CN117168758A - Application method of hypersonic flight test parameter test system - Google Patents
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Abstract
The invention discloses an application method of a hypersonic flight test parameter test system, which relates to the technical field of hypersonic flight tests, and is characterized in that a signal test device is designed on the surface or the inner wall of a model to measure the physical quantities such as the temperature, the pressure, the heat flow and the like of the air flow on the surface of the model in the flight test process; and the debugging work of the parameter testing system at each stage of hypersonic flight test is completed by matching with the signal converter, the signal conversion and acquisition integrated machine, the high-frequency signal acquisition and editing machine, the cable network and the ground data testing table, and the testing data is analyzed. The invention provides an application method of a hypersonic flight test parameter testing system, which is used for meeting the test requirements of various aerodynamic parameters of hypersonic flight tests and can adapt to the requirements of severe flight test environments such as hypersonic high temperature, high pressure and the like.
Description
Technical Field
The invention relates to the field of hypersonic flight tests. More particularly, the invention relates to a hypersonic flight test parameter testing system application method.
Background
The hypersonic flight test technology is characterized in that real flight test data are provided for researching basic aerodynamic problems such as boundary layer transition control, local shock wave interference flow mechanism, high enthalpy thermal boundary layer heat mass transfer characteristics and the like by measuring aerodynamic parameters such as surface temperature, pressure, heat flow, acceleration and the like of a model in the hypersonic flight test process, and verification data are provided for theoretical and numerical calculation results. The hypersonic flight test technology is a common foundation for supporting the research of various hypersonic aerodynamic physical effects, and is also a basic reference for the design and analysis of various hypersonic aircrafts.
In hypersonic flight test, the pneumatic parameters to be measured are various, so that in the process of acquiring the pneumatic parameter signals, an independent acquisition system is generally adopted for different signals, and when the required sensors and the corresponding conversion acquisition equipment have different requirements, no complete signal acquisition, conversion, coding and analysis system can be applied to meet the requirements of testing and debugging various pneumatic parameters of hypersonic flight test.
In addition, the conventional test system generally adopts a general standard power supply to supply power to the sensor and the stand-alone machine, and the receiving equipment such as a universal meter, an oscilloscope and the like can be adopted to receive the physical electric signals of the sensor. When the test is carried out, the power supply equipment and the signal receiving equipment are respectively connected to different sensors and single machines, so that the test system is messy, and the test is more complicated by connecting cables with various functions.
In addition, the conventional test parameter testing system only tests the performance of the sensor (it should be noted that, the "conventional test parameter testing system" described herein generally refers to that after the sensor is in stock, the resistance of the sensor is measured by a multimeter, or the sensor is powered up by an external power source to measure the feedback voltage signal of the sensor, so that such test for acceptance is not performed with a test structure), and the test is not performed together with the sensor test structure. In the actual use process, the sensor test structure can influence the performance of the sensor.
Disclosure of Invention
It is an object of the present invention to address at least the above problems and/or disadvantages and to provide at least the advantages described below.
To achieve these objects and other advantages and in accordance with the purpose of the invention, a hypersonic flight test parameter testing system application method is provided, comprising:
s1, a signal testing device acquires parameter signals on the surface of a flight test process model and converts the parameter signals into corresponding electric signals, wherein the electric signals comprise high-frequency weak electric signals and non-high-frequency weak electric signals;
s2, the signal converter and the signal conversion and acquisition integrated machine respectively condition and amplify the received high-frequency weak current signals and the non-high-frequency weak current signals;
s3, the conversion and acquisition integrated machine and the high-frequency signal acquisition and editing device perform AD sampling and encoding on the conditioned and amplified electric signals, package the data through a cable network and transmit the packaged data to the data recorder and the ground data test board through the high-frequency signal acquisition and editing device;
and S4, the test software in the ground data test table reads all the test data stored in the data recorder, and analyzes and processes the test data to complete the debugging work of the parameter test system at each stage of hypersonic flight test.
