CN112179522A - Aircraft surface temperature sensor testing system and testing method - Google Patents
Aircraft surface temperature sensor testing system and testing method Download PDFInfo
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- CN112179522A CN112179522A CN202010960630.9A CN202010960630A CN112179522A CN 112179522 A CN112179522 A CN 112179522A CN 202010960630 A CN202010960630 A CN 202010960630A CN 112179522 A CN112179522 A CN 112179522A
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- 238000012360 testing method Methods 0.000 title claims abstract description 93
- 238000000034 method Methods 0.000 claims abstract description 11
- 230000003068 static effect Effects 0.000 claims abstract description 8
- 238000005259 measurement Methods 0.000 claims description 17
- 230000002159 abnormal effect Effects 0.000 claims description 12
- 230000008859 change Effects 0.000 claims description 11
- 238000010438 heat treatment Methods 0.000 claims description 8
- 230000007613 environmental effect Effects 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 4
- 238000010924 continuous production Methods 0.000 claims description 3
- 238000011017 operating method Methods 0.000 claims description 2
- 238000010998 test method Methods 0.000 claims description 2
- 230000008569 process Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K15/00—Testing or calibrating of thermometers
- G01K15/007—Testing
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- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04W—WIRELESS COMMUNICATION NETWORKS
- H04W4/00—Services specially adapted for wireless communication networks; Facilities therefor
- H04W4/30—Services specially adapted for particular environments, situations or purposes
- H04W4/38—Services specially adapted for particular environments, situations or purposes for collecting sensor information
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Abstract
The invention discloses a system and a method for testing an aircraft surface temperature sensor, wherein the system comprises: the system comprises an aircraft body, a surface temperature sensor, an airborne remote measuring system, a ground testing system, a temperature loading device, a standard thermometer and a stopwatch timer. The invention respectively tests the performance of the surface temperature sensor through a static test and a loading test, wherein the static test is used for interpreting the deviation between the measured value of the surface temperature sensor and the ambient temperature, and the loading test is used for judging whether the data of the surface temperature sensor is normal under the load condition; the invention solves the problems that the function correctness of the aircraft surface sensor and the data acquisition system can not be verified, and the reliability of the surface pressure sensor system of the aircraft after storage and transportation can not be verified, tests are carried out by taking the surface temperature sensor as a subsystem of the whole aircraft, the test operation is simple, the data are clear and reliable, the judgment standard is clear, and the test level of the aircraft sensor system is obviously improved.
Description
Technical Field
The invention belongs to the technical field of aircraft sensor testing, and particularly relates to a system and a method for testing an aircraft surface temperature sensor.
Background
In the flight test process of the aerospace model, the temperature change information of the surface of the aircraft, in particular the gravity areas such as a windward surface, a transition area, a shock wave interference area and the like needs to be measured. The atmospheric environment of the areas is complex, the temperature changes violently, the measuring interference factors are more, and the reliability of the sensor directly influences the result of the flight test. Therefore, a series of calibration and test means need to be designed to verify the working reliability of the sensor. However, in the existing flight test process, the temperature sensor can only complete the single-machine calibration work before installation; there is no suitable means to perform functional and performance verification of the sensor after it is installed on the aircraft. The sensor may fail or otherwise degrade due to installation, environmental testing, shipping, etc. If the state of the sensor cannot be verified before flight, the reliability of the data obtained by flight test measurement is also affected.
Disclosure of Invention
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter.
To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided an aircraft surface temperature sensor testing system comprising:
the surface of the aircraft body is provided with a surface temperature sensor, and the interior of the aircraft body is provided with an airborne remote measuring system connected with the surface temperature sensor;
the ground remote measuring system is used for interpreting aircraft test data and the ground test system is used for controlling aircraft test; the ground test system is connected with the aircraft body through a cable, and the ground remote measurement system is in wireless communication connection with the airborne remote measurement system;
the temperature loading device is used for loading the temperature of the surface temperature sensor, and the detachable equipment of the temperature loading device is mounted on the surface of the aircraft body;
a standard thermometer for measuring ambient temperature values and a stopwatch timer for accurately recording the test time.
A method of testing an aircraft surface temperature sensor testing system, comprising the steps of:
step one, carrying out static test, specifically comprising the following steps:
step S11, measuring the temperature value of the current environment by using a calibrated standard thermometer;
step S12, taking the average value of the environmental temperature at the time specified by the operating procedure as the estimated value of the current real temperature;
step S13, reading the measured value of the aircraft surface temperature sensor through a ground telemetering system;
step S14, comparing the measured value of the aircraft surface temperature sensor with the environment temperature estimated value obtained in the step I, indicating that the data of the surface temperature sensor is normal within the given temperature deviation, otherwise indicating that the surface temperature sensor works abnormally;
step two, carrying out a surface temperature sensor loading test, which comprises the following specific steps:
step S21, self-checking the temperature loading device;
step S22, setting the temperature loading device to the temperature required by the test;
s23, recording an initial temperature value of a point to be measured on the surface of the aircraft body;
s24, heating the aircraft surface temperature sensor by using a temperature loading device, wherein the heating time is subject to the test operation regulation, and the heating process is a continuous process;
step S25, recording a temperature value measured by the surface temperature sensor to be measured when the loading is finished;
step S26, judging whether the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured are within the specified deviation range when the loading is finished; if the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured are within the specified deviation range after the loading is finished, the surface temperature sensor to be measured works normally, otherwise, the surface temperature sensor to be measured works abnormally;
and step S27, repeating the fourth step to the sixth step until all the surface temperature sensor tests are completed.
