CN116465595A - Balance temperature measurement method in hypersonic wind tunnel test process - Google Patents
Balance temperature measurement method in hypersonic wind tunnel test process Download PDFInfo
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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
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- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
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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
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Abstract
The invention belongs to the technical field of hypersonic wind tunnel tests, and discloses a balance temperature measurement method in a hypersonic wind tunnel test process, which comprises the following steps: selecting the position of a measuring point; welding a thermocouple; sticking a strain gauge; static calibration of the balance; and (5) collecting test data and analyzing and processing the data. The method for measuring the balance temperature in the hypersonic wind tunnel test process is simple, quick in response, easy to implement and accurate in result. The thermocouple used is small in structure, safe and reliable, does not need to change the balance structure, can be installed in the gap between the balance and the water cooling jacket or the heat insulation jacket, can accurately acquire the temperature of the measuring point position under the condition that the balance force measurement data and the structural strength are not influenced, can be used for measuring the temperature of the sky in the hypersonic wind tunnel test process, can be popularized and applied to low-temperature wind tunnel balance temperature measurement, and can be used for measuring the temperature of other structural members with high response speed requirements and narrow internal space, and has engineering practicability.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a balance temperature measurement method in a hypersonic wind tunnel test process.
Background
The hypersonic wind tunnel is an important platform for developing hypersonic aerodynamics research and is also an important ground test device essential in the development process of hypersonic aircrafts. Because the aircraft has the complex aerodynamic problems of mutual coupling of a real gas effect, a viscous interference effect and a thin gas effect in hypersonic flight, the accuracy of the numerical simulation method is relatively limited, and the accurate acquisition of the aerodynamic characteristic parameters of the hypersonic aircraft still needs to depend on various wind tunnel tests within a foreseeable period.
In hypersonic wind tunnel test, the air flow speed is extremely high, in order to avoid condensation phenomenon, main air flow needs to be heated during test, after heating, the total temperature of a hypersonic wind tunnel front chamber can be up to more than 1100K, and a force measuring balance is used as a multi-component force and moment compound sensor with a complex structure, so that the measuring precision is extremely easy to be influenced by the surrounding environment. In hypersonic wind tunnel test, the temperature effect of the balance mainly comes from temperature gradient generated by high-temperature heating and uneven heating, and the elastic modulus of the structure, the resistance value of the strain gauge and the resistance value of the circuit can change after the balance is heated, so that temperature distribution of positions of different elements in hypersonic wind tunnel test must be considered in balance calibration in order to obtain accurate measurement results. However, because of various heat transfer modes such as heat conduction, convection and radiation exist among the balance, the model and the supporting system in the hypersonic wind tunnel test, and the connection relationship between the balance and the model is relatively complex, only an approximate temperature distribution rule can be obtained through numerical simulation, an accurate temperature value cannot be obtained, and only hypersonic wind tunnel test can be performed in order to accurately obtain temperature distribution and change conditions of different parts of the balance in the hypersonic wind tunnel test process.
In hypersonic wind tunnel test, the hypersonic wind tunnel test is characterized in that the hypersonic wind tunnel test is horizontally arranged in the inner cavity of the model, and in order to reduce the influence of temperature change generated by the change of the attack angle of the model on the measurement value of the balance, a water cooling jacket or a heat insulation jacket is arranged outside the balance, and the space inside the water cooling jacket or the heat insulation jacket is very limited. In this case, only a micro temperature measuring device can be used in order to achieve the balance internal temperature measurement. Currently, the commonly used miniature temperature measuring devices are mainly miniature film type temperature sensors and probe type temperature sensors. The film type temperature sensor (such as PT100 temperature sensor) has small structural size, and is fixed on the surface of the balance in an adhesive manner when in use without damaging the balance structure, however, the thermal conductivity of the adhesive is poor, the temperature response time is overlong, the measurement error is large, and the requirement of hypersonic wind tunnel test measurement cannot be met; when the probe type temperature sensor is installed, holes are required to be drilled on the surface of the balance, the installation process is relatively complex, stress concentration can be generated after the balance structure is stressed, and the structural strength of the balance is reduced.