Preferably, in S1, the parameter signals include a temperature signal and a pressure signal;
in S4, the analysis process of the test software on all the test data includes:
the test software reads the sensor data packet file stored in the data recorder and determines whether the data in the sensor data packet file is temperature sensor data according to the initial of the name of the sensor data packet file.
Preferably, in S4, if it is determined that the data in the sensor data packet file is temperature sensor data, the processing procedure of the test software on the temperature sensor data is:
s410, calculating a sensor output voltage value based on the coding layering value in the sensor data packet file and the transformation coefficient calibrated by the transformation equipment by the following formula:
in the method, in the process of the invention,M i the coding hierarchy values given for the data packets,Ufor the output voltage of the sensor,V ref for the full-scale output voltage of the converter,A、Bslope coefficient and intercept coefficient of linear transformation equation calibrated for transformation equipment, sigma is sensor signal resolution;
s411, based on the sensor output voltage value obtained in the S410, finding out the upper and lower voltage limit graduation values and corresponding temperature values corresponding to the sensor output voltage in the thermocouple graduation table corresponding to the sensor type through a selection algorithm;
s412, based onS410, obtaining upper and lower limit values of voltage and temperature, and calculating a sensor temperature value by a linear interpolation methodW；
S413, calculating the sensor temperature value according to the sensor cold end temperature value pair in the converterWlbPerforming temperature compensation to obtain a real temperature value of the measuring pointWqc；
Wherein the cold end temperatureWlbObtained by the following formula:
Wlb=Klb×Mlb+Blb
in the above-mentioned method, the step of,Wlbfor the temperature value of the cold end of the sensor,Mlbthe layered values are encoded for the cold side compensation channels,Klb、Blbslope coefficient and intercept coefficient of cold end linear transformation equation calibrated for transformation equipment;
the real temperature value of the measuring pointWqcObtained by the following formula:
Wqc=W×Wlb。
preferably, in S4, if it is determined that the data in the sensor data packet file is not temperature sensor data, the processing procedure of the test software on the non-temperature sensor data is as follows:
s420, calculating the output voltage value of the sensor based on the coding layering value in the sensor data packet file by the following formulaU o ：
In the above-mentioned method, the step of,M i the coding hierarchy values given for the data packets,V ref for full scale output of the transducer, σ is the sensor signal resolution;
s421, output voltage valueU o The calibration coefficient of the signal converter and the measuring range of the pressure sensor, the pressure value of the measuring point is obtained through the following stepsP：
P=P o ×(X×P o +Y)
In the above-mentioned method, the step of,P 0 as the range of the pressure sensor,X、Yfor signal convertersAnd (5) determining coefficients.
Preferably, the hypersonic flight test parameter testing system is matched with the application method, and is configured to comprise:
the signal testing device is used for acquiring a flight test process model surface parameter signal;
the signal converter and the signal conversion acquisition all-in-one machine are in communication connection with the signal testing device to classify and process the high-frequency weak current signals and the non-high-frequency weak current signals;
the high-frequency signal collecting and editing device is in communication connection with the signal converter and the signal conversion and collection integrated machine;
the data recorder is in communication connection with the high-frequency signal coder and the ground data test board;
wherein, each device realizes communication connection through a cable network.
Preferably, the signal testing device includes: a sensor and a test mechanism matched with the sensor.
Preferably, the high-frequency signal coder is provided with three acquisition modules with upper sampling frequency limits of 30kHz, 200kHz and 1MHz respectively.
Preferably, the sampling frequency of the signal conversion and acquisition integrated machine is 100Hz, and 120 paths of sensor signal sampling channels are provided.
The invention at least comprises the following beneficial effects: the invention establishes a complete signal acquisition, transformation, coding and analysis system, which is used for meeting the test and debugging requirements of various aerodynamic parameters of hypersonic flight test.
Meanwhile, the parameter test system of the invention can supply power to the sensor and each single machine equipment through the ground data test table, and can realize the acquisition and conversion of various parameter signals and the signal transmission among the equipment through the ground data test table and various type connectors carried by the cable network, so that the test work is simpler and more efficient
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
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FIG. 1 is a schematic flow chart of the parameter testing system of the present invention when data analysis and processing are performed;
fig. 2 is a schematic diagram of a hypersonic flight test parameter testing system according to the present invention.
