CN116952523A - Near-field acoustic explosion signal optical measurement method based on velocity field - Google Patents
Near-field acoustic explosion signal optical measurement method based on velocity field Download PDFInfo
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- G—PHYSICS
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
- G01L11/02—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00 by optical means
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Abstract
The invention provides a near-field acoustic explosion signal optical measurement method based on a velocity field, belongs to the technical field of wind tunnel near-field acoustic explosion signal measurement, and solves the problems of flow field interference, complex system and the like in the prior art; according to the invention, the PIV technology is adopted to measure the speed distribution of the flow field, and the relative position between the aircraft model and the PIV measuring area is changed according to the requirement while measuring, so as to obtain a corresponding space speed field; then, through a post-processing program, calculating corresponding space pressure distribution; in the post-processing procedure, the pressure distribution of each point in the corresponding interval is obtained in a mode of calculating different intervals in the space velocity field in a segmented mode; in the calculation process, starting from points which are not disturbed outside the wave system, calculating the points point by point in forward flow, and integrating to obtain the spatial pressure distribution; the invention realizes the non-contact measuring process, has no interference to the flow field, can simultaneously measure a plurality of high acoustic explosion signals and greatly improves the measuring efficiency.
Description
Technical Field
The invention belongs to the technical field of wind tunnel near-field acoustic explosion signal measurement, and particularly relates to a near-field acoustic explosion signal optical measurement method based on a velocity field.
Background
Acoustic explosion is an acoustic phenomenon specific to supersonic flight; when the aircraft makes supersonic speed flight, shock waves and expansion wave systems are generated in the surrounding air, and the wave systems are transmitted to the ground to form N-shaped pressure disturbance, so that the human ear can hear the popping and popping two-sound explosion sound. Since the sound explosion phenomenon can seriously affect the normal life of people, the supersonic flight is generally forbidden on land, and the development of supersonic civil aircraft is severely limited.
Wind tunnel near field acoustic explosion signal measurement is one of important means for researching near field acoustic explosion signal characteristics, and is mainly used for measuring spatial pressure distribution near an aircraft model. The measurement results can be used as verification data of CFD calculation and also can be used as input of far-field propagation models.
The space pressure distribution signal measuring technology developed in the prior art mainly comprises a supersonic probe, a pressure measuring plate, a total reflection pressure measuring rail, a reflection-free pressure measuring rail and the like. The ultrasonic probe has higher measurement precision, but has low measurement test efficiency; the pressure measuring plate has serious boundary layer accumulation and has poor measuring effect; in order to ensure a reflection coefficient of 2.0, the total reflection pressure measuring rail is required to have a certain width, a certain boundary layer influence still exists, and the measurement result is not completely satisfactory; the reflection-free pressure measuring rail basically eliminates the influence of a boundary layer, has a good measuring effect, and has high processing difficulty. In addition, the above measurement means have a certain interference to the flow field, so that the accuracy of the measurement result is affected to a certain extent.
To sum up, the deficiencies of the prior art can also be summarized as the following 4 points:
1. the existing measurement belongs to contact measurement, and has certain interference to a flow field, so that the accuracy of a measurement result is affected;
2. the existing measuring equipment is complex to install, and has certain requirements on the space and the interface of the wind tunnel test section;
3. the prior art cannot utilize the existing wind tunnel test equipment, and different near-field acoustic explosion signal measuring devices are required to be designed and processed according to the specific conditions of the wind tunnel;
4. in the prior art, only one signal on the separation distance can be obtained in one measurement test, and the experimental efficiency is low.
Disclosure of Invention
The invention aims to solve the defect problem of the existing wind tunnel near field acoustic explosion signal measurement technology at least partially, and provides a near field acoustic explosion signal optical measurement method based on a velocity field.
The invention adopts the following technical scheme to achieve the purpose:
a near-field acoustic explosion signal optical measurement method based on a velocity field comprises the following steps: measuring the speed distribution of the flow field by adopting the PIV technology, and changing the relative position between the aircraft model and the PIV measuring area according to the near-field acoustic explosion signal measurement requirement during measurement to obtain a space speed field corresponding to the flow field; calculating the spatial pressure distribution corresponding to the outflow field through a post-processing program according to the spatial velocity field, and taking the spatial pressure distribution as a measurement result; in the post-processing procedure, the pressure distribution of each point in the corresponding interval is obtained in a mode of calculating different intervals in the space velocity field in a segmented mode; in the calculation process, starting from the undisturbed points outside the flow field wave system, calculating point by point in the forward flow direction, and finally integrating to obtain the spatial pressure distribution.