In order to accurately acquire the balance temperature distribution and change conditions in the inner cavity of the model in a complex thermal environment during hypersonic wind tunnel test, development of a balance temperature measurement method during hypersonic wind tunnel test is needed.
Disclosure of Invention
The invention aims to provide a method for measuring the balance temperature in a hypersonic wind tunnel test process, which is used for overcoming the defects in the prior art.
The invention discloses a method for measuring the balance temperature in a hypersonic wind tunnel test process, which comprises the following steps:
a. selecting the position of a measuring point;
b. welding a thermocouple;
c. sticking a strain gauge;
d. static calibration of the balance;
e. collecting test data;
f. and (5) data analysis and processing.
Further, the specific content of the selection of the measuring point position of the a is as follows:
the measuring point positions cover the balance strain gauge pasting area from front to back, and each measuring point position is close to the corresponding balance strain gauge.
Further, the specific contents of the thermocouple welding of the b are as follows:
and welding a thermocouple wire of the thermocouple at a measuring point by adopting a precise laser spot welder, confirming that the welding spot is qualified by a microscope, leading a wire of the thermocouple out of the rear end of the balance through a balance wiring groove and a threading hole, and leading out a hypersonic wind tunnel body through a balance strut central hole.
Further, the specific contents of the strain gauge sticking of c are as follows:
after the balance is cooled, a balance strain gauge is stuck to form a measuring bridge, so that adverse effects on the balance strain gauge caused by high temperature generated during the operation of the precise laser spot welding machine are avoided.
Further, the specific content of the static calibration of the d balance is as follows:
the balance static calibration comprises thermocouple calibration and balance strain gauge force measurement result calibration; the thermocouple calibration is carried out in an incubator, wherein balance temperature compensation is required; and calibrating the force measurement result of the balance strain gauge on a balance calibration frame, and loading the calibration frame to obtain an elastic angle formula of the balance.
Further, the specific content of the test data acquisition of e is as follows:
carrying out hypersonic wind tunnel test, wherein in the test process, temperature data obtained by thermocouple measurement are collected through a thermocouple data collection system, and balance force measurement test data are collected through the hypersonic wind tunnel data collection system;
because the system time and the acquisition frequency of the thermocouple data acquisition system and the hypersonic wind tunnel data acquisition system are different, after the hypersonic wind tunnel is started, a high pulse level signal is simultaneously transmitted to the thermocouple data acquisition system and the hypersonic wind tunnel data acquisition system through a special signal generator after a flow field is established, a model attack angle is in place, a test is ended and related characteristic moments are carried out, and the thermocouple data acquisition system and the hypersonic wind tunnel data acquisition system are controlled to synchronously acquire.
Further, the specific contents of the data analysis processing of f are as follows:
the data analysis processing comprises temperature data processing and force measurement data processing;
the temperature data processing process comprises data filtering, data removing and temperature calculating; the data filtering adopts a low-pass filter to eliminate high-frequency interference signals; the data rejection is used for rejecting abnormal data generated by welding spot falling and related reasons; calculating the temperature corresponding to the measuring point through the thermoelectric voltage output value of the thermocouple;
the force measurement data processing is carried out according to hypersonic wind tunnel data processing specifications.
The method for measuring the balance temperature in the hypersonic wind tunnel test process has the following advantages:
(1) The installation is simple, and the balance structure is not required to be changed;
(2) The response is rapid, and the temperature change of the measuring point position can be quickly followed;
(3) The structure is small and exquisite, can install in the interval between balance and water-cooled jacket or the heat-insulating sleeve;
(4) The balance temperature measuring device is safe and reliable, can measure the balance temperature while measuring the force, and can not influence the force measuring data and the structural strength of the balance.