Detailed Description
The present invention is described in further detail below with reference to the drawings to enable those skilled in the art to practice the invention by referring to the description.
The hypersonic flight test parameter testing system can meet the test requirements of various pneumatic parameters of hypersonic flight tests, and can adapt to the requirements of severe flight test environments such as hypersonic high temperature, hypersonic high pressure and the like. Meanwhile, when the system is used for carrying out ground and on-bullet tests, equipment connection can be rapidly completed, performance tests can be carried out on various types of sensors and single-machine equipment required by flight tests, and analysis can be carried out on test data in real time.
The hypersonic flight test parameter test system is used for testing a signal test device when the hypersonic flight test parameter test system is actually applied, namely, a sensor and a corresponding test mechanism are used as a whole to be tested, and the sensor performance verification tests such as a temperature cycle, random vibration, transportation condition vibration, low/high frequency impact, acceleration, low air pressure, low temperature and the like, a pressure sensor frequency response test, a temperature sensor thermal vibration test and a sensor test mechanism thermal protection test are carried out by carrying out sensor environment tests, so that the technical indexes which can be achieved by the signal test device under various assessment tests are comprehensively tested, and the condition that the overall performance indexes of the signal test device meet the use requirements of the flight test is obtained. The system can supply power to the sensor and the single machine equipment through the socket and the corresponding cable of the ground data test board, and can realize collection, transformation and analysis of various parameter signals of the sensor and the single machine, so that the test work is simpler, more convenient and more efficient.
Specifically, as shown in fig. 2, a hypersonic flight test parameter testing system of the present invention includes:
the signal testing device 1 is arranged on the surface or the inner wall of a model and consists of a sensor and a corresponding testing mechanism, wherein the sensor is used for sensing physical quantities such as air flow temperature, pressure and the like on the surface of the model in the flight test process and converting the physical quantities into usable electric signals such as voltage, current and the like, the usable electric signals are output through a cable, the testing mechanism is used for guaranteeing that the strength and the heat resistance of the device meet the requirements of the space flight test environment, the testing mechanism currently has 5 structures, 2 types of temperature measurement and 3 types of pressure measurement, one type of temperature measurement is realized by adopting a nonmetallic inner wall to install a temperature sensor, and an integral measurement mode is realized during the test, one type of temperature measurement is mainly realized by directly welding a temperature sensor testing end on a thin-wall testing structure in a spot welding mode, the inner wall temperature sensor is realized in a spring compression and thread positioning mode, and the sensor and the testing structure are connected through threads and then realized in a glue adding fixing mode.
The signal converter 2 is arranged at the rear end of the sensor and is used for conditioning and amplifying the electric signals input by the high-frequency sensor.
The high-frequency signal coder 3 is arranged at the rear end of the signal converter and is used for converting continuous high-frequency electric signals and encoding after AD sampling, and packaging non-high-frequency signals sent by the conversion and acquisition integrated machine 4 and sending the non-high-frequency signals to the data recorder. The high-frequency signal collecting and editing device is provided with three collecting modules with the upper limit of sampling frequency of 30kHz, 200kHz and 1MHz respectively, and can collect high-frequency electric signals of the sensor according to the signal frequency collecting requirement. Each acquisition module is provided with an independent controller (FPGA), frames the acquisition data of the current module, and the data after framing is sent to the main control module under the control of the main control module main controller (FPGA).