Preferably, the specific determination method for comparing the measured value of the aircraft surface temperature sensor in the first step with the estimated value of the ambient temperature obtained in the first step includes:
if the measured value of the surface temperature sensor and the estimated value of the environment temperature are within the deviation range, the following steps are carried out:
it is judged that the surface temperature sensor is operating normally, where TiIs the measurement of the ith surface temperature sensor,
is an ambient temperature estimate, Δ T is a prescribed temperature range deviation amount;
calculating the mean value E (T) of all the surface temperature sensor measurements
Calculating the standard deviation sigma of all the surface temperature sensor measurement values by using the calculated mean value E (T)
Wherein, TiIs the ith surface temperature sensor measurement, n is the number of surface temperature sensors; if the data of the surface temperature sensor are distributed within 3 sigma, but the deviation between the mean value E (T) and the environment temperature estimated value is larger, the standard thermometer is indicated to be in fault;
if the measured value of the surface temperature sensor exceeds a given deviation limit, but the deviation between the actual measured value and the environment temperature estimated value is in a white noise state, the deviation limit is set to be too small;
the other cases determine that the surface temperature sensor data is abnormal.
Preferably, in the second step, it is determined whether or not the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured at the end of the loading are within a predetermined deviation range, and if the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured at the end of the loading are within the predetermined deviation range, the second step is that:
it is judged that the surface temperature sensor is operating normally, where Ti eIs the temperature value at the end of the loading of the ith surface temperature sensor, Ti SIs the initial temperature value of the ith surface temperature sensor, t is the loading duration, and is the given deviation range; the other cases determine that the surface temperature sensor is operating abnormally.
Preferably, in the second step, if the temperature data of the surface sensor to be tested is found to be abnormal in the loading test, the loading test and the data interpretation are repeatedly performed on the abnormal surface temperature sensor; if the two times of continuous abnormity, confirming that the surface temperature sensor to be measured works abnormally; and if the second test data is normal, carrying out third repeated loading test and data interpretation, and if the data is normal, determining that the surface temperature sensor works normally, and if the data is abnormal, determining that the surface temperature sensor works abnormally.
The invention at least comprises the following beneficial effects: the invention can test the installation correctness of the surface temperature sensor after the aircraft assembly is finished; the reliability of the surface temperature sensor can be tested after environmental tests, storehouse storage and long-distance transportation; the method can be used as the last gateway before the aircraft is subjected to emergent takeoff to verify the reliability of the data of the surface temperature sensor. The correctness of the surface temperature sensor body and the collection and transformation system is verified by interpreting the measurement data of the surface temperature sensor under the static and dynamic conditions.
The invention solves the problems that after the aircraft is assembled, the function correctness of the aircraft surface sensor and the data acquisition system can not be verified, and the reliability of the aircraft surface pressure sensor system after environmental test, storehouse storage and transportation can not be verified; the surface temperature sensor is used as a subsystem of the whole aircraft for testing, the testing operation is simple, the data are clear and reliable, the judgment standard is clear, and the testing level of the aircraft sensor system is obviously improved.
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.
Description of the drawings:
FIG. 1 is a schematic structural diagram of an aircraft surface temperature sensor testing system provided by the invention.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
It is to be understood that in the description of the present invention, the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are used only for convenience in describing the present invention and for simplification of the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless otherwise specifically stated or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are used broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, or a communication between two elements, and those skilled in the art will understand the specific meaning of the terms in the present invention specifically.
Further, in the present invention, unless otherwise explicitly specified or limited, a first feature "on" or "under" a second feature may be directly contacted with the first and second features, or indirectly contacted with the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
As shown in fig. 1: the invention relates to a system for testing an aircraft surface temperature sensor, which comprises:
the surface temperature monitoring system comprises an aircraft body 1, a surface temperature sensor 2 is mounted on the surface of the aircraft body 1, an airborne telemetering system 8 is mounted inside the aircraft body 1, and the airborne telemetering system 8 is connected with the surface temperature sensor 2 through a cable; during the test shown in fig. 1, the aircraft body 1 is in a stationary parked state.
The system comprises a ground remote measuring system 5 for reading test data of the aircraft and a ground test system 4 for testing and controlling the aircraft, wherein the ground test system 4 is connected with an aircraft body 1 by a cable, the ground remote measuring system 5 is in wireless communication connection with an airborne remote measuring system 8, and the airborne remote measuring system 8 is used for storing and transmitting temperature data obtained by measurement of a surface temperature sensor 2 to the ground remote measuring system 5;
the temperature loading device 3 is used for loading the temperature of the surface temperature sensor 2 and detachably mounted on the surface of the aircraft body 1;
a standard thermometer 6 for measuring ambient temperature values and a stopwatch timer 7 for accurately recording the test time.
