forces, and normalizing the coordinate system. The basic information about points and loads is the gray background portion of the tables, including point numbering, three-directional load information, resultant force information, and coordinate system information. The program execution statements establish a one-to-one correspondence between the point's position and the load at that position, achieving point-load matching. Create a new txt document (named "English"), copy the data from the loaded program's tables into txt document 2, and modify the format in txt document 2. Since the UE software has better format modification capabilities, open txt document 2 with the UE software to modify the format. The modifications are as follows:

[0076] ① Edit the document and delete the tab character: In the UE software, press Ctrl+R to enter the replace function, and replace "^t" with "space";

[0077] ② Delete redundant consecutive spaces: Use the replace function to replace "space" "space" with "space";

[0078] ③ Command line breaks: Use the replace function to replace "space*" with "^p*" to complete the line break;

[0079] Finally, the format of the second txt document was modified. The modified program is as follows: Figure 7 As shown, then change the file extension of the second txt document to tcl, creating a second tcl file;

[0080] In the modeling software Hypermesh, open File→Run→Tcl / Tk Script in sequence, and run the tcl file to batch load the inertial forces of the inertial load data in Hypermesh; the loaded loads are as follows. Figure 8 As shown in the figure; each FORCE is Figure 6 The combined force in;

[0081] exist Figure 9 In the modeling software Hypermesh, create a one-dimensional cell connecting all points, as shown. Figure 9 As shown in the figure, the line segment marked RBE3 (that is, the line connecting all the points) is the created one-dimensional element. The one-dimensional element is the loaded MPC (multipoint constraint) file, which is the created loaded MPC file. The loaded MPC file contains all the points and the corresponding load information. For ease of display, only a few points are shown here. The actual load positions and number of loads are 68 groups.

[0082] In step three, ① the resultant force and resultant moment of the active forces are calculated as follows:

[0083] Since the amount of data on the active forces is relatively small, the resultant force and resultant moment of the active forces can be directly calculated:

[0084] The resultant force of the active force in the X direction is Fzx = 2617 N, the resultant force of the active force in the Y direction is Fzy = 36103 N, and the resultant force of the active force in the Z direction is Fzz = -18051 N.

[0085] The resultant torque in the Y direction of the active force is Mzy = 105230 N*m, and the resultant torque in the Z direction of the active force is Mzz = 210466 N*m; since the active force has no position in the Y and Z directions, it will not generate a resultant torque in the X direction.

[0086] ②The resultant force and resultant moment of inertial forces are calculated as follows:

[0087] Import the created MPC file into the finite element analysis software Patran, such as Figure 10 As shown, the resultant force and resultant moment of inertial forces are calculated in the finite element analysis software Patran: Open Utilities→Loads / BCs→LBCResultants in sequence to obtain the resultant force and resultant moment of inertial forces as follows. Figure 11 As shown in the figure, the unit of force is N, and the unit of resultant torque is N*mm. Therefore, the final resultant force and resultant torque of the inertial forces are as follows:

[0088] The resultant force of inertial forces in the X direction is Fgx = -2617 N, the resultant force of inertial forces in the Y direction is Fgy = -36103 N, and the resultant force of inertial forces in the Z direction is Fgz = 18051 N.

[0089] The resultant moment of the inertial force in the Y direction is Mgy = -105802 N*m, and the resultant moment of the inertial force in the Z direction is Mgz = -213621 N*m. Since the inertial force has no position in the Y and Z directions, it will not generate a resultant moment in the X direction.

[0090] In step four, based on the calculation results of the resultant force and resultant torque in step three, it is determined whether the forces and torques in the three directions of the entire machine are balanced:

[0091] The resultant force in the X direction of the entire machine is: Fgx + Fzx = -2617N + 2617N = 0N.

[0092] The resultant force in the Y direction of the entire machine is: Fgy + Fzy = -36103 N + 36103 N = 0 N.

[0093] The net force in the Z direction for the entire machine is: Fgz + Fzz = 18051 N ± 18051 N = 0 N.

[0094] It can be seen that the resultant force in the X direction, the resultant force in the Y direction, and the resultant force in the Z direction of the entire machine are all in equilibrium;

[0095] The resultant torque in the Y direction of the entire machine is: Mgy + Mzy = -108502 N*m + 105230 N*m = -3272 N*m.

[0096] The resultant torque in the Z direction of the entire machine is: Mgz + Mzz = -213621 N*m + 210466 N*m = -3155 N*m.

[0097] It can be seen that the resultant torque in the Y direction and the resultant torque in the Z direction of the entire machine are unbalanced;

[0098] This provides compensating torques to balance the resultant torques in the Y and Z directions of the entire machine. The compensating torques are as follows:

[0099] Z-direction compensation torque ΔMz=3153N*m, Y-direction compensation torque ΔMy=3271N*m;

[0100] Therefore, the resultant torque in the Y direction of the entire machine after balancing is:

[0101] Mgy+Mzy+ΔMy=-108502N*m+105230N*m+3271N*m=-1N*m,

[0102] The resultant torque in the Z direction of the entire machine after balancing:

[0103] Mgz+Mzz+ΔMz=-213621N*m+210466N*m+3153N*m=-2N*m.

[0104] The calculation results after balancing show that under the YZW working condition, the entire machine is in force balance, and the torque error in the Y and Z directions is no greater than 10 N*m, indicating that the forces and torques of the entire machine are balanced.