The signal conversion and acquisition integrated machine 4 is arranged at the rear end of the sensor, conditioning, amplifying and converting the non-high frequency electric signal input by the sensor, encoding after AD sampling, and packaging and transmitting the data to the high frequency signal coder 3 through a cable network. The main functions of the signal conversion module in each module of the equipment are to convert the input electric parameters, amplify the signals, filter the signals, modulate and demodulate the signals and the like. The module can convert various electrical parameter input signals such as resistance, inductance, capacitance, frequency and the like into voltage signals. The main function of the acquisition module is to convert the converted continuous analog signals into discrete digital signals, and code and send the discrete digital signals to the high-frequency signal acquisition and editing device, when the signal conversion and acquisition integrated machine is practically applied, the design sampling frequency is 100Hz, 120 paths of sensor signals can be sampled at the same time, the signal conversion and acquisition integrated machine adopts a unit type hardware structure, and each sensor signal conversion unit can flexibly assemble according to task requirements and different modules according to the types and the quantity of measured parameters.
And the data recorder 5 is used for receiving and storing all data signals sent by the high-frequency signal coder.
And the ground data test board 6 is used for completing the single machine function test of the signal conversion and acquisition integrated machine, the high-speed gatherer and the data recorder and monitoring the working state of the equipment. Meanwhile, the system has the functions of displaying data in real time and reading data of a data recorder, and can analyze the data to finish the debugging work of a parameter testing system at each stage of hypersonic flight test, and in practical application, the ground data testing table processes the acquired data of the temperature sensor, and the data processing method comprises the following steps: and calculating the output voltage value of the sensor according to the coding layering value given by the data packet, checking a thermocouple graduation table according to the output voltage value, performing linear interpolation, and performing cold end temperature compensation on a temperature value obtained after the linear interpolation through the cold end temperature. The measured temperature resolution is 16 bits; in practical applications: the ground data test board processes collected pressure sensor data according to the following steps: and calculating the output voltage value of the sensor according to the coding layering value given by the data packet, and calculating the pressure value according to the output voltage value and the calibration coefficient of the signal converter. The pressure resolution measured was 16 bits.
And a cable network 7 for realizing power supply and signal transmission between the sensors of the system and the stand-alone machine.
Further, the invention discloses an application method of a hypersonic flight test parameter testing system, which comprises the following steps of: firstly, a sensor in a signal testing device 1 obtains physical quantity signals such as air flow temperature, pressure and the like on the surface of a model in a flight test process and converts the physical quantity signals into usable electric signals; then the signal converter 2 arranged at the rear end of the sensor carries out conditioning amplification on the high-frequency weak current signals transmitted by the signal testing device 1, and the signal conversion and acquisition integrated machine 4 carries out conditioning amplification on the rest non-high-frequency weak current signals transmitted by the signal testing device 1; and the signal conversion and acquisition all-in-one machine 4 and the high-frequency signal coder 3 perform AD sampling and coding on the conditioned and amplified electric signals, the high-frequency signal coder 3 packages all electric signal data through a cable network 7 and then transmits the packaged electric signal data to the data recorder 5, and the data recorder 5 receives and stores all data signals sent by the signal conversion and acquisition all-in-one machine 4 and the high-frequency signal coder 3.
The ground data test board 6 can call and read all the test data stored in the data recorder 5, analyze the test data and finally finish the debugging work of the parameter test system at each stage of hypersonic flight test. The power supply and the signal transmission of each sensor and the single machine of the system are realized through a cable network 7.
The system can receive batch non-high frequency signals through the signal conversion and acquisition integrated machine 4, and can acquire 120 paths of non-high frequency signals at the same time. When there is a high frequency signal test requirement, it can be realized by the high frequency signal gatherer 3. The mode is that the signal converter 2 amplifies the high-frequency electric signal, and the high-frequency signal coder 3 regulates and codes the amplified signal.
The system can supply power to the sensor and each single machine device through the ground data test board 6, and meanwhile, various parameter signals can be acquired and converted and signal transmission among the devices can be realized through various type interfaces carried by the ground data test board 6 and the cable network 7, so that the test work is simpler, more convenient and more efficient.
In specific implementation, in the parameter testing system provided by the invention, as shown in fig. 2, the processing of temperature and pressure data can be realized by the following algorithm:
step A: and reading the sensor data packet file stored in the data recorder by the ground data test board, and determining whether the data in the sensor data packet file is temperature sensor data according to the initial of the name of the sensor data packet file.
