CN117949164B - Time-related data correction method for high-speed continuous wind tunnel balance - Google Patents
Time-related data correction method for high-speed continuous wind tunnel balance Download PDFInfo
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- CN117949164B CN117949164B CN202410334706.5A CN202410334706A CN117949164B CN 117949164 B CN117949164 B CN 117949164B CN 202410334706 A CN202410334706 A CN 202410334706A CN 117949164 B CN117949164 B CN 117949164B
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- 238000012937 correction Methods 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000012360 testing method Methods 0.000 claims abstract description 42
- 238000007664 blowing Methods 0.000 claims abstract description 5
- 238000012545 processing Methods 0.000 claims description 3
- 230000036962 time dependent Effects 0.000 abstract description 11
- 230000000694 effects Effects 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention belongs to the technical field of high-speed wind tunnel tests, and discloses a time-related data correction method of a high-speed continuous wind tunnel balance. The time-dependent data correction method comprises the following steps: acquiring initial readings of a balance; continuously changing Mach numbers M, and acquiring 0-degree angle of attack balance readings under each Mach number M; carrying out a blowing test to obtain balance readings of each Mach number M corresponding to each attack angle step; obtaining a balance end reading; calculating balance zero drift correction under each test train number; determining a balance zero drift correction amount; correcting the initial reading of the balance. The time-dependent data correction method can effectively eliminate balance zero drift caused by temperature change and time change caused by long-time operation of the high-speed continuous wind tunnel, and the compressor can continuously blow a plurality of pole curves after being started at one time, so that the test efficiency is greatly improved, the influence on the compressor caused by frequent turning-off restarting is reduced for playing the advantages of the high-speed continuous wind tunnel, the test efficiency is improved, and the good engineering effect is achieved.
Description
Technical Field
The invention belongs to the technical field of high-speed wind tunnel tests, and particularly relates to a time-related data correction method of a high-speed continuous wind tunnel balance.
Background
High-speed continuous wind tunnels generally adopt balances as measuring instruments for aerodynamic property tests, but temperature changes and time changes caused by long-time operation of the high-speed continuous wind tunnels can cause zero drift of the balances, thereby causing measurement data deviation.
At present, after 1 to 2 pole curves are blown in each time, a compressor is stopped at a reduced speed and restarted, and the balance zero point drift problem of the high-speed continuous wind tunnel is solved by collecting the balance zero point. However, frequent off-vehicle restarting of the compressor affects the service life of the compressor, and causes that the high-speed continuous wind tunnel cannot continuously run, and the test efficiency of the high-speed continuous wind tunnel is greatly reduced.
Currently, there is a need to develop a time-dependent data correction method for a high-speed continuous wind tunnel balance.
Disclosure of Invention
The invention aims to solve the technical problem of providing a time-related data correction method for a high-speed continuous wind tunnel balance, which is used for eliminating balance zero drift caused by temperature change and time change caused by long-time running of the high-speed continuous wind tunnel and realizing the aim of continuously blowing a plurality of pole curves by one-time starting of a compressor.
