A method for processing flight vehicle simulation result data

Abstract

This application relates to the technical field of electronic digital data processing, and particularly to a method for processing aircraft simulation result data. The method includes the following steps: obtaining the.f06 and.xdb result files corresponding to the working condition time input by the user; obtaining a frequency list according to the.f06 result file; obtaining the vibration modes and vibration mode slopes corresponding to each contour node; constructing a cloud map library, a vibration mode curve library, and a vibration mode slope curve library; displaying the cloud map that matches the modal number input by the user; if the user sets the matching cloud map as the cloud map corresponding to the preset order, storing the corresponding relationship between the modal number input by the user and the preset order in the relationship library; repeating the above two steps until an indication that the construction of the relationship library input by the user is completed is obtained; displaying the cloud map, vibration mode curve, and vibration mode slope curve that match the order input by the user. The present invention realizes the processing and display of simulation result data, and improves the user experience.

Description

Technical Field

[0001] The present invention relates to the technical field of electronic digital data processing, and particularly to a method for processing aircraft simulation result data. Background Art

[0002] In the prior art, the Patran software can be used to model a model, and after the modeling is completed, the Nastran software can be used to simulate the model. However, the simulation result data output by the Nastran software is relatively raw data. In order to further obtain some parameters related to the model, such as the vibration mode and vibration mode frequency, etc., users need to manually search for and analyze a large amount of relevant raw data, and the user experience is poor. In order to improve the user experience, how to process the simulation result data output by the Nastran software and optimize the visual display of the simulation results is an urgent problem to be solved. Summary of the Invention

[0003] The purpose of the present invention is to provide a method for processing aircraft simulation result data to process the simulation result data output by the Nastran software and optimize the visual display of the simulation results, and improve the user experience.

[0004] According to the present invention, a method for processing aircraft simulation result data is provided, including the following steps:

[0005] S100, obtain the working condition time input by the user on the first user interface, match the result subfolder after the Nastran software completes the solution for the aircraft according to the working condition time, the result subfolder includes a.f06 result file and an.xdb result file, the.f06 result file includes the frequency values of the aircraft under each mode corresponding to the working condition time, and the.xdb file includes the X-axis coordinates, Y-direction vibration mode amplitudes, and Z-direction vibration mode amplitudes of each node of the aircraft under each mode corresponding to the working condition time; a list of working condition times corresponding to the aircraft is displayed on the first user interface.

[0006] S200, obtain a frequency list corresponding to the working condition time according to the.f06 result file, and display the frequency list on the first user interface; the frequency list includes the numbers corresponding to each mode and the frequency values corresponding to each mode.

[0007] S300, drive the Patran software to bind and read the.xdb file, and drive the Patran software to obtain the vibration modes and vibration mode slopes corresponding to each contour node of the aircraft under each mode corresponding to the working condition time according to the result of reading the.xdb file.

[0008] S400, construct a cloud map library, a mode shape curve library, and a mode shape slope curve library; the cloud map library includes cloud maps in each mode corresponding to the working condition time, and the cloud maps are constructed based on the X-axis coordinates, Y-direction mode shape amplitudes, and Z-direction mode shape amplitudes of each node of the aircraft in the corresponding mode; the mode shape curve library includes mode shape curves in each mode corresponding to the working condition time, the abscissa of the mode shape curve is the X-axis coordinate of each contour node of the aircraft in the corresponding mode, and the ordinate of the mode shape curve is the mode shape of each contour node of the aircraft in the corresponding mode; the mode shape slope curve library includes mode shape slope curves in each mode corresponding to the working condition time, the abscissa of the mode shape slope curve is the X-axis coordinate of each contour node of the aircraft in the corresponding mode, and the ordinate of the mode shape slope curve is the mode shape slope of each contour node of the aircraft in the corresponding mode.

[0009] S500, match in the cloud map library according to the mode number input by the user on the first user interface, and display the matched cloud map on the first user interface.

[0010] S600, if the user sets the matched cloud map as the cloud map corresponding to the preset order on the first user interface, then store the corresponding relationship between the mode number input by the user on the first user interface and the preset order in the relationship library; if the user does not set the matched cloud map as the cloud map corresponding to the preset order on the first user interface, then determine that there is no corresponding relationship between the mode number input by the user on the first user interface and the preset order.

[0011] S700, if the user re-enters the mode number on the first user interface, then repeat steps S500 - S600; until an indication that the construction of the relationship library input by the user is completed is obtained.

