CN117950668A - Design method of aircraft surface pressure data display software - Google Patents

Abstract

The invention belongs to the technical field of wind tunnel tests, and discloses a design method of aircraft surface pressure data display software. The design method comprises the steps of examining the distribution rule of the pressure measuring points on the surface of the test model, and determining the data of the pressure measuring points; determining a data output format; establishing a pressure measurement display configuration file; establishing an aircraft surface pressure data display software interface; display of aircraft surface pressure data is performed. The design method is based on the distribution of pressure measurement points of the pressure measurement model, the pressure measurement configuration is pre-programmed, test data are read according to the pressure measurement configuration, and then drawing and analysis are carried out according to display requirements. The design method realizes the general design of the aircraft surface pressure data display software, improves the processing and analysis efficiency of the aircraft surface pressure data, and has engineering practical value.

Description

Design method of aircraft surface pressure data display software

Technical Field

The invention belongs to the technical field of wind tunnel tests, and particularly relates to a design method of aircraft surface pressure data display software.

Background

The wind tunnel is a pipeline-shaped test device for generating uniform controllable air flow in the range of a test section, and is used for researching the air flow rule and checking the aerodynamic characteristics of an aircraft or other objects. And (3) supporting a test model of the research object shrinkage ratio in a wind tunnel test section, opening a plurality of pressure measuring holes on the surface of the test model, and researching the aerodynamic characteristics of the test model by measuring the surface pressure of the test model.

In order to intuitively display the pressure measurement result, a plurality of surface pressure data display software is developed in combination with the special requirements of wind tunnel pressure measurement tests. Currently, there is a need to develop an aircraft surface pressure data display software design method.

Disclosure of Invention

The invention aims to provide a design method of aircraft surface pressure data display software, which is used for perfecting the prior art.

A method for designing aircraft surface pressure data display software, the method comprising the steps of:

s10, examining the distribution rule of the pressure measuring points on the surface of the test model, and determining the data of the pressure measuring points;

For a rotating body test model with a cambered surface measuring surface, including a missile, the pressure measuring points on each pressure measuring section are arranged along the azimuth angle theta by taking the corresponding points on the central axis of the test model as dots; for an aircraft test model including an aircraft wing, having a planar measurement surface, the pressure taps on each pressure section are arranged in local chord percentages or three-dimensional coordinates (X, Y, Z); determining the point measurement data as (X, Y, Z, theta); wherein, (X, Y, Z) represents the three-dimensional coordinates of the pressure measurement point, theta represents the number corresponding to the azimuth angle Theta of the pressure measurement point;

s20, determining a data output format;

Dividing data into an A data segment and a B data segment; the data section A is a wind tunnel parameter section, and the test train number, mach number, attack angle, sideslip angle, rapid pressure and Reynolds number are sequentially arranged from front to back; the data section B is a measurement data section, and is sequentially provided with a pressure measuring point serial number and a pressure measuring point pressure coefficient Cp from front to back;

S30, building a pressure measurement display configuration file;

The pressure measurement display configuration file includes the following 5 paragraphs from top to bottom:

the first section: a test name;

And a second section: the total number of the pressure measuring parts distributed with the pressure measuring points on the test model is the total test part, the total number of the pressure measuring sections on each pressure measuring part is the total section number, and the total number of the pressure measuring points on each pressure measuring section is the total point number;

Third section: sequentially defining the names of the pressure measuring parts, the corresponding section numbers and the corresponding section numbers;

Fourth section: the curve display arrangement of each section is described in sequence as follows: selecting one of Cp-X, cp-Y, cp-Z or Theta as an icon; name of the pressure section; the pressure measurement points of the pressure measurement section are points; the serial numbers of all the pressure measuring points are point numbers;

fifth section: the method comprises the steps of sequentially setting pressure measurement point data (X, Y, Z, theta) of each pressure measurement point;

S40, establishing an aircraft surface pressure data display software interface;