S10, obtaining initial readings of a balance;
The method comprises the steps of installing a balance on an attack angle mechanism of a high-speed continuous wind tunnel, and collecting initial reading U0 t0 of the balance under the attack angle of 0 degrees;
s20, continuously changing Mach numbers M, and acquiring 0-degree angle of attack balance readings under each Mach number M;
Starting a compressor, continuously changing Mach numbers M in the shortest time required by control of the high-speed continuous wind tunnel, and sequentially obtaining 0-degree attack angles and balance readings under the Mach numbers M: wherein, the method comprises the steps of, wherein, ；
S30, carrying out a blowing test to obtain balance readings of each Mach number M corresponding to each attack angle step;
The compressor is kept in a starting state, the initial Mach number M is kept unchanged according to aerodynamic characteristic test requirements under a specified Mach number M, then an attack angle mechanism of the wind tunnel walks away an attack angle, balance readings under each given test attack angle are obtained, and the balance readings under the attack angle of 0 degree are obtained as follows ；
The compressor changes the rotating speed, continuously adopts a continuous Mach number M mode, and sequentially obtains balance readings of balance readings under each given test attack angle under each remaining Mach number M according to the aerodynamic characteristic test requirement, wherein the balance readings under the attack angle of 0 degree are obtained as follows；
S40, obtaining a balance end reading;
and (3) stopping the compressor at a reduced speed, and collecting balance end reading: ; wherein/> ；
S50, calculating balance zero drift correction under each test vehicle number;
calculating balance zero drift correction amount under each test train number:
；
S60, determining balance zero drift correction;
Respectively judging whether the time difference between t1, t2, t3, … …, tn and t0 is within the linear change range of the balance reading, if so, taking: ；
respectively judging t1, t2, t3, … …, tn and If the time difference of (2) is within the linear range of the balance reading, if taken within the linear range of the balance reading: /(I)；
S70, correcting initial readings of the balance;
The initial reading of the balance after correction is: ；
and substituting the corrected initial balance reading U0 into a balance formula to calculate and obtain corrected aerodynamic characteristic test data in the aerodynamic characteristic test data processing process.
The time-related data correction method of the high-speed continuous wind tunnel balance can effectively eliminate balance zero drift caused by temperature change and time change caused by long-time operation of the high-speed continuous wind tunnel, and the compressor can continuously blow a plurality of pole curves after being started at one time, so that the test efficiency is greatly improved, the influence on the compressor caused by frequent turning-off restarting is reduced for exerting the advantages of the high-speed continuous wind tunnel, and the method has good engineering effect.
Drawings
FIG. 1 is a flow chart of a method for correcting time-dependent data of a high-speed continuous wind tunnel balance according to the present invention;
FIG. 2a is a graph of CL-CD before correction of time dependent data;
FIG. 2b is a graph of a CL-CD corrected by time dependent data;
FIG. 3a is a graph of CY-alpha graph before correction of time dependent data;
FIG. 3b is a graph of CY-alpha graph after time-dependent data correction.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
As shown in fig. 1, the time-dependent data correction method of the high-speed continuous wind tunnel balance of the invention comprises the following steps:
S10, obtaining initial readings of a balance;
The method comprises the steps of installing a balance on an attack angle mechanism of a high-speed continuous wind tunnel, and collecting initial reading U0 t0 of the balance under the attack angle of 0 degrees;
s20, continuously changing Mach numbers M, and acquiring 0-degree angle of attack balance readings under each Mach number M;
Starting a compressor, continuously changing Mach numbers M in the shortest time required by control of the high-speed continuous wind tunnel, and sequentially obtaining 0-degree attack angles and balance readings under the Mach numbers M: wherein, the method comprises the steps of, wherein, ；
S30, carrying out a blowing test to obtain balance readings of each Mach number M corresponding to each attack angle step;
The compressor is kept in a starting state, the initial Mach number M is kept unchanged according to aerodynamic characteristic test requirements under a specified Mach number M, then an attack angle mechanism of the wind tunnel walks away an attack angle, balance readings under each given test attack angle are obtained, and the balance readings under the attack angle of 0 degree are obtained as follows ；
The compressor changes the rotating speed, continuously adopts a continuous Mach number M mode, and sequentially obtains balance readings of balance readings under each given test attack angle under each remaining Mach number M according to the aerodynamic characteristic test requirement, wherein the balance readings under the attack angle of 0 degree are obtained as follows；
S40, obtaining a balance end reading;
and (3) stopping the compressor at a reduced speed, and collecting balance end reading: ; wherein/> ；
S50, calculating balance zero drift correction under each test vehicle number;
calculating balance zero drift correction amount under each test train number:
；
S60, determining balance zero drift correction;
Respectively judging whether the time difference between t1, t2, t3, … …, tn and t0 is within the linear change range of the balance reading, if so, taking: ；
respectively judging t1, t2, t3, … …, tn and If the time difference of (2) is within the linear range of the balance reading, if taken within the linear range of the balance reading: /(I)；
S70, correcting initial readings of the balance;
The initial reading of the balance after correction is: ；
and substituting the corrected initial balance reading U0 into a balance formula to calculate and obtain corrected aerodynamic characteristic test data in the aerodynamic characteristic test data processing process.