If yes, executing the step B, and if not, executing the step F;
and (B) step (B): when step A, yes, this step is performed. Calculating the output voltage of the sensor by using the method 1 according to the coding layering value in the data packet file and the transformation coefficient A, B calibrated by the transformation equipment;
wherein:M i coding layering values given for the data packets;Uoutputting a voltage for the sensor;V ref for a full scale output of the converter, typically 5000mV;A、Bslope coefficient and intercept coefficient of linear transformation equation for calibrating transformation equipmentA、BBefore leaving the factory, calibrating each channel of each conversion device by a manufacturer; σ is the sensor signal resolution and its value is 65536.
Step C: based on the sensor output voltage value obtained in the step S410, finding out the upper and lower voltage limit graduation values and corresponding temperature values corresponding to the sensor output voltage in a thermocouple graduation table (the thermocouple graduation table is a national standard) of the corresponding sensor type through a selection algorithm;
step D: calculating a sensor temperature value by a linear interpolation method according to the upper limit value and the lower limit value of the voltage and the temperature;
step E: and carrying out temperature compensation on the calculated sensor temperature value according to the sensor cold end temperature value in the converter to obtain a measuring point real temperature value. And obtaining a cold end temperature by using the formula 2, and obtaining a measuring point real temperature value by using the formula 3.
Wlb=Klb×Mlb+Blb
Wherein:Wlbthe temperature value of the cold end of the sensor;Mlbcoding a layering value for the cold-end compensation channel;Klb、Blbslope coefficients and intercept coefficients of a cold-end linear transformation equation calibrated for a transformation device.
Wqc=W×Wlb
Wherein:Wqcthe real temperature value of the measuring point is;Wcalculate for step DThe obtained temperature value;Wlbis the temperature value of the cold end of the sensor.
Step F: when step A, yes, this step is performed. Calculating a sensor output voltage value by using a sensor data coding layering value given by a data packet according to the sensor output voltage value given by the data packet;
wherein:M i coding layering values given for the data packets;U o outputting a voltage value for the sensor;V ref for a full scale output of the converter, typically 5000mV; σ is the sensor signal resolution and its value is 65536.
Step G: calculating to obtain a measuring point pressure value by using a 5 according to the output voltage value of the sensor, the calibration coefficient of the signal converter 2 and the measuring range of the pressure sensor in the last step;
P=P o ×(X×P o +Y)
wherein:Pthe pressure value is the measured point pressure value;P 0 is the pressure sensor range, typically 170kPa;U o outputting a voltage value for the sensor;X、Ythe coefficients are calibrated for the signal converter.
The above is merely illustrative of a preferred embodiment, but is not limited thereto. In practicing the present invention, appropriate substitutions and/or modifications may be made according to the needs of the user.
The number of equipment and the scale of processing described herein are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be readily apparent to those skilled in the art.
Although embodiments of the invention have been disclosed above, they are not limited to the use listed in the specification and embodiments. It can be applied to various fields suitable for the present invention. Additional modifications will readily occur to those skilled in the art. Therefore, the invention is not to be limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
Claims (8)
1. The application method of the hypersonic flight test parameter testing system is characterized by comprising the following steps of:
s1, a signal testing device acquires parameter signals on the surface of a flight test process model and converts the parameter signals into corresponding electric signals, wherein the electric signals comprise high-frequency weak electric signals and non-high-frequency weak electric signals;
s2, the signal converter and the signal conversion and acquisition integrated machine respectively condition and amplify the received high-frequency weak current signals and the non-high-frequency weak current signals;
s3, the conversion and acquisition integrated machine and the high-frequency signal acquisition and editing device perform AD sampling and encoding on the conditioned and amplified electric signals, package the data through a cable network and transmit the packaged data to the data recorder and the ground data test board through the high-frequency signal acquisition and editing device;
and S4, the test software in the ground data test table reads all the test data stored in the data recorder, and analyzes and processes the test data to complete the debugging work of the parameter test system at each stage of hypersonic flight test.