The aircraft surface pressure data display software interface comprises a menu bar, a tool bar, a status bar, a drawing parameter window, a file browsing window and a drawing window;

The menu bar comprises a file menu, an editing menu, a path menu, a configuration menu, a drawing menu, a help menu, a difference menu, a dead point processing menu and a version menu; the file menu comprises two options, namely an opening option for opening data from the file and a saving option for saving drawing configuration; the editing menu comprises two options of printing pictures and saving pictures, wherein the printing picture option is used for printing drawing curves, and the saving picture option is used for saving the drawing curves into a picture format; the path menu is used for inputting paths and importing data; the configuration menu is used for generating or loading a pressure measurement display configuration file; the drawing menu comprises drawing curve selection, coordinate axes and line attributes; the help menu displays help items; the difference menu is used for selecting two drawing curves and solving the difference of the two curves; the dead point processing menu is used for removing dead points, which are points where the pressure measurement points are blocked or leak; the version menu is used for displaying the version, the completion time, the author information and the contact information of the aircraft surface pressure data display software;

the tool bar provides shortcut buttons of common options in the menu bar, wherein the shortcut buttons comprise opening, saving, printing, enlarging, shrinking, recovering, saving pictures, loading configuration, loading paths, drawing curve selection, coordinate axes, configuration file generation, curve attribute, component combined display, help document and version information;

the status column is positioned below the interface and displays the name of the pressure measurement test;

under the cooperation of the menu bar, the drawing parameter window, the file browsing window and the drawing window jointly complete the display of the surface pressure data of the aircraft;

s50, displaying surface pressure data of the aircraft;

the display process of the surface pressure data of the aircraft comprises the steps of setting a configuration file on a software interface, loading the configuration file, setting a data path, and carrying out drawing and analysis;

Setting configuration files in two ways, wherein the first is to write the pressure measurement display configuration files in advance according to the requirements of the pressure measurement display configuration files and store the pressure measurement display configuration files in a specified path; the second is to click a loading configuration button in a menu bar, open a configuration file generation window, input a pressure measurement display configuration file on site according to the requirement of the pressure measurement display configuration file, store the pressure measurement display configuration file into a designated path after the pressure measurement display configuration file is generated, or generate test data to test whether the pressure measurement display configuration file is correct;

Loading a configuration file, namely clicking a loading pressure measurement display configuration file in a configuration menu or clicking a loading configuration button in a shortcut button; secondly, selecting a pressure measurement display configuration file; finally, displaying successful loading configuration and completing loading configuration files;

setting a data path, namely clicking a path menu in a configuration menu or clicking a path loading button in a shortcut button, directly copying the path into a path selection frame, and finishing data path setting; secondly, opening data, wherein the data opening modes comprise three modes of reading from Excel, reading from a path and directly reading from a file; clicking the added data again, and adding the data to the list; finally, the successful data import is displayed, and the data path is set;

Drawing and analysis are carried out, and when drawing is carried out, a drawing curve style, a line style and a coordinate axis style are set through a menu bar or a shortcut button; during analysis, the pressure measuring component is combined and displayed according to the requirements, and bad points are removed; after drawing two curves, calculating the difference of the concerned data points, and researching the surface pressure change of the same pressure measuring point under different states; the graph is scaled up, scaled down, or restored.

The design method of the aircraft surface pressure data display software is based on the pressure measurement point distribution of the pressure measurement model, the pressure measurement configuration is compiled in advance, test data are read according to the pressure measurement configuration, and then drawing and analysis are carried out according to display requirements. The design method of the aircraft surface pressure data display software realizes the general design of the aircraft surface pressure data display software, improves the processing and analysis efficiency of the aircraft surface pressure data, and has engineering practical value.