Example 1: in the high-speed continuous wind tunnel of the embodiment, the test Mach number is Mach number 0.4, 7 times of repeatability tests are carried out on the air, the test model is an airplane model I, a force measuring balance I is used, and the attack angle range is-3-2 degrees. Fig. 2a shows the corrected leading curve, i.e., the lift coefficient CL and drag coefficient CD curve, with a 7-pass repeatability error bandwidth of 0.00029 for the drag coefficient CD 0. Fig. 2b shows the corrected post-pole curve, i.e., the lift coefficient CL and drag coefficient CD, and it can be seen that the 7-time repetitive error bandwidth of the zero lift drag coefficient CD 0 is reduced to 0.0001 after the time-dependent data correction.
Example 2: in the high-speed continuous wind tunnel of the embodiment, the test Mach number is 0.75, 7 times of repeatability tests are carried out on the air, the test model is an airplane model II, a force measuring balance II is used, and the attack angle range is-4 degrees to 7 degrees. Fig. 3a is a graph of the correction front side force coefficient CY versus the angle of attack α, with a 7-time repeatability error bandwidth of 0.00047 for the side force coefficient CY at 0 ° angle of attack. Fig. 3b is a graph of the corrected lateral force coefficient CY versus the angle of attack α, and it can be seen that the 7-time repeatability error bandwidth of the lateral force coefficient CY at 0 ° angle of attack is reduced to 0.00007 after the time-dependent data correction.
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. The time-related data correction method of the high-speed continuous wind tunnel balance is characterized by comprising the following steps of:
S10, obtaining initial readings of a balance;
The method comprises the steps of installing a balance on an attack angle mechanism of a high-speed continuous wind tunnel, and collecting initial reading U0 t0 of the balance under the attack angle of 0 degrees;
s20, continuously changing Mach numbers M, and acquiring 0-degree angle of attack balance readings under each Mach number M;
Starting a compressor, continuously changing Mach numbers M in the shortest time required by control of the high-speed continuous wind tunnel, and sequentially obtaining 0-degree attack angles and balance readings under the Mach numbers M: Wherein/> ；
S30, carrying out a blowing test to obtain balance readings of each Mach number M corresponding to each attack angle step;
The compressor is kept in a starting state, the initial Mach number M is kept unchanged according to aerodynamic characteristic test requirements under a specified Mach number M, then an attack angle mechanism of the wind tunnel walks away an attack angle, balance readings under each given test attack angle are obtained, and the balance readings under the attack angle of 0 degree are obtained as follows ；
The compressor changes the rotating speed, continuously adopts a continuous Mach number M mode, and sequentially obtains balance readings of balance readings under each given test attack angle under each remaining Mach number M according to the aerodynamic characteristic test requirement, wherein the balance readings under the attack angle of 0 degree are obtained as follows；
S40, obtaining a balance end reading;
and (3) stopping the compressor at a reduced speed, and collecting balance end reading: ; wherein/> ；
S50, calculating balance zero drift correction under each test vehicle number;
calculating balance zero drift correction amount under each test train number:
；
S60, determining balance zero drift correction;
Respectively judging whether the time difference between t1, t2, t3, … …, tn and t0 is within the linear change range of the balance reading, if so, taking: ；
respectively judging t1, t2, t3, … …, tn and If the time difference of (2) is within the linear range of the balance reading, if taken within the linear range of the balance reading: /(I)；
S70, correcting initial readings of the balance;
The initial reading of the balance after correction is: ；
and substituting the corrected initial balance reading U0 into a balance formula to calculate and obtain corrected aerodynamic characteristic test data in the aerodynamic characteristic test data processing process.
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