[0012] S800, match in the relationship library according to the order input by the user on the second user interface to obtain the matched mode, and match in the cloud map library, the mode shape curve library, and the mode shape slope curve library according to the matched mode, and display the cloud map, the mode shape curve, and the mode shape slope curve matched with the matched mode on the second user interface.

[0013] Compared with the prior art, the present invention has obvious beneficial effects. By means of the above technical solutions, the aircraft simulation result data processing method provided by the present invention can achieve considerable technological progress and practicality, and has wide utilization value in the industry. It has at least the following beneficial effects:

[0014] The present invention realizes the construction of a cloud map library, a mode shape curve library, and a mode shape slope curve library corresponding to the working condition time input by the user. Thus, the user only needs to input relevant information to see the matching cloud map, mode shape curve, and mode shape slope curve on the display interface, eliminating the cumbersome process of the user's own data analysis of the simulation results and providing a good user experience. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0016] Figure 1 Schematic diagram of the.f06 result file of the present invention;

[0017] Figure 2 Schematic diagram of the aircraft model constructed by the Patran software of the present invention;

[0018] Figure 3 First-order cloud map of the aircraft of the present invention;

[0019] Figure 4 Second-order cloud map of the aircraft of the present invention;

[0020] Figure 5 Third-order cloud map of the aircraft of the present invention;

[0021] Figure 6 Schematic diagram of the mode shape curve of the aircraft of the present invention;

[0022] Figure 7 Schematic diagram of the mode shape slope curve of the aircraft of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, rather than all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0024] According to the present invention, a method for processing aircraft simulation result data is provided, as Figure 1 shown, including the following steps:

[0025] S100. Obtain the working condition time input by the user on the first user interface, and match the result subfolder after the Nastran software completes the solution for the aircraft. The result subfolder includes a.f06 result file and an.xdb result file. The.f06 result file includes the frequency values of the aircraft in each mode corresponding to the working condition time, and the.xdb file includes the X-axis coordinates, Y-direction vibration mode amplitudes, and Z-direction vibration mode amplitudes of each node of the aircraft in each mode corresponding to the working condition time. A list of working condition times corresponding to the aircraft is displayed on the first user interface.

[0026] Before starting the simulation, the user will manually select the storage location of the simulation result data, that is, the storage address of the result folder after the Nastran software solves the aircraft is known. Thus, when the user inputs the working condition time they want to view on the first user interface, they can match it in the above-mentioned known result folder after the aircraft is solved to obtain the result subfolder corresponding to the working condition time the user wants to view.

[0027] The working condition time refers to the moment when the mass of the model (the aircraft model in the present invention) changes with time. The user will preset the working condition time, and the number of working condition times is not unique. The Nastran software will store the result files after solving the aircraft in different subfolders according to the working condition time. Thus, the data in the subfolder obtained by matching according to the working condition time the user wants to view are all data corresponding to the working condition time the user inputs.

[0028] The result subfolder corresponding to the working condition time the user wants to view includes many files, such as a.f06 result file and an.xdb result file. When the number of modes corresponding to the working condition time the user wants to view is not unique, the above-mentioned.f06 result file includes the frequency values of the aircraft in each mode corresponding to the above-mentioned working condition time, and the above-mentioned.xdb file includes the X-axis coordinates, Y-direction vibration mode amplitudes, and Z-direction vibration mode amplitudes of each node of the aircraft in each mode corresponding to the working condition time. In addition, the above-mentioned.xdb file also includes the numbers and position information of each node, etc.

[0029] A list of working condition times corresponding to the aircraft is displayed on the first user interface. The user can input the working condition time they want to view by selecting the working condition time they want to view on the first user interface.

[0030] S200. Obtain a frequency list corresponding to the working condition time according to the.f06 result file, and display the frequency list on the first user interface. The frequency list includes the numbers corresponding to each mode and the frequency values corresponding to each mode.

[0031] Optionally, obtain a frequency list corresponding to the working condition time according to the.f06 result file, including:

[0032] S210, obtain the start and end positions of all paragraphs containing frequency values in the.f06 result file. Among them, the start position of the paragraph containing frequency values is the position of the third row and the fifth column under the character REAL EIGENVALUES in the.f06 result file, and the end position of the paragraph containing frequency values is the position of the first row and the fifth column under the character PAGE in the.f06 result file.

[0033] As Figure 1 shown, the boxed area is the paragraph containing frequency values. There may be multiple paragraphs containing frequency values in the.f06 result file. The search and positioning of paragraphs containing frequency values can be achieved according to the method of determining the start and end positions above.

[0034] S220, splice the frequency values in the obtained paragraph containing frequency values before and after, and construct a frequency list corresponding to the working condition time in the order of the numbers of the corresponding modes.