Optionally, changing the relative position between the aircraft model and the PIV measurement region is achieved by a relative position adjustment system disposed within the wind tunnel test section; the relative position adjusting system comprises three types, which respectively correspond to different position adjusting modes and specifically comprises the following steps: a system that adjusts only the position of the aircraft model alone, a system that adjusts only the spatial position of the PIV survey area alone, a system that adjusts both the position of the aircraft model and the spatial position of the PIV survey area.
Further, the space velocity field corresponding to the flow field measured by adopting the PIV technology is an off-body space velocity field, namely a velocity field which does not contain the area where the aircraft model is located; and the post-processing program calculates the space velocity field of the split body to obtain the space pressure distribution corresponding to the flow field.
The region where the separation space velocity field is located is also an acoustic explosion signal measurement region, and a straight line in the region is taken as an extraction line; the direction of the extraction line is parallel to the axis direction of the aircraft model, and the length of the extraction line covers the range of the space wave system in the whole flow field.
Further, the specific process of the post-processing program comprises the following steps:
s1, obtaining speed distribution on an extraction line;
s2, determining a compression section and an expansion section on the extraction line according to the speed distribution;
s3, taking one point on the extraction line in front of the space wave system in the PIV measuring area as a starting point, and sequentially calculating the parameter values of the downstream points on the extraction line by adopting a forward flow point-by-point calculation mode according to the parameter values of the starting point;
and S4, the parameter values comprise the pressure of the corresponding points, and after the parameter values of the points on the extraction line in the PIV measuring region are calculated, the spatial pressure distribution of the corresponding flow field is obtained through integration.
The compression section is a section in which the extraction line speed is reduced, and the expansion section is a section in which the extraction line speed is increased.
In summary, by adopting the technical scheme, the invention has the following beneficial effects:
the invention provides a thought concept for measuring a near-field acoustic explosion signal of a wind tunnel based on PIV technology, namely, the distribution of space pressure is realized by measuring a space velocity field; in the process, the invention creatively provides a mode for calculating the space pressure distribution in a subsection way in a compression section and an expansion section, and calculates the pressure point by point in a concurrent way from an undisturbed point outside a wave system; the invention utilizes the great advantage of the measuring area of PIV measuring technology, and improves the line measurement of the existing pressure measuring rail in the near-field acoustic explosion signal measuring technology to the surface measurement.
In addition, the invention belongs to non-contact measurement, and has no interference to a flow field; the measurement system built by the invention is relatively easy, does not need to additionally install complicated pressure measurement equipment, has low requirements on space and interfaces of the wind tunnel test section, is beneficial to building a near-field acoustic explosion measurement technology in a small-caliber wind tunnel, can simultaneously measure acoustic explosion signals with a plurality of heights, and greatly improves the measurement efficiency; the strict simulation proves that the method is completely feasible and can bring better application effect.
Drawings
FIG. 1 is a schematic diagram of a process of changing relative positions during measurement;
FIG. 2 is a schematic diagram of a separation space velocity field and measurement process;
FIG. 3 is a schematic diagram showing the comparison of the pressure measurement results with the actual results;
FIG. 4 is a schematic diagram showing the comparison of the temperature measurement results with the actual results;
fig. 5 is a schematic diagram showing the comparison of the mach number measurement result and the actual result.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
A near-field acoustic explosion signal optical measurement method based on a velocity field comprises the following steps: measuring the speed distribution of the flow field by adopting the PIV technology, and changing the relative position between the aircraft model and the PIV measuring area according to the near-field acoustic explosion signal measurement requirement during measurement to obtain a space speed field corresponding to the flow field; calculating the spatial pressure distribution corresponding to the outflow field through a post-processing program according to the spatial velocity field, and taking the spatial pressure distribution as a measurement result; in the post-processing procedure, the pressure distribution of each point in the corresponding interval is obtained in a mode of calculating different intervals in the space velocity field in a segmented mode; in the calculation process, starting from the undisturbed points outside the flow field wave system, calculating point by point in the forward flow direction, and finally integrating to obtain the spatial pressure distribution.