The following embodiments provide a testing method of an aircraft surface temperature sensor testing system, comprising the following steps:
firstly, carrying out static test on a surface temperature sensor, and specifically comprising the following steps:
step S11, using a calibrated standard thermometer to stand near the aircraft body 1;
step S12, keeping the standard thermometer still for 3 minutes, reading the measured values of the standard thermometer every 30 seconds, obtaining 6 measured values of the environment temperature in total, and calculating to obtain the current estimated value of the environment temperature
Step S13, reading the temperature measurement value of each surface temperature sensor one by one through a ground telemetering system, and setting the measured value of the ith surface temperature sensor obtained by reading as
Step S14, data interpretation, judging whether the surface temperature sensor is normal under the static test condition;
the mean E (T) and standard deviation σ of all surface temperature sensor measurements were calculated:
wherein, TiIs the ith surface temperature sensor measurement, n is the number of surface temperature sensors;
if surface temperature sensor data Ti tDistributed within 3 σ, but with mean E (T) and ambient temperature estimate
The deviation is large, which indicates that the standard thermometer fails; if the surface temperature sensor measures
Beyond a given deviation limit, e.g. 50 ℃, but the actual measured value is compared with the ambient temperature estimate
The deviation is in a white noise state, which shows that the deviation limit is set to be too small; the other cases determine that the surface temperature sensor data is abnormal.
Step two, carrying out a surface temperature sensor loading test, which comprises the following specific steps:
step S21, self-checking the temperature loading device;
step S22, setting the temperature loading device to be 600 ℃ required by the test;
step S23, recording the initial temperature value T of the ith surface temperature sensor on the surface of the aircraft bodyi S；
Step S24, heating the ith surface temperature sensor by using a temperature loading device for 30 seconds, wherein the heating process is a continuous process;
step S25, recording the temperature value T measured by the ith surface temperature sensor when the loading is finishedi e；
Step S26, judging whether the temperature value and the temperature change gradient value measured by the ith surface temperature sensor are in the specified deviation range when the loading is finished;
if the temperature value and the temperature change gradient value measured by the surface temperature sensor at the end of loading are within the specified deviation range, namely:
it is judged that the surface temperature sensor is operating normally, where Ti eIs the temperature value T measured by the surface temperature sensor to be measured at the end of loadingi SThe initial temperature value of the surface temperature sensor to be measured, t is loading time and is a given deviation range; judging whether the surface temperature sensor to be detected works abnormally under other conditions;
and step S27, repeating the fourth step to the sixth step until all the surface temperature sensor tests are completed.
In the above technical solution, in the second step, if the temperature data of the surface sensor to be tested is found to be abnormal in the loading test, the loading test and the data interpretation are repeatedly performed on the abnormal surface temperature sensor; if the two times of continuous abnormity, confirming that the surface temperature sensor to be measured works abnormally; and if the second test data is normal, carrying out third repeated loading test and data interpretation, and if the data is normal, determining that the surface temperature sensor works normally, and if the data is abnormal, determining that the surface temperature sensor works abnormally.
The invention is applied to aircraft final assembly test, delivery test, technical position test, loading test implementation and static test implementation before launching of the launching position of the aircraft. In the testing process, the aircraft body is kept still, the detachable equipment 31 of the temperature loading device 3 is removed from the aircraft body 1 after the testing is finished, and the connection between the aircraft body 1 and the airborne remote measuring system 8 and the ground remote measuring system 5 and the ground testing system 4 is disconnected.
The number of apparatuses and the scale of the process described herein are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be apparent to those skilled in the art.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (5)
1. An aircraft skin temperature sensor testing system, comprising:
the surface of the aircraft body is provided with a surface temperature sensor, and the interior of the aircraft body is provided with an airborne remote measuring system connected with the surface temperature sensor;
the ground remote measuring system is used for interpreting aircraft test data and the ground test system is used for controlling aircraft test; the ground test system is connected with the aircraft body through a cable, and the ground remote measurement system is in wireless communication connection with the airborne remote measurement system;
the temperature loading device is used for loading the temperature of the surface temperature sensor, and the detachable equipment of the temperature loading device is mounted on the surface of the aircraft body;
a standard thermometer for measuring ambient temperature values and a stopwatch timer for accurately recording the test time.
2. A method of testing an aircraft surface temperature sensor testing system according to claim 1, comprising the steps of:
step one, carrying out static test, specifically comprising the following steps:
step S11, measuring the temperature value of the current environment by using a calibrated standard thermometer;
step S12, taking the average value of the environmental temperature at the time specified by the operating procedure as the estimated value of the current real temperature;
step S13, reading the measured value of the aircraft surface temperature sensor through a ground telemetering system;
step S14, comparing the measured value of the aircraft surface temperature