[0035] When only 1 paragraph containing frequency values appears in the.f06 result file, then use the frequency value with the smallest mode number corresponding to this paragraph as the first frequency in the frequency list, and use the frequency value with the second smallest mode number corresponding to this paragraph as the second frequency in the frequency list, and so on, to obtain the frequency list. As Figure 1 shown, the first column under the character REAL EIGENVALUES in the.f06 result file corresponds to the mode number.

[0036] When more than 2 paragraphs containing frequency values appear in the.f06 result file, then traverse each paragraph in the order from top to bottom. Use the frequency value with the smallest mode number corresponding to the first paragraph as the first frequency in the frequency list, and use the frequency value with the second smallest mode number corresponding to the first paragraph as the second frequency in the frequency list, and so on, until all the frequency values in the first paragraph are added to the frequency list; then add the frequency values in the second paragraph to the frequency list in a similar manner as above; and so on, until all the frequency values of all paragraphs are added to the frequency list, and thus the frequency list is constructed.

[0037] The present invention displays the frequency list on the first user interface. The frequency list includes the numbers corresponding to each mode and the frequency values corresponding to each mode. The number corresponding to each mode and the corresponding frequency value form a row in the list; thus, the user can input the mode number in S500 by clicking on the corresponding row.

[0038] The S300 drives the Patran software to bind and read the.xdb file, and drives the Patran software to obtain the vibration modes and vibration mode slopes corresponding to each contour node of the aircraft in each mode corresponding to the working condition time according to the result of reading the.xdb file.

[0039] Optionally, driving the Patran software to obtain the vibration modes corresponding to each contour node of the aircraft in each mode corresponding to the working condition time according to the result of reading the.xdb file includes:

[0040] S310, for any mode, obtain the mean value of the Y-direction vibration mode amplitude and the mean value of the Z-direction vibration mode amplitude of each node of the aircraft corresponding to this mode.

[0041] S320, if the mean value of the Y-direction vibration mode amplitude is greater than the mean value of the Z-direction vibration mode amplitude, obtain the ratio of the Y-direction vibration mode amplitude of each contour line node of the aircraft to the Y-direction vibration mode amplitude of the vertex node of the aircraft, and use the corresponding ratio as the vibration mode corresponding to each contour node; if the mean value of the Y-direction vibration mode amplitude is not greater than the mean value of the Z-direction vibration mode amplitude, obtain the ratio of the Z-direction vibration mode amplitude of each contour node of the aircraft to the Z-direction vibration mode amplitude of the vertex node of the aircraft, and use the corresponding ratio as the vibration mode corresponding to each contour node.

[0042] The contour nodes in the present invention refer to the nodes on the top contour line in the aircraft model; after successful modeling in the Patran software, the contour nodes will be stored in a separate group, and thus, the relevant processing of the contour nodes can be achieved by directly retrieving the nodes in this group.

[0043] Optionally, driving the Patran software to obtain the vibration mode slopes corresponding to each contour node of the aircraft in each mode corresponding to the working condition time according to the result of reading the.xdb file includes:

[0044] S330, obtain the X-axis coordinate values and the corresponding vibration mode values of each contour line node of the aircraft.

[0045] S340, use the slope of the vibration mode value corresponding to each contour line node of the aircraft changing with the X-axis coordinate value as the vibration mode slope corresponding to each contour node.

[0046] Preferably, the S300 in the present invention also drives the Patran software to obtain the modal mass of the aircraft in each mode corresponding to the working condition time according to the result of reading the.xdb file, and stores it in a preset report file for later display to the user. The method for obtaining the modal mass includes: obtaining the Y-direction vibration mode amplitude Y 0 and the Z-direction vibration mode amplitude Z 0 of the vertex node of the aircraft, and then obtaining as the modal mass.

[0047] S400. Build a cloud map library, a mode shape curve library, and a mode shape slope curve library. The cloud map library includes cloud maps in each mode corresponding to the working condition time. The cloud map is constructed based on the X-axis coordinates, Y-direction mode shape amplitudes, and Z-direction mode shape amplitudes of each node of the aircraft in the corresponding mode. The mode shape curve library includes mode shape curves in each mode corresponding to the working condition time. The abscissa of the mode shape curve is the X-axis coordinate of each profile node of the aircraft in the corresponding mode, and the ordinate of the mode shape curve is the mode shape of each profile node of the aircraft in the corresponding mode. The mode shape slope curve library includes mode shape slope curves in each mode corresponding to the working condition time. The abscissa of the mode shape slope curve is the X-axis coordinate of each profile node of the aircraft in the corresponding mode, and the ordinate of the mode shape slope curve is the mode shape slope of each profile node of the aircraft in the corresponding mode.