2. The hypersonic flight test parameter testing system application method as set forth in claim 1, wherein in S1, the parameter signals include a temperature signal and a pressure signal;
in S4, the analysis process of the test software on all the test data includes:
the test software reads the sensor data packet file stored in the data recorder and determines whether the data in the sensor data packet file is temperature sensor data according to the initial of the name of the sensor data packet file.
3. The hypersonic flight test parameter testing system application method as set forth in claim 2, wherein in S4, if it is determined that the data in the sensor data packet file is temperature sensor data, the processing procedure of the test software on the temperature sensor data is:
s410, calculating a sensor output voltage value based on the coding layering value in the sensor data packet file and the transformation coefficient calibrated by the transformation equipment by the following formula:
in the method, in the process of the invention,M i the coding hierarchy values given for the data packets,Ufor the output voltage of the sensor,V ref for the full-scale output voltage of the converter,A、Bslope coefficient and intercept coefficient of linear transformation equation calibrated for transformation equipment, sigma is sensor signal resolution;
s411, based on the sensor output voltage value obtained in the S410, finding out the upper and lower voltage limit graduation values and corresponding temperature values corresponding to the sensor output voltage in the thermocouple graduation table corresponding to the sensor type through a selection algorithm;
s412, calculating the temperature value of the sensor by a linear interpolation method based on the upper and lower limit values of the voltage and the temperature obtained in S410W；
S413, calculating the sensor temperature value according to the sensor cold end temperature value pair in the converterWlbPerforming temperature compensation to obtain a real temperature value of the measuring pointWqc；
Wherein the cold end temperatureWlbObtained by the following formula:
Wlb=Klb×Mlb+Blb
in the above-mentioned method, the step of,Wlbfor the temperature value of the cold end of the sensor,Mlbthe layered values are encoded for the cold side compensation channels,Klb、Blbslope coefficient and intercept coefficient of cold end linear transformation equation calibrated for transformation equipment;
the real temperature value of the measuring pointWqcObtained by the following formula:
Wqc=W×Wlb。
4. the hypersonic flight test parameter testing system application method as set forth in claim 2, wherein in S4, if it is determined that the data in the sensor data packet file is not temperature sensor data, the processing procedure of the testing software on the non-temperature sensor data is:
s420, calculating the output voltage value of the sensor based on the coding layering value in the sensor data packet file by the following formulaU o ：
In the above-mentioned method, the step of,M i the coding hierarchy values given for the data packets,V ref for the full scale output voltage of the converter, σ is the sensor signal resolution;
s421, output voltage valueU o The calibration coefficient of the signal converter and the measuring range of the pressure sensor, the pressure value of the measuring point is obtained through the following stepsP：
P=P o ×(X×P o +Y)
In the above-mentioned method, the step of,P 0 as the range of the pressure sensor,X、Ythe coefficients are calibrated for the signal converter.
5. The hypersonic flight test parameter testing system application method as set forth in claim 1, further comprising a hypersonic flight test parameter testing system in cooperation with the application method, configured to include:
the signal testing device is used for acquiring a flight test process model surface parameter signal;
the signal converter and the signal conversion acquisition all-in-one machine are in communication connection with the signal testing device to classify and process the high-frequency weak current signals and the non-high-frequency weak current signals;
the high-frequency signal collecting and editing device is in communication connection with the signal converter and the signal conversion and collection integrated machine;
the data recorder is in communication connection with the high-frequency signal coder and the ground data test board;
wherein, each device realizes communication connection through a cable network.
6. The hypersonic flight test parameter testing system application method as set forth in claim 5, wherein the signal testing device includes: a sensor and a test structure matched with the sensor.
7. The hypersonic flight test parameter testing system application method as claimed in claim 5, wherein three acquisition modules with the upper limits of sampling frequencies of 30kHz, 200kHz and 1MHz are arranged on the high-frequency signal gatherer.
8. The hypersonic flight test parameter testing system application method of claim 5, wherein the sampling frequency of the signal conversion and acquisition integrated machine is 100Hz, and 120 paths of sensor signal sampling channels are provided.