PIV (Particle Image Velocimetry) technology is one of the flow field measurement technologies commonly used in wind tunnels; in the embodiment, when PIV technology is adopted to measure the speed distribution of a flow field, trace particles are scattered in the flow field, the trace particles are imaged through a specific time interval, and the displacement of the trace particles in the imaging time interval is obtained based on a cross-correlation algorithm, so that the instantaneous speed of the trace particles is obtained; if the trace particles have high enough flow following performance, the instantaneous speed of the particles can reflect the flow speed at the position in the flow field; because the trace particles can be dispersed in a large quantity, the velocity distribution on a large number of space points can be acquired at the same instant, and the space velocity field corresponding to the flow field at the moment can be obtained.
In order to know the near-field acoustic explosion signal characteristics of an aircraft, the pressure distribution of the detached space of the aircraft model in a wind tunnel needs to be measured, and the relative positions of the aircraft model and measuring equipment generally need to be changed; in the embodiment, the relative position between the aircraft model and the PIV measurement area is changed by a relative position adjusting system arranged in the wind tunnel test section; the relative position adjusting system comprises three types, which respectively correspond to different position adjusting modes and specifically comprises the following steps: a system that adjusts only the position of the aircraft model alone, a system that adjusts only the spatial position of the PIV survey area alone, a system that adjusts both the position of the aircraft model and the spatial position of the PIV survey area; taking the example of a system for individually adjusting the position of an aircraft model, a change in its relative position is schematically illustrated with reference to fig. 1.
Therefore, the space velocity field corresponding to the flow field measured by adopting the PIV technology is the separation space velocity field, i.e. the velocity field which does not contain the area where the aircraft model is located, and the schematic of FIG. 2 can be referred to; the post-processing program calculates the space velocity field of the split body to obtain the space pressure distribution corresponding to the flow field.
In this embodiment, the region where the separation space velocity field is located is also an acoustic explosion signal measurement region, and a straight line in the region is taken as an extraction line; the direction of the extraction line is parallel to the axis direction of the aircraft model, and the length of the extraction line covers the range of the space wave system in the whole flow field.
The preferred extraction line is the velocity field centerline of the PIV measurement region parallel to the aircraft axis direction, the velocity profile on the velocity field centerline being obtained directly in accordance with PIV measurement techniques.
The following is the details of the post-processing procedure, including the following steps:
s1, obtaining speed distribution on an extraction line;
s2, determining a compression section and an expansion section on the extraction line according to the speed distribution;
s3, taking one point on the extraction line in front of the space wave system in the PIV measuring area as a starting point, and sequentially calculating the parameter values of the downstream points on the extraction line by adopting a forward flow point-by-point calculation mode according to the parameter values of the starting point;
and S4, the parameter values comprise the pressure of the corresponding points, and after the parameter values of the points on the extraction line in the PIV measuring region are calculated, the spatial pressure distribution of the corresponding flow field is obtained through integration.
In step S2, the compression section is a section in which the extraction line speed decreases, and the expansion section is a section in which the extraction line speed increases.
In step S3, the parameter values of the starting point include: mach number, pressure and temperature respectively correspond to wind tunnel incoming flow Mach number, wind tunnel static pressure and wind tunnel static temperature, and are all known quantities; the method adopts a forward flow point-by-point calculation mode, and comprises the following specific processes:
the parameters of the upstream known points are Mach numbersPressure->Temperature->Speed->And (c) angle->The method comprises the steps of carrying out a first treatment on the surface of the Wherein, at the beginning of calculation, the upstream known point is the starting point; included angle->Is speed->An included angle with the extraction line;
the parameters of adjacent downstream points are Mach numbers respectivelyPressure->Temperature->Speed->And (c) angle->Also included angle->Is speed->The angle with the extraction line is due to the speed +.>Known->It is also known to take the specific heat ratio +.>；
When the downstream point is in the compression section, according to the oblique shock wave formula, the following is adopted:
due toAnd->It is known that the shock angle +.>Then, the method is obtained according to the following various formulas:
i.e. the pressure at the downstream point in the compression zone is completedTemperature->Mach number->Is calculated by the computer.