The method for measuring the balance temperature in the hypersonic wind tunnel test process is simple, quick in response, easy to implement and accurate in result. The thermocouple used is small in structure, safe and reliable, does not need to change the balance structure, can be installed in the gap between the balance and the water cooling jacket or the heat insulation jacket, can accurately acquire the temperature of the measuring point position under the condition that the balance force measurement data and the structural strength are not influenced, can be used for measuring the temperature of the sky in the hypersonic wind tunnel test process, can be popularized and applied to low-temperature wind tunnel balance temperature measurement, and can be used for measuring the temperature of other structural members with high response speed requirements and narrow internal space, and has engineering practicability.
Drawings
FIG. 1 is a workflow diagram of a method for measuring balance temperature in a hypersonic wind tunnel test process according to the present invention;
FIG. 2a is a six-component bar balance used in the hypersonic wind tunnel test procedure balance temperature measurement method of example 1;
FIG. 2b is a plot of the thermocouple station position on a six-component bar balance in the hypersonic wind tunnel test procedure balance temperature measurement method of example 1;
FIG. 3 is a comparison (Mach number 5) of the temperature measurement results of the test whole-process thermocouple obtained by the hypersonic wind tunnel test process balance temperature measurement method of example 1 and the PT100 sensor;
FIG. 4 is a comparison (Mach number 8) of the temperature measurement results of the test whole-process thermocouple and the PT100 sensor obtained by the hypersonic wind tunnel test process balance temperature measurement method of example 1;
FIG. 5 is a comparison of the temperature measurement results of the test whole-process thermocouple obtained by the hypersonic wind tunnel test process balance temperature measurement method of example 1 with the PT100 sensor (Mach number 5, angle of attack 10 °);
fig. 6 is a comparison of the temperature measurement results (mach number 8, angle of attack 10 °) of the experimental whole-process thermocouple obtained by the hypersonic wind tunnel experimental process balance temperature measurement method of example 1 and the PT100 sensor.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Example 1:
the following examples are illustrative of the invention and are not intended to limit the scope of the invention.
The balance in the embodiment is a six-component bar balance of the hypersonic wind tunnel shown in fig. 2a, and is used for measuring the temperature distribution and the change condition of the six-component bar balance structure in the hypersonic wind tunnel test process, and the six-component bar balance is divided into 11 sections a-K along the axial direction, wherein the sectional view of each section is shown in fig. 2b. Wherein M1, M5 electric bridge is arranged in B-B and D-D cross section, M2, M6 electric bridge is arranged in I-I and J-J cross section, X element electric bridge is arranged in F-F, G-G cross section, and Mx element electric bridge is arranged in B-B cross section.
A flow chart of a balance temperature measurement method in the hypersonic wind tunnel test process in the embodiment is shown in fig. 1.
a. Selecting the position of a measuring point;
in order to obtain the temperature distribution of the six-component rod balance strain gauge mounting area, 20 temperature measuring points shown in figure 2b are determined at 11 sections of a-K, wherein a measuring point 1# and a measuring point 2# which are positioned at the section of A-A are positioned at the front part of the strain gauge, a measuring point 19# and a measuring point 20# which are positioned at the section of K are positioned at the rear part of the strain gauge, and the positions of the rest measuring points are positioned near a bridge formed by the strain gauge;
b. welding a thermocouple;
the thermocouple wires of the thermocouples are welded at the measuring point positions by adopting a precise laser spot welder, the K-type thermocouple with the wire core made of nichrome/nickel-silicon alloy is selected, the temperature measuring range is-200-260 ℃, and the six-component rod balance temperature measuring requirement of a model inner cavity below the Mach number 8 (comprising Mach number 8) of the hypersonic wind tunnel can be met. Confirming that welding points are qualified through a microscope, enabling a wire of a thermocouple to pass through a balance wiring groove and a threading hole, leading out from the rear end of a balance, and leading out a hypersonic wind tunnel body through a balance strut central hole;
c. sticking a strain gauge;
after the six-component rod type balance is cooled, a balance strain gauge is stuck to form a measuring bridge, so that adverse effects on the balance strain gauge caused by high temperature generated during the operation of the precise laser spot welder are avoided;
d. static calibration of the balance;
the balance static calibration comprises thermocouple calibration and balance strain gauge force measurement result calibration; the thermocouple calibration is carried out in an incubator, wherein balance temperature compensation is required; calibrating the force measurement result of the balance strain gauge on a balance calibration frame, and loading the calibration frame to obtain an elastic angle formula of the balance;