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4149089A (en) * | 1975-12-05 | 1979-04-10 | The Bendix Corporation | Electro-optical scanner for generating digital flaw data |
| US4708495A (en) * | 1985-04-23 | 1987-11-24 | Noranda Inc. | Metal surface temperature monitor |
| CN205228771U (en) * | 2015-11-13 | 2016-05-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Experimental minute -pressure measurement system in low speed wind tunnel flow field |
| CN206990072U (en) * | 2017-08-08 | 2018-02-09 | 天信仪表集团有限公司 | A kind of flowmeter on-line diagnosing apparatus |
| CN211696724U (en) * | 2019-12-23 | 2020-10-16 | 陕西电器研究所 | Multi-channel temperature signal conversion device |
| CN112326184A (en) * | 2020-11-25 | 2021-02-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Frequency-variable high-precision wind tunnel test data acquisition method |
| CN112326050A (en) * | 2020-11-18 | 2021-02-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | System and method for testing large-area temperature distribution of hypersonic-speed high-temperature wind tunnel |
| CN112649148A (en) * | 2021-01-19 | 2021-04-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-frequency pulsating pressure testing device for hypersonic flight test |
| CN115014696A (en) * | 2022-08-08 | 2022-09-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for synchronous acquisition and integrated processing of wind tunnel multi-signal source data |
| CN115183897A (en) * | 2022-09-09 | 2022-10-14 | 之江实验室 | Temperature measuring system and method based on high-frequency alternating current signals |
| CN115508040A (en) * | 2022-11-17 | 2022-12-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Synchronous parallel acquisition system for data of speed field and temperature field and application method |
-
2023
- 2023-11-01 CN CN202311437152.3A patent/CN117168758B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4149089A (en) * | 1975-12-05 | 1979-04-10 | The Bendix Corporation | Electro-optical scanner for generating digital flaw data |
| US4708495A (en) * | 1985-04-23 | 1987-11-24 | Noranda Inc. | Metal surface temperature monitor |
| CN205228771U (en) * | 2015-11-13 | 2016-05-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Experimental minute -pressure measurement system in low speed wind tunnel flow field |
| CN206990072U (en) * | 2017-08-08 | 2018-02-09 | 天信仪表集团有限公司 | A kind of flowmeter on-line diagnosing apparatus |
| CN211696724U (en) * | 2019-12-23 | 2020-10-16 | 陕西电器研究所 | Multi-channel temperature signal conversion device |
| CN112326050A (en) * | 2020-11-18 | 2021-02-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | System and method for testing large-area temperature distribution of hypersonic-speed high-temperature wind tunnel |
| CN112326184A (en) * | 2020-11-25 | 2021-02-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Frequency-variable high-precision wind tunnel test data acquisition method |
| CN112649148A (en) * | 2021-01-19 | 2021-04-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-frequency pulsating pressure testing device for hypersonic flight test |
| CN115014696A (en) * | 2022-08-08 | 2022-09-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for synchronous acquisition and integrated processing of wind tunnel multi-signal source data |
| CN115183897A (en) * | 2022-09-09 | 2022-10-14 | 之江实验室 | Temperature measuring system and method based on high-frequency alternating current signals |
| CN115508040A (en) * | 2022-11-17 | 2022-12-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Synchronous parallel acquisition system for data of speed field and temperature field and application method |
Non-Patent Citations (5)
| Title |
|---|
| 唐志共: "高速空气动力学三大手段数据融合研究进展", 空气动力学学报 * |
| 张晋铭: "基于FPGA的高精度采集系统的优化设计", 现代电子技术 * |
| 罗金玲;周丹;康宏琳;王济康;: "典型气动问题试验方法研究的综述", 空气动力学学报, no. 05 * |
| 陆小革: "高超声速边界层转捩及激波湍流边界层干扰的实验研究", 中国博士学位论文全文数据库 基础科学辑 * |
| 马游春;何巧;孙宇梦;刘鹏媛;: "基于文件管理的采编记录仪设计", 电子器件, no. 03 * |
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