Next, when the downstream point is within the expansion zone, according toThe expansion wave relationship is as follows:
due toAnd->It is known that +.>And then, by utilizing the isentropic relation, obtaining:
i.e. the pressure at the downstream point in the expansion zone is completedTemperature->Mach number->Is calculated by the computer.
At the point of obtaining the pressure at the downstream pointTemperature->And Mach number->Then, taking the downstream point as a new upstream point, and taking the next adjacent point on the extraction line as a new downstream point so as to realize the forward flow point-by-point calculation process; and continuously calculating the parameter value of the new downstream point by using the known parameter value obtained by calculating the new upstream point to obtain the pressure distribution on the extraction line, and integrating to obtain the spatial pressure distribution of the corresponding flow field.
Example 2
Based on example 1, the present example describes the implementation and effects of the present invention with specific experimental measurement data.
The method of example 1 was applied to first obtain the velocity profile of the flow field. Obtaining all data of a streaming field of a certain cone column body in a numerical simulation mode, wherein the incoming stream Mach number。
Data of 19 points as shown in the line of the velocity field are extracted as shown in table 1 below.
In Table 1, the 1 st point is outside the wave system, mach number of the pointPressure->Temperature->Respectively the Mach number, static pressure and static temperature of incoming flow; in actual measurement, these parameters are provided by the wind tunnel measurement system. Position x, speed of 19 points>And (c) angle->Given by PIV measurements, i.e. known parameters at the time of actual measurement calculation.
TABLE 1 data sheet of points extracted after actual measurement
Next, a compression section and an expansion section are determined; according to the speed change condition corresponding to each point, a compression interval between points 1 and 4, an expansion interval between points 4 and 7, a compression interval between points 7 and 9, an expansion interval between points 9 and 11, a compression interval between points 11 and 13, and an expansion interval between points 13 and 19 can be determined. In this embodiment, when the post-processing program runs, the interval in which the next point is located can be determined by comparing the speeds of two adjacent points.
Then, according to the calculation method and formula corresponding to different intervals in the embodiment, since the parameters of the point 1 are known, the mach number, pressure and temperature of each subsequent point can be calculated point by point, so that the last 18 points are unknown points of the relevant parameters to be calculated, and the calculated results are shown in the following table 2.
The mach numbers, pressures and temperatures in tables 1 and 2 are compared, and reference is made to the schematic illustrations of fig. 3-5.
Table 2 table of data of points calculated according to the method
The comparison shows that the calculation result of the unknown point (namely the corresponding actual measurement result when the method is actually applied) and all the data values obtained in the table 1 in a numerical simulation mode have better consistency, and the calculation process of the method can accurately reflect the measurement condition of the actual flow field and has higher precision, so that the effects of no need of installing pressure measurement equipment in a wind tunnel test section, low space interface requirement and greatly improved measurement efficiency can be realized.
Claims (9)
1. A near-field acoustic explosion signal optical measurement method based on a velocity field is characterized by comprising the following steps of: measuring the speed distribution of the flow field by adopting the PIV technology, and changing the relative position between the aircraft model and the PIV measuring area according to the near-field acoustic explosion signal measurement requirement during measurement to obtain a space speed field corresponding to the flow field; calculating the spatial pressure distribution corresponding to the outflow field through a post-processing program according to the spatial velocity field, and taking the spatial pressure distribution as a measurement result; in the post-processing procedure, the pressure distribution of each point in the corresponding interval is obtained in a mode of calculating different intervals in the space velocity field in a segmented mode; in the calculation process, starting from the undisturbed points outside the flow field wave system, calculating point by point in the forward flow direction, and finally integrating to obtain the spatial pressure distribution.
2. The optical measurement method of near-field acoustic explosion signals based on velocity fields according to claim 1, wherein: the relative position between the aircraft model and the PIV measuring area is changed by a relative position adjusting system arranged in the wind tunnel test section; the relative position adjusting system comprises three types, which respectively correspond to different position adjusting modes and specifically comprises the following steps: a system that adjusts only the position of the aircraft model alone, a system that adjusts only the spatial position of the PIV survey area alone, a system that adjusts both the position of the aircraft model and the spatial position of the PIV survey area.