e. collecting test data;
carrying out hypersonic wind tunnel test, wherein in the test process, temperature data measured by a thermocouple are acquired by a DEWESoft SIRIUS data acquisition system, and the sampling frequency is 100Hz; the six-component rod balance force measurement test data are collected through a hypersonic wind tunnel data collection system;
the hypersonic wind tunnel test adopts a fixed attack angle test mode, namely, the model attack angle is stable and motionless in a wind tunnel flow field after being in place, and continuously acquires temperature and aerodynamic force during the period to acquire the change condition of the temperature and aerodynamic force of a six-component rod balance in the continuous heating process;
f. analyzing and processing data;
the data analysis processing comprises temperature data processing and force measurement data processing;
the temperature data processing process comprises data filtering, data removing and temperature calculating; the data filtering adopts a low-pass filter to eliminate high-frequency interference signals; the data rejection is used for rejecting abnormal data generated by welding spot falling and related reasons; calculating the temperature corresponding to the measuring point through the thermoelectric voltage output value of the thermocouple;
the force measurement data processing is carried out according to hypersonic wind tunnel data processing specifications.
Since the results of the measurement of the thermocouples in the same section in the hypersonic wind tunnel test are not quite different, the average value of the measurement of the thermocouples in the same time can be used for representing the section temperature at the time, for example, for the section C-C, the method is usedT f The temperature at any time of the section is represented by:
；
wherein, the liquid crystal display device comprises a liquid crystal display device,T i for the next timeiThe temperature values obtained by measuring the measuring points.
For the 17# and 18# measuring points at the tail of the strut, the temperature measurement values are basically consistent during the test, thus the same asThe sample adopts the mean valueT r The temperatures of the I-I section to J-J section area are described as follows:
。
in order to compare the difference between the measurement results of the thermocouple and the PT100 temperature sensor, a temperature sensor with the number PT100-1 is stuck to the C-C section in the hypersonic wind tunnel test, and a temperature sensor with the number PT100-2 is stuck between the I-I section and the J-J section.
Fig. 3 and fig. 4 show the time-dependent temperature curves of the six-component lever balance measured by the thermocouple and the PT100 temperature sensor during the hypersonic wind tunnel test at mach 5 and mach 8, respectively. In fig. 3 and 4, the abscissa t is time in S; the ordinate T is temperature in degrees Celsius. The four dashed lines parallel to the longitudinal axis and marked as I, II, III, IV correspond to the four characteristic moments of "flow field establishment", "model 0 ° attack angle in place", "model 10 ° attack angle in place" and "end of test", respectively. As can be seen from fig. 3 and fig. 4, the temperature curve measured by the thermocouple has a significant difference from the measured value of PT100, compared with the thermocouple, the PT100 temperature sensor cannot obtain the balance temperature peak value in the hypersonic wind tunnel test due to longer response time, the measured value of the temperature is lower than the measured value of the thermocouple before the flow field is established, the measured value of the temperature is higher than the measured value of the thermocouple after the attack angle of the model is in place, and the temperature change is not great in the whole hypersonic wind tunnel test process. In comparison, the thermocouple has higher accuracy of measurement results.
Fig. 5 and 6 are graphs comparing the results of the thermocouple and the PT100 temperature sensor after the model 10 ° attack angle is in place and before the test is finished, at mach 5 and mach 8. In fig. 5 and 6, the abscissa t is time in S; the ordinate T is temperature in degrees Celsius. As can be seen from FIGS. 5 and 6, during Mach number 5 test, the front and rear thermocouples of the six-component bar balance measureT f And (3) withT r Essentially the same, the thermocouple gradually decreased from 23.0 ℃ to about 19.5 ℃ throughout the test, whereas the PT100 sensorThe measured value does not change much. At Mach 8, thermocouple measurement is performed after the model attack angle is in placeT f Compared withT r About 3 ℃ higher, as the test proceeds,T f and (3) withT r The measured value and the temperature difference between the measured value and the measured value show a decreasing trend, and when the test is finished,T f compared withT r The temperature is about 1.8 ℃. Compared with the prior art, the PT100 has the advantages that due to hysteresis, the measured value of the same position at the same moment is higher than the measured value of the thermocouple, the measured value of the PT100-1 of the C-C section gradually increases, and the measured value of the PT100-2 of the tail part of the six-component rod balance does not change greatly.