Drawings

FIG. 1 is a flow chart of an aircraft surface pressure data display software design method of the present invention;

FIG. 2 shows pressure taps of a spinodal test model arranged azimuthally;

FIG. 3 is a pressure measurement point of a planar measurement surface of an aircraft test model arranged according to three-dimensional coordinates;

FIG. 4 is a data output format;

FIG. 5 is a display configuration file format for pressure measurements;

FIG. 6a is a pressure measurement curve of a spinodal test model;

Fig. 6b is a pressure measurement curve of a planar measurement surface of an aircraft test model.

Where α in fig. 6a and 6b represents the experimental model angle of attack in "°.

Detailed Description

The invention is described in detail below with reference to the drawings and examples.

Example 1: a method for designing aircraft surface pressure data display software, as shown in fig. 1, the method comprising the steps of:

s10, examining the distribution rule of the pressure measuring points on the surface of the test model, and determining the data of the pressure measuring points;

As shown in fig. 2, for a spinned body test model including a missile and having a cambered surface measuring surface, the pressure measurement points on each pressure measurement section are arranged along an azimuth angle θ with the corresponding points on the central axis of the test model as dots; as shown in fig. 3, for an aircraft test model including an aircraft wing, having planar measurement surfaces, the pressure taps on each pressure section are arranged in local chord percentages or three-dimensional coordinates (X, Y, Z); determining that the pressure measurement point data is (X, Y, Z, theta), wherein (X, Y, Z) represents the three-dimensional coordinates of the pressure measurement point, and Theta represents the number corresponding to the azimuth angle Theta of the pressure measurement point;

s20, determining a data output format;

As shown in fig. 4, data is divided into an a data segment and a B data segment; the data section A is a wind tunnel parameter section, and the test train number, mach number, attack angle, sideslip angle, rapid pressure and Reynolds number are sequentially arranged from front to back; the data section B is a measurement data section, and is sequentially provided with a pressure measuring point serial number and a pressure measuring point pressure coefficient Cp from front to back;

S30, building a pressure measurement display configuration file;

As shown in fig. 5, the pressure measurement display configuration file includes the following 5 paragraphs from top to bottom:

the first section: a test name;

And a second section: the total number of the pressure measuring parts distributed with the pressure measuring points on the test model is the total test part, the total number of the pressure measuring sections on each pressure measuring part is the total section number, and the total number of the pressure measuring points on each pressure measuring section is the total point number;

Third section: sequentially defining the names of the pressure measuring parts, the corresponding section numbers and the corresponding section numbers;

Fourth section: the curve display arrangement of each section is described in sequence as follows: selecting one of Cp-X, cp-Y, cp-Z or Theta as an icon; name of the pressure section; the pressure measurement points of the pressure measurement section are points; the serial numbers of all the pressure measuring points are point numbers;

fifth section: the method comprises the steps of sequentially setting pressure measurement point data (X, Y, Z, theta) of each pressure measurement point;

S40, establishing an aircraft surface pressure data display software interface;

The aircraft surface pressure data display software interface comprises a menu bar, a tool bar, a status bar, a drawing parameter window, a file browsing window and a drawing window;

The menu bar comprises a file menu, an editing menu, a path menu, a configuration menu, a drawing menu, a help menu, a difference menu, a dead point processing menu and a version menu; the file menu comprises two options, namely an opening option for opening data from the file and a saving option for saving drawing configuration; the editing menu comprises two options of printing pictures and saving pictures, wherein the printing picture option is used for printing drawing curves, and the saving picture option is used for saving the drawing curves into a picture format; the path menu is used for inputting paths and importing data; the configuration menu is used for generating or loading a pressure measurement display configuration file; the drawing menu comprises drawing curve selection, coordinate axes and line attributes; the help menu displays help items; the difference menu is used for selecting two drawing curves and solving the difference of the two curves; the dead point processing menu is used for removing dead points, which are points where the pressure measurement points are blocked or leak; the version menu is used for displaying the version, the completion time, the author information and the contact information of the aircraft surface pressure data display software;

the tool bar provides shortcut buttons of common options in the menu bar, wherein the shortcut buttons comprise opening, saving, printing, enlarging, shrinking, recovering, saving pictures, loading configuration, loading paths, drawing curve selection, coordinate axes, configuration file generation, curve attribute, component combined display, help document and version information;

the status column is positioned below the interface and displays the name of the pressure measurement test;

under the cooperation of the menu bar, the drawing parameter window, the file browsing window and the drawing window jointly complete the display of the surface pressure data of the aircraft;

s50, displaying surface pressure data of the aircraft;

the display process of the surface pressure data of the aircraft comprises the steps of setting a configuration file on a software interface, loading the configuration file, setting a data path, and carrying out drawing and analysis;

Setting configuration files in two ways, wherein the first is to write the pressure measurement display configuration files in advance according to the requirements of the pressure measurement display configuration files and store the pressure measurement display configuration files in a specified path; the second is to click a loading configuration button in a menu bar, open a configuration file generation window, input a pressure measurement display configuration file on site according to the requirement of the pressure measurement display configuration file, store the pressure measurement display configuration file into a designated path after the pressure measurement display configuration file is generated, or generate test data to test whether the pressure measurement display configuration file is correct;

Loading a configuration file, namely clicking a loading pressure measurement display configuration file in a configuration menu or clicking a loading configuration button in a shortcut button; secondly, selecting a pressure measurement display configuration file; finally, displaying successful loading configuration and completing loading configuration files;

setting a data path, namely clicking a path menu in a configuration menu or clicking a path loading button in a shortcut button, directly copying the path into a path selection frame, and finishing data path setting; secondly, opening data, wherein the data opening modes comprise three modes of reading from Excel, reading from a path and directly reading from a file; clicking the added data again, and adding the data to the list; finally, the successful data import is displayed, and the data path is set;

drawing and analysis are carried out, as shown in fig. 6a and 6b, when drawing is carried out, drawing curve patterns, line patterns and coordinate axis patterns are set through menu bars or shortcut buttons; during analysis, the pressure measuring component is combined and displayed according to the requirements, and bad points are removed; after drawing two curves, calculating the difference of the concerned data points, and researching the surface pressure change of the same pressure measuring point under different states; the graph is scaled up, scaled down, or restored.

Although embodiments of the invention have been disclosed in the foregoing description and illustrated in the drawings, it will be understood by those skilled in the art that the present invention is not limited to the specific details and illustrations of features and steps set forth herein, and that all features of the invention disclosed, or steps of the method or process, except for mutually exclusive features and/or steps, may be combined in any manner without departing from the principles of the invention.

Claims (1)

1. A method for designing aircraft surface pressure data display software, the method comprising the steps of:

s10, examining the distribution rule of the pressure measuring points on the surface of the test model, and determining the data of the pressure measuring points;

For a rotating body test model with a cambered surface measuring surface, including a missile, the pressure measuring points on each pressure measuring section are arranged along the azimuth angle theta by taking the corresponding points on the central axis of the test model as dots; for an aircraft test model including an aircraft wing, having a planar measurement surface, the pressure taps on each pressure section are arranged in local chord percentages or three-dimensional coordinates (X, Y, Z); determining the point measurement data as (X, Y, Z, theta); wherein, (X, Y, Z) represents the three-dimensional coordinates of the pressure measurement point, theta represents the number corresponding to the azimuth angle Theta of the pressure measurement point;

s20, determining a data output format;

Dividing data into an A data segment and a B data segment; the data section A is a wind tunnel parameter section, and the test train number, mach number, attack angle, sideslip angle, rapid pressure and Reynolds number are sequentially arranged from front to back; the data section B is a measurement data section, and is sequentially provided with a pressure measuring point serial number and a pressure measuring point pressure coefficient Cp from front to back;

S30, building a pressure measurement display configuration file;

The pressure measurement display configuration file includes the following 5 paragraphs from top to bottom:

the first section: a test name;

And a second section: the total number of the pressure measuring parts distributed with the pressure measuring points on the test model is the total test part, the total number of the pressure measuring sections on each pressure measuring part is the total section number, and the total number of the pressure measuring points on each pressure measuring section is the total point number;

Third section: sequentially defining the names of the pressure measuring parts, the corresponding section numbers and the corresponding section numbers;

Fourth section: the curve display arrangement of each section is described in sequence as follows: selecting one of Cp-X, cp-Y, cp-Z or Theta as an icon; name of the pressure section; the pressure measurement points of the pressure measurement section are points; the serial numbers of all the pressure measuring points are point numbers;

fifth section: the method comprises the steps of sequentially setting pressure measurement point data (X, Y, Z, theta) of each pressure measurement point;

S40, establishing an aircraft surface pressure data display software interface;

The aircraft surface pressure data display software interface comprises a menu bar, a tool bar, a status bar, a drawing parameter window, a file browsing window and a drawing window;

The menu bar comprises a file menu, an editing menu, a path menu, a configuration menu, a drawing menu, a help menu, a difference menu, a dead point processing menu and a version menu; the file menu comprises two options, namely an opening option for opening data from the file and a saving option for saving drawing configuration; the editing menu comprises two options of printing pictures and saving pictures, wherein the printing picture option is used for printing drawing curves, and the saving picture option is used for saving the drawing curves into a picture format; the path menu is used for inputting paths and importing data; the configuration menu is used for generating or loading a pressure measurement display configuration file; the drawing menu comprises drawing curve selection, coordinate axes and line attributes; the help menu displays help items; the difference menu is used for selecting two drawing curves and solving the difference of the two curves; the dead point processing menu is used for removing dead points, which are points where the pressure measurement points are blocked or leak; the version menu is used for displaying the version, the completion time, the author information and the contact information of the aircraft surface pressure data display software;

the tool bar provides shortcut buttons of common options in the menu bar, wherein the shortcut buttons comprise opening, saving, printing, enlarging, shrinking, recovering, saving pictures, loading configuration, loading paths, drawing curve selection, coordinate axes, configuration file generation, curve attribute, component combined display, help document and version information;

the status column is positioned below the interface and displays the name of the pressure measurement test;

under the cooperation of the menu bar, the drawing parameter window, the file browsing window and the drawing window jointly complete the display of the surface pressure data of the aircraft;

s50, displaying surface pressure data of the aircraft;

the display process of the surface pressure data of the aircraft comprises the steps of setting a configuration file on a software interface, loading the configuration file, setting a data path, and carrying out drawing and analysis;

Setting configuration files in two ways, wherein the first is to write the pressure measurement display configuration files in advance according to the requirements of the pressure measurement display configuration files and store the pressure measurement display configuration files in a specified path; the second is to click a loading configuration button in a menu bar, open a configuration file generation window, input a pressure measurement display configuration file on site according to the requirement of the pressure measurement display configuration file, store the pressure measurement display configuration file into a designated path after the pressure measurement display configuration file is generated, or generate test data to test whether the pressure measurement display configuration file is correct;

Loading a configuration file, namely clicking a loading pressure measurement display configuration file in a configuration menu or clicking a loading configuration button in a shortcut button; secondly, selecting a pressure measurement display configuration file; finally, displaying successful loading configuration and completing loading configuration files;

setting a data path, namely clicking a path menu in a configuration menu or clicking a path loading button in a shortcut button, directly copying the path into a path selection frame, and finishing data path setting; secondly, opening data, wherein the data opening modes comprise three modes of reading from Excel, reading from a path and directly reading from a file; clicking the added data again, and adding the data to the list; finally, the successful data import is displayed, and the data path is set;

Drawing and analysis are carried out, and when drawing is carried out, a drawing curve style, a line style and a coordinate axis style are set through a menu bar or a shortcut button; during analysis, the pressure measuring component is combined and displayed according to the requirements, and bad points are removed; after drawing two curves, calculating the difference of the concerned data points, and researching the surface pressure change of the same pressure measuring point under different states; the graph is scaled up, scaled down, or restored.