3. The optical measurement method of near-field acoustic explosion signals based on velocity fields according to claim 1, wherein: the space velocity field corresponding to the flow field measured by adopting the PIV technology is an off-body space velocity field, namely a velocity field which does not contain the area where the aircraft model is located; and the post-processing program calculates the space velocity field of the split body to obtain the space pressure distribution corresponding to the flow field.
4. A method for optically measuring a near field acoustic burst signal based on a velocity field as claimed in claim 3, wherein: the region where the separation space velocity field is located is also an acoustic explosion signal measurement region, and a straight line in the region is taken as an extraction line; the direction of the extraction line is parallel to the axis direction of the aircraft model, and the length of the extraction line covers the range of the space wave system in the whole flow field.
5. The optical measurement method of near field acoustic explosion signal based on velocity field according to claim 4, wherein the specific process of the post-processing procedure comprises the following steps:
s1, obtaining speed distribution on an extraction line;
s2, determining a compression section and an expansion section on the extraction line according to the speed distribution;
s3, taking one point on the extraction line in front of the space wave system in the PIV measuring area as a starting point, and sequentially calculating the parameter values of the downstream points on the extraction line by adopting a forward flow point-by-point calculation mode according to the parameter values of the starting point;
and S4, the parameter values comprise the pressure of the corresponding points, and after the parameter values of the points on the extraction line in the PIV measuring region are calculated, the spatial pressure distribution of the corresponding flow field is obtained through integration.
6. The optical measurement method of near-field acoustic explosion signals based on velocity fields according to claim 5, wherein: in step S1, the extraction line is a speed field center line parallel to the axis direction of the aircraft in the PIV measurement area, and the speed distribution on the speed field center line is directly obtained according to the PIV measurement technology; in step S2, the compression section is a section in which the extraction line speed decreases, and the expansion section is a section in which the extraction line speed increases.
7. The optical measurement method of near-field acoustic explosion signals based on velocity fields according to claim 6, wherein: in step S3, the parameter values of the starting point include: the Mach number, the pressure and the temperature respectively correspond to the wind tunnel incoming flow Mach number, the wind tunnel static pressure and the wind tunnel static temperature and are all known quantities; the forward flow point-by-point calculation mode adopted in the step S3 is as follows:
the parameters of the upstream known points are Mach numbersPressure->Temperature->Speed->And (c) angle->The method comprises the steps of carrying out a first treatment on the surface of the At the beginning of the calculation, the upstream known point is the starting point; included angle->Is speed->An included angle with the extraction line;
the parameters of adjacent downstream points are Mach numbers respectivelyPressure->Temperature->Speed->And (c) angle->Angle->Is speed->An included angle with the extraction line; get the specific heat ratio->Directly obtaining the speed by PIV measurement technique>Make the included angleAnd (2) after that:
when the downstream point is in the compression section, the inclined shock wave formula and the included angle are usedAnd Mach number->Calculating to obtain the shock wave angleThe method comprises the steps of carrying out a first treatment on the surface of the According to the shock angle->Further calculating the pressure of the downstream point in the compression section from the parameters of the upstream known point>Temperature (temperature)And Mach number->。
8. The optical measurement method of near-field acoustic explosion signals based on velocity fields according to claim 7, wherein: when the downstream point is in the expansion zone, according toExpansion wave relation, included angle->And Mach number->Calculating Mach numberThe method comprises the steps of carrying out a first treatment on the surface of the At Mach number->Based on isentropic relationship, further calculating to obtain pressure +.>And temperature->。
9. The optical measurement method of near-field acoustic explosion signals based on velocity fields according to claim 8, wherein: at the point of obtaining the pressure at the downstream pointTemperature->And Mach number->Then, taking the downstream point as a new upstream point, and taking the next adjacent point on the extraction line as a new downstream point so as to realize the forward flow point-by-point calculation process; and continuously calculating the parameter value of the new downstream point by using the known parameter value obtained by calculating the new upstream point to obtain the pressure distribution on the extraction line, and integrating to obtain the spatial pressure distribution of the corresponding flow field.
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| CN117760681A (en) * | 2024-02-22 | 2024-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | combined type acoustic explosion test device and method suitable for large supersonic wind tunnel |
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