Although the embodiments of the present invention have been disclosed above, it is not limited to the use listed in the specification and the embodiments, but it can be fully applied to various fields suitable for the present invention. Additional modifications and variations may readily be made by those skilled in the art without departing from the principles of the present invention, and the invention is not limited to the specific details and illustrations shown and described herein.
Claims (7)
1. The method for measuring the balance temperature in the hypersonic wind tunnel test process is characterized by comprising the following steps of:
a. selecting the position of a measuring point;
b. welding a thermocouple;
c. sticking a strain gauge;
d. static calibration of the balance;
e. collecting test data;
f. and (5) data analysis and processing.
2. The hypersonic wind tunnel test process balance temperature measurement method according to claim 1 is characterized in that the specific content of the measurement point position selection of the a is as follows:
the measuring point positions cover the balance strain gauge pasting area from front to back, and each measuring point position is close to the corresponding balance strain gauge.
3. The hypersonic wind tunnel test process balance temperature measurement method according to claim 1, wherein the specific contents of the thermocouple welding of b are as follows:
and welding a thermocouple wire of the thermocouple at a measuring point by adopting a precise laser spot welder, confirming that the welding spot is qualified by a microscope, leading a wire of the thermocouple out of the rear end of the balance through a balance wiring groove and a threading hole, and leading out a hypersonic wind tunnel body through a balance strut central hole.
4. The method for measuring the balance temperature in the hypersonic wind tunnel test process according to claim 1, wherein the specific contents of the strain gauge sticking of c are as follows:
and after the balance is cooled, pasting a balance strain gauge to form a measuring bridge.
5. The hypersonic wind tunnel test process balance temperature measurement method according to claim 1, wherein the specific contents of the static calibration of the d balance are as follows:
the balance static calibration comprises thermocouple calibration and balance strain gauge force measurement result calibration; the thermocouple calibration is carried out in an incubator, wherein balance temperature compensation is required; and calibrating the force measurement result of the balance strain gauge on a balance calibration frame, and loading the calibration frame to obtain an elastic angle formula of the balance.
6. The hypersonic wind tunnel test process balance temperature measurement method according to claim 1, wherein the specific content of test data acquisition of e is as follows:
carrying out hypersonic wind tunnel test, wherein in the test process, temperature data obtained by thermocouple measurement are collected through a thermocouple data collection system, and balance force measurement test data are collected through the hypersonic wind tunnel data collection system;
because the system time and the acquisition frequency of the thermocouple data acquisition system and the hypersonic wind tunnel data acquisition system are different, after the hypersonic wind tunnel is started, a high pulse level signal is simultaneously transmitted to the thermocouple data acquisition system and the hypersonic wind tunnel data acquisition system through a special signal generator after a flow field is established, a model attack angle is in place, a test is ended and related characteristic moments are carried out, and the thermocouple data acquisition system and the hypersonic wind tunnel data acquisition system are controlled to synchronously acquire.
7. The hypersonic wind tunnel test process balance temperature measurement method according to claim 1, wherein the specific contents of the data analysis processing of f are as follows:
the data analysis processing comprises temperature data processing and force measurement data processing;
the temperature data processing process comprises data filtering, data removing and temperature calculating; the data filtering adopts a low-pass filter to eliminate high-frequency interference signals; the data rejection is used for rejecting abnormal data generated by welding spot falling and related reasons; calculating the temperature corresponding to the measuring point through the thermoelectric voltage output value of the thermocouple;
the force measurement data processing is carried out according to hypersonic wind tunnel data processing specifications.
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| CN117245196A (en) * | 2023-11-16 | 2023-12-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Strain balance electron beam welding structure and welding method thereof |
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