[0048] S500. Match according to the mode number input by the user on the first user interface in the cloud map library, and display the matched cloud map on the first user interface.

[0049] S600. If the user sets the matched cloud map as the cloud map corresponding to the preset order on the first user interface, then store the corresponding relationship between the mode number input by the user on the first user interface and the preset order in the relationship library; if the user does not set the matched cloud map as the cloud map corresponding to the preset order on the first user interface, then determine that there is no corresponding relationship between the mode number input by the user on the first user interface and the preset order.

[0050] In the present invention, the order corresponding to each cloud map needs to be set by the user. Optionally, the preset orders include the first order, the second order, and the third order. On the first user interface, there are order setting buttons of "Set as the first order", "Set as the second order", and "Set as the third order". Thus, after the user clicks on a certain order setting button, it is possible to know which order the cloud map displayed on the first interface is. Since the cloud map displayed on the first interface is the cloud map corresponding to the mode number input on the first user interface, it is also possible to obtain the corresponding relationship between the mode number input on the first user interface and the preset order. If after the user inputs a certain mode label, the user does not set the order of the cloud map displayed on the first interface but continues to click on another mode number, in this case, it is determined that there is no corresponding relationship between the above-mentioned certain mode label and the preset order.

[0051] S700. If the user re-enters the mode number on the first user interface, then repeat steps S500 - S600; until an indication indicating that the construction of the relationship library input by the user is completed is obtained.

[0052] Since the frequency list may include more than one mode number, the user may repeatedly input the mode number and set the order multiple times. Therefore, each time the user re-enters the mode number on the first user interface, the steps S500 - S600 are repeatedly executed. After the user finishes setting the order, the user will input an indication indicating the completion of the relationship library construction. Optionally, there is a button on the first user interface to indicate the completion of the order setting, and the user clicks the button to indicate the completion of the relationship library construction.

[0053] S800, perform matching in the relationship library according to the order input by the user on the second user interface to obtain the matching mode, and perform matching in the cloud map library, vibration mode curve library, and vibration mode slope curve library according to the matching mode, and display the cloud map, vibration mode curve, and vibration mode slope curve matching the matching mode on the second user interface.

[0054] Such as Figures 2 - 5 They are respectively a schematic diagram of an aircraft model constructed by Patran software, the first-order cloud map of the aircraft corresponding to the working condition time input by the user, the second-order cloud map of the aircraft corresponding to the working condition time input by the user, and the third-order cloud map of the aircraft corresponding to the working condition time input by the user. Such as Figures 6 - 7 They are respectively the vibration mode curve and vibration mode slope curve of the aircraft corresponding to the working condition time input by the user. Optionally, the vibration mode curves corresponding to each order can also be displayed separately, and the vibration mode slope curves corresponding to each order can be displayed separately.

[0055] Although some specific embodiments of the present invention have been described in detail by way of examples, those skilled in the art should understand that the above examples are only for illustration and not for limiting the scope of the present invention. Those skilled in the art should also understand that various modifications can be made to the embodiments without departing from the scope and spirit of the present invention. The scope of the present invention is defined by the appended claims.