[0105] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0106] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0107] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for load input and trim based on a large batch data loader, characterized by, The method is as follows: Step 1: Analyze the load report, select a working condition, and statistically analyze the load location, inertial force, and active force of the fuselage for the selected working condition to form data file 1. Data file 1 contains load data for load location, inertial force, and active force. Step 2: Process the data file 1 obtained in Step 1 using the loading program, converting it into a data file 2 that can be received by the modeling software Hypermesh. Input the data file 2 into the modeling software Hypermesh, and use the modeling software Hypermesh to create points at the load locations contained in the data file 2. Apply loads to the inertial forces and active forces at the load locations contained in the data file 2. Finally, complete the batch operation of point creation and load application. After the data input is completed, automatically generate a loaded MPC file containing point and corresponding load information. Step 3: Import the loaded MPC file into the finite element analysis software Patran; The load calculation function of the finite element analysis software Patran was used to calculate the load information and obtain the resultant force and resultant moment of all loads. Step 4: Determine whether the resultant force and resultant moment of the entire machine are balanced. If they are balanced, it means that no load balancing is required. If they are not balanced, a compensating force or a compensating moment is required to balance the resultant force or moment and the resultant moment of the entire machine.

2. The method of claim 1, wherein, In step two, when creating load locations in batches: Based on the load location, fill in the X, Y, Z coordinates of the points to be created and the reference coordinate system into the Excel spreadsheet; Create a txt document, copy the information from the Excel spreadsheet into the txt document, and then change the file extension of the txt document to tcl to create a tcl file. In the modeling software Hypermesh, open File→Run→Tcl / Tk Script in sequence, and run the tcl file to create a batch of load locations for the inertial load data in Hypermesh.

3. The method of claim 2, wherein the mass input and trim method is based on a bulk data loader program. When creating points in batches, the points are numbered, starting from 1.

4. The method of claim 3, wherein, In step two, when loading the load in batches: The point number, inertial forces in the X, Y, and Z directions, and reference coordinate system are entered into the table of the loading program. The table includes basic information about the point and load, as well as program execution statements. The basic information about the point and load includes the point number, load information in the three directions, resultant force information, and coordinate system information. The program execution statements include the program's start statement, end statement, and operations for selecting points, creating forces, and normalizing the coordinate system. Through the program execution statements, the position of the point is matched one-to-one with the load at the point position, thus achieving point-load matching. Create a second txt document, copy the data from the table in the data loading program into the second txt document, and modify the format in the second txt document; Change the file extension of the second txt document to tcl, creating a second tcl file; In the modeling software Hypermesh, open File→Run→Tcl / Tk Script in sequence, and run the tcl file to perform batch load loading on the inertial forces of the inertial load data in the modeling software Hypermesh; Create beam elements that connect all points in the modeling software Hypermesh, i.e., load the MPC file. The loaded MPC file contains all points and the corresponding load information.

5. The method of loading and trim based on bulk data loader program of claim 4, wherein, When modifying the format of the second txt document, open the second txt document with UE software to modify the format. The modified content is as follows: ① Edit the document and delete the tab characters: In the UE software, press Ctrl+R to enter the replace function, and replace "^t" with "space"; ② Delete redundant consecutive spaces: Use the replace function to replace "space""space" with "space"; ③ Command line breaks: Use the replace function to replace "space*" with "^p*" to complete the line break.

6. The method of loading and trim based on bulk data loader of claim 1, wherein, In step three, the calculation of the resultant force and resultant moment of all loads includes: the calculation of the resultant force and resultant moment of the active forces, and the calculation of the resultant force and resultant moment of the inertial forces; The resultant force of the active forces includes: the resultant force Fzx in the X direction, the resultant force Fzy in the Y direction, and the resultant force Fzz in the Z direction; The resultant torque of the active force includes: the resultant torque Mzy in the Y direction of the active force and the resultant torque Mzz in the Z direction of the active force; The resultant force of inertial forces includes: the resultant force Fgy in the Y direction of inertial forces and the resultant force Fgz in the Z direction of inertial forces; The resultant torque of inertial forces includes: the resultant torque Mgy in the Y direction of the inertial forces and the resultant torque Mgz in the Z direction of the inertial forces.

7. A mass data loading program based load input, trim method as claimed in claim 6, wherein, In step four, based on the calculation results of the resultant force and resultant torque in step three, it is determined whether the forces and torques in the three directions of the entire machine are balanced: If the resultant force in the X direction of the entire machine is Fgx + Fzx = 0 N, the resultant force in the Y direction of the entire machine is Fgy + Fzy = 0 N, and the resultant force in the Z direction of the entire machine is Fgz + Fzz = 0 N, it means that the resultant forces in the X, Y, and Z directions of the entire machine are all in balance; otherwise, it means that they are unbalanced. For the unbalanced resultant forces, a compensating force is provided to balance them until the resultant forces in all three directions of the entire machine are in balance. The resultant torque in the Y direction of the entire machine is mgy + Mzy = b N*m. The resultant torque in the Z direction of the entire machine is Mgz + Mzz = cN*m. If the absolute values ​​of b and c are less than 10, it means that the resultant torque in the Y direction and the resultant torque in the Z direction of the entire machine are balanced. Otherwise, it means that they are unbalanced. For the unbalanced resultant torque, a compensating torque is provided to balance it until the resultant torque in the Y direction and the Z direction of the entire machine are balanced.

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