CN114018527A - Design method of semi-automatic interactive wind tunnel test scheme - Google Patents
Design method of semi-automatic interactive wind tunnel test scheme Download PDFInfo
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- CN114018527A CN114018527A CN202111316805.3A CN202111316805A CN114018527A CN 114018527 A CN114018527 A CN 114018527A CN 202111316805 A CN202111316805 A CN 202111316805A CN 114018527 A CN114018527 A CN 114018527A
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- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention discloses a design method of a semi-automatic interactive wind tunnel test scheme. The design method of the wind tunnel test scheme comprises the steps of establishing a database and a program library and designing the test scheme, wherein the process of designing the test scheme comprises the steps of inputting information, determining a scaling ratio, calculating a load, screening a balance, selecting a device, virtually assembling, checking interference, simulating movement, configuring a camera and generating a report. The wind tunnel test scheme design method can integrate the working experience into the design process of the preliminary test scheme, reduce the optimization iteration times of the design parameters of the preliminary test scheme and shorten the design time of the preliminary test scheme; the preliminary test scheme can confirm the installation position of the aircraft model through computer virtual assembly, the operation problem existing in the preliminary test scheme is found through the dynamic simulation test process of the computer, the preliminary test scheme is conveniently returned to be continuously modified, the final test scheme is obtained, and the problems encountered in the implementation process of the final test scheme are reduced.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a design method of a semi-automatic interactive wind tunnel test scheme.
Background
The wind tunnel test is a main means for predicting the aerodynamic performance of the aircraft and acquiring key aerodynamic data required by the design of the aircraft. The aerodynamic problems in modern aerospace vehicle design have been addressed to date, in large part, by wind tunnel testing. The flow field of the aircraft is directly and physically simulated through a wind tunnel test, and the authenticity and reliability of the obtained test result cannot be replaced by other means. Therefore, the wind tunnel test plays an important role in the aircraft development process. The quality of the wind tunnel test scheme design directly relates to the effect and the period of the whole wind tunnel test.
At present, the design of the wind tunnel test scheme mainly depends on the personal work experience of workers, and the design time spent by different workers is greatly different, namely, the design time is short for several hours, and the design time is long for several days, even weeks and months.
At present, a design method of a semi-automatic interactive wind tunnel test scheme needs to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a design method of a semi-automatic interactive wind tunnel test scheme.
The design method of the semi-automatic interactive wind tunnel test scheme comprises the following steps:
a. building databases and libraries
a1. Establishing a wind tunnel database, and inputting key parameters of a wind tunnel, including the size of a wind tunnel test section, the test Mach number, the Reynolds number, the temperature, the attack angle, the sideslip angle, the roll angle and the like;
a2. establishing a test device database, wherein the test device comprises a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a locking nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support; inputting characteristic parameters, storage positions and working states of the existing testing device into a testing device database;
a3. developing a parameterized design program of the test device in modules, inputting characteristic parameters in each module, and automatically generating a corresponding test device;
a4. developing a virtual assembly visualization program, and having the functions of assembly demonstration and motion demonstration;
a5. developing a motion simulation program with a rigidity and strength checking function;
a6. developing an optical configuration program with optical camera installation and optical path demonstration functions;
b. design of test protocol
b1. Inputting information; inputting characteristic parameters of the aircraft, and calculating the maximum projection area of the theoretical appearance of the aircraft;
b2. determining the scaling; according to the requirement that the blockage degree epsilon of a conventional hypersonic wind tunnel is less than or equal to 8%, calculating the maximum projection area of the aircraft within the range of a test attack angle, a sideslip angle and a roll angle, determining the scaling of the aircraft model according to the preset model blockage degree epsilon as the ratio of the projection area of the aircraft model to the area of the outlet of the spray pipe, and obtaining the characteristic parameters of the aircraft model;
b3. calculating the load; calculating the aerodynamic load of the aircraft model, namely the aerodynamic force and aerodynamic moment coefficients of the aircraft model relative to a reference point according to the provided estimated aerodynamic force coefficient of the aircraft; taking an aircraft model pressure center from a reference point;
b4. screening balances; selecting an existing balance in the test device database of step a2 according to the aerodynamic loads of the aircraft model; if the existing balance does not meet the pneumatic load requirement of the aircraft model, designing the required balance by using the balance module of the step a 3;
b5. a selection device; selecting devices including a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a locking nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support in the test device database of the step a 2;
b6. virtual assembly; operating the virtual assembly visualization program of the step a4, and assembling the aircraft model, the balance and the test device; calculating the distance between the aircraft model head and the nozzle outlet; calculating the position of the wind tunnel rotation center on the aircraft model;
b7. checking interference; the virtual assembly visualization program in the step a4 is operated, dynamic visualization operation is carried out within the range of the test attack angle, the sideslip angle and the rolling angle, whether the aircraft model is interfered with the wind tunnel or not is checked, and if the aircraft model is interfered with the wind tunnel, the steps b 4-b 6 are repeated until the aircraft model is not interfered with the wind tunnel;
b8. motion simulation; operating the motion simulation program in the step a5, and performing simulation check on the strength and the rigidity of the aircraft model, the balance and the test device to avoid that the wind tunnel test data quality of the aircraft model is influenced by insufficient strength and rigidity;
b9. configuring a camera; operating the optical configuration program of the step a6, setting parameters of an optical measurement device including an optical camera and illumination, and dynamically simulating an optical measurement test, and checking the geometrical interference among the optical camera, the illumination, the aircraft model, the wind tunnel and the camera view field by setting the position and the angle of the optical camera and the illumination, the type of a lens and the attitude of the aircraft model; through multiple iterative adjustment, geometric interference is avoided;
b10. generating a report; and determining relevant information of the wind tunnel test of the aircraft model, generating an information report and finishing the design of the wind tunnel test scheme.
The semi-automatic interactive wind tunnel test scheme design method can integrate working experience into the design process of the preliminary test scheme, reduces the optimization iteration times of the design parameters of the preliminary test scheme, and shortens the design time of the preliminary test scheme; the preliminary test scheme can confirm the installation position of the aircraft model through computer virtual assembly, the operation problem existing in the preliminary test scheme is found through the dynamic simulation test process of the computer, the preliminary test scheme is conveniently returned to be continuously modified, the final test scheme is obtained, and the problems encountered in the implementation process of the final test scheme are reduced.
Drawings
FIG. 1 is a flow chart of a semi-automatic interactive wind tunnel test scheme design method of the present invention;
FIG. 2 is an outline view of an aircraft model selected by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 3 is a balance support rod selected by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 4 is a switching section selected by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 5 is a copper sleeve selected by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 6a is a top view of a positioning key selected by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 6b is a front view of a positioning key selected by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 7 is an assembly drawing of an aircraft model obtained by the design method of the semi-automatic interactive wind tunnel test scheme of the present invention;
FIG. 8 is an assembled view of an aircraft model in a wind tunnel;
FIG. 9 is a final test scenario design table obtained by the semi-automatic interactive wind tunnel test scenario design method of the present invention.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
The aircraft model of the embodiment is HB-2, and the hypersonic wind tunnel is a CARDC hypersonic wind tunnel with the diameter of phi 1 m, and the implementation process is as follows:
the design method of the semi-automatic interactive wind tunnel test scheme comprises the following steps:
a. building databases and libraries
a1. Establishing a wind tunnel database, and inputting key parameters of a wind tunnel, including the size of a wind tunnel test section, the test Mach number, the Reynolds number, the temperature, the attack angle, the sideslip angle, the roll angle and the like;
a2. establishing a test device database, wherein the test device comprises a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a locking nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support; inputting characteristic parameters, storage positions and working states of the existing testing device into a testing device database;
a3. developing a parameterized design program of the test device in modules, inputting characteristic parameters in each module, and automatically generating a corresponding test device;
a4. developing a virtual assembly visualization program, and having the functions of assembly demonstration and motion demonstration;
a5. developing a motion simulation program with a rigidity and strength checking function;
a6. developing an optical configuration program with optical camera installation and optical path demonstration functions;
b. design the test protocol as shown in FIG. 1
b1. Inputting information; inputting characteristic parameters of the aircraft, and calculating the maximum projection area of the theoretical appearance of the aircraft;
b2. determining the scaling; according to the requirement that the blockage degree epsilon of a conventional hypersonic wind tunnel is less than or equal to 8%, calculating the maximum projection area of the aircraft within the range of a test attack angle, a sideslip angle and a roll angle, determining the scaling of the aircraft model according to the preset model blockage degree epsilon as the ratio of the projection area of the aircraft model to the area of the outlet of the spray pipe, obtaining the characteristic parameters of the aircraft model, and obtaining the aircraft model shown in the screenshot of fig. 2;
b3. calculating the load; calculating the aerodynamic load of the aircraft model, namely the aerodynamic force and aerodynamic moment coefficients of the aircraft model relative to a reference point according to the provided estimated aerodynamic force coefficient of the aircraft; taking an aircraft model pressure center from a reference point;
b4. screening balances; selecting an existing balance in the test device database of step a2 according to the aerodynamic loads of the aircraft model; if the existing balance does not meet the pneumatic load requirement of the aircraft model, designing the required balance by using the balance module of the step a 3;
b5. a selection device; selecting devices including a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a locking nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support in the test device database of the step a2, wherein the specific devices are shown in corresponding screenshots, namely, fig. 3-5, fig. 6a and fig. 6 b;
b6. virtual assembly; operating the virtual assembly visualization program of the step a4, and assembling the aircraft model, the balance and the test device, specifically referring to the screenshot, namely fig. 7; calculating the distance between the aircraft model head and the nozzle outlet; calculating the position of the wind tunnel rotation center on the aircraft model, specifically referring to a screenshot, namely fig. 8;
b7. checking interference; the virtual assembly visualization program in the step a4 is operated, dynamic visualization operation is carried out within the range of the test attack angle, the sideslip angle and the rolling angle, whether the aircraft model is interfered with the wind tunnel or not is checked, and if the aircraft model is interfered with the wind tunnel, the steps b 4-b 6 are repeated until the aircraft model is not interfered with the wind tunnel;
b8. motion simulation; operating the motion simulation program in the step a5, and performing simulation check on the strength and the rigidity of the aircraft model, the balance and the test device to avoid that the wind tunnel test data quality of the aircraft model is influenced by insufficient strength and rigidity;
b9. configuring a camera; operating the optical configuration program of the step a6, setting parameters of an optical measurement device including an optical camera and illumination, and dynamically simulating an optical measurement test, and checking the geometrical interference among the optical camera, the illumination, the aircraft model, the wind tunnel and the camera view field by setting the position and the angle of the optical camera and the illumination, the type of a lens and the attitude of the aircraft model; through multiple iterative adjustment, geometric interference is avoided;
b10. generating a report; and determining relevant information of the wind tunnel test of the aircraft model, generating an information report shown in the screenshot of fig. 9, and finishing the design of the wind tunnel test scheme.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (1)
1. A design method for a semi-automatic interactive wind tunnel test scheme is characterized by comprising the following steps:
a. building databases and libraries
a1. Establishing a wind tunnel database, and inputting key parameters of a wind tunnel, including the size of a wind tunnel test section, the test Mach number, the Reynolds number, the temperature, the attack angle, the sideslip angle, the roll angle and the like;
a2. establishing a test device database, wherein the test device comprises a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a locking nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support; inputting characteristic parameters, storage positions and working states of the existing testing device into a testing device database;
a3. developing a parameterized design program of the test device in modules, inputting characteristic parameters in each module, and automatically generating a corresponding test device;
a4. developing a virtual assembly visualization program, and having the functions of assembly demonstration and motion demonstration;
a5. developing a motion simulation program with a rigidity and strength checking function;
a6. developing an optical configuration program with optical camera installation and optical path demonstration functions;
b. design of test protocol
b1. Inputting information; inputting characteristic parameters of the aircraft, and calculating the maximum projection area of the theoretical appearance of the aircraft;
b2. determining the scaling; according to the requirement that the blockage degree epsilon of a conventional hypersonic wind tunnel is less than or equal to 8%, calculating the maximum projection area of the aircraft within the range of a test attack angle, a sideslip angle and a roll angle, determining the scaling of the aircraft model according to the preset model blockage degree epsilon as the ratio of the projection area of the aircraft model to the area of the outlet of the spray pipe, and obtaining the characteristic parameters of the aircraft model;
b3. calculating the load; calculating the aerodynamic load of the aircraft model, namely the aerodynamic force and aerodynamic moment coefficients of the aircraft model relative to a reference point according to the provided estimated aerodynamic force coefficient of the aircraft; taking an aircraft model pressure center from a reference point;
b4. screening balances; selecting an existing balance in the test device database of step a2 according to the aerodynamic loads of the aircraft model; if the existing balance does not meet the pneumatic load requirement of the aircraft model, designing the required balance by using the balance module of the step a 3;
b5. a selection device; selecting devices including a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a locking nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support in the test device database of the step a 2;
b6. virtual assembly; operating the virtual assembly visualization program of the step a4, and assembling the aircraft model, the balance and the test device; calculating the distance between the aircraft model head and the nozzle outlet; calculating the position of the wind tunnel rotation center on the aircraft model;
b7. checking interference; the virtual assembly visualization program in the step a4 is operated, dynamic visualization operation is carried out within the range of the test attack angle, the sideslip angle and the rolling angle, whether the aircraft model is interfered with the wind tunnel or not is checked, and if the aircraft model is interfered with the wind tunnel, the steps b 4-b 6 are repeated until the aircraft model is not interfered with the wind tunnel;
b8. motion simulation; operating the motion simulation program in the step a5, and performing simulation check on the strength and the rigidity of the aircraft model, the balance and the test device to avoid that the wind tunnel test data quality of the aircraft model is influenced by insufficient strength and rigidity;
b9. configuring a camera; operating the optical configuration program of the step a6, setting parameters of an optical measurement device including an optical camera and illumination, and dynamically simulating an optical measurement test, and checking the geometrical interference among the optical camera, the illumination, the aircraft model, the wind tunnel and the camera view field by setting the position and the angle of the optical camera and the illumination, the type of a lens and the attitude of the aircraft model; through multiple iterative adjustment, geometric interference is avoided;
b10. generating a report; and determining relevant information of the wind tunnel test of the aircraft model, generating an information report and finishing the design of the wind tunnel test scheme.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114608794A (en) * | 2022-05-11 | 2022-06-10 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for measuring aerodynamic coefficient of model wind tunnel virtual flight test |
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