Claims

1. A method for processing aircraft simulation result data, characterized in that, it includes the following steps: S100. Obtain the working condition time input by the user on the first user interface, match the result subfolder after the aircraft is solved by Nastran software according to the working condition time, the result subfolder includes.f06 result files and.xdb result files, the.f06 result files include the frequency values of the aircraft under each mode corresponding to the working condition time, and the.xdb files include the X-axis coordinates, Y-direction vibration mode amplitudes, and Z-direction vibration mode amplitudes of each node of the aircraft under each mode corresponding to the working condition time; a list of working condition times corresponding to the aircraft is displayed on the first user interface; S200. Obtain a frequency list corresponding to the working condition time according to the.f06 result files, and display the frequency list on the first user interface; the frequency list includes the numbers corresponding to each mode and the frequency values corresponding to each mode; S300. Drive Patran software to bind and read the.xdb files, and drive Patran software to obtain the vibration modes and vibration mode slopes corresponding to each profile node of the aircraft under each mode according to the results of reading the.xdb files; S400. Construct a cloud map library, a vibration mode curve library, and a vibration mode slope curve library; the cloud map library includes cloud maps under each mode corresponding to the working condition time, and the cloud maps are constructed according to the X-axis coordinates, Y-direction vibration mode amplitudes, and Z-direction vibration mode amplitudes of each node of the aircraft under the corresponding mode; the vibration mode curve library includes vibration mode curves under each mode corresponding to the working condition time, the abscissa of the vibration mode curve is the X-axis coordinate of each profile node of the aircraft under the corresponding mode, and the ordinate of the vibration mode curve is the vibration mode of each profile node of the aircraft under the corresponding mode; the vibration mode slope curve library includes vibration mode slope curves under each mode corresponding to the working condition time, the abscissa of the vibration mode slope curve is the X-axis coordinate of each profile node of the aircraft under the corresponding mode, and the ordinate of the vibration mode slope curve is the vibration mode slope of each profile node of the aircraft under the corresponding mode; S500. Match in the cloud map library according to the mode number input by the user on the first user interface, and display the matched cloud map on the first user interface; S600. If the user sets the matched cloud map as the cloud map corresponding to the preset order on the first user interface, store the corresponding relationship between the mode number input by the user on the first user interface and the preset order in the relationship library; If the user does not set the matched cloud map as the cloud map corresponding to the preset order on the first user interface, it is determined that there is no corresponding relationship between the mode number input by the user on the first user interface and the preset order; S700. If the user re-enters the mode number on the first user interface, repeat steps S500 - S600; until an indication indicating that the construction of the relationship library by the user input is completed is obtained; S800 matches in the relation library according to the order input by the user on the second user interface to obtain the matched mode, and matches in the cloud atlas library, the mode shape curve library, and the mode shape slope curve library according to the matched mode, and displays the cloud atlas, the mode shape curve, and the mode shape slope curve matched with the matched mode on the second user interface.

2. The method according to claim 1, wherein, in S200, a frequency list corresponding to the working condition time is obtained according to the.f06 result file, including: S210, obtaining the start and end positions of all paragraphs containing frequency values in the.f06 result file, wherein the start position of the paragraph containing frequency values is the position of the third row and the fifth column under the character REAL EIGENVALUES in the.f06 result file, and the end position of the paragraph containing frequency values is the position of the first row and the fifth column on the character PAGE in the.f06 result file; S220, splicing the frequency values in the obtained paragraph of frequency values before and after, and constructing a frequency list corresponding to the working condition time in the order of the numbers of the corresponding modes.

3. The method according to claim 1, wherein, in S300, driving the Patran software to obtain the mode shapes corresponding to each contour node of the aircraft in each mode corresponding to the working condition time according to the result of reading the.xdb file, including: S310, for any mode, obtaining the mean value of the Y-direction mode shape amplitudes and the mean value of the Z-direction mode shape amplitudes of each node of the aircraft corresponding to the mode; S320, if the mean value of the Y-direction mode shape amplitudes is greater than the mean value of the Z-direction mode shape amplitudes, obtaining the ratio of the Y-direction mode shape amplitude of each contour line node of the aircraft to the Y-direction mode shape amplitude of the vertex node of the aircraft, and using the corresponding ratio as the mode shape corresponding to each contour node; if the mean value of the Y-direction mode shape amplitudes is not greater than the mean value of the Z-direction mode shape amplitudes, obtaining the ratio of the Z-direction mode shape amplitude of each contour node of the aircraft to the Z-direction mode shape amplitude of the vertex node of the aircraft, and using the corresponding ratio as the mode shape corresponding to each contour node.

4. The method according to claim 3, wherein, in S300, driving the Patran software to obtain the mode shape slopes corresponding to each contour node of the aircraft in each mode corresponding to the working condition time according to the result of reading the.xdb file, including: S330, obtaining the X-axis coordinate values and the corresponding mode shape values of each contour line node of the aircraft; S340, using the slope of the change of the mode shape values corresponding to each contour line node of the aircraft with the X-axis coordinate values as the mode shape slope corresponding to each contour node.

5. The method according to claim 1, wherein, in S600, the relation library is in the form of an excel table.

6. The method according to claim 1, wherein, a button indicating the completion of the order setting is displayed on the first user interface, and the user indicates the completion of the construction of the relation library by clicking the button indicating the completion of the order setting.

7. The method according to claim 1, wherein, the preset orders include the first order, the second order, and the third order.

8. The method according to claim 1, wherein, the second user interface includes four parts. The first part is used to display a list of orders that can be selected by the user. The second part is used to display a contour map that matches the order input by the user on the second user interface. The third part is used to display a vibration mode curve that matches the order input by the user on the second user interface. The third part is used to display a vibration mode slope curve that matches the order input by the user on the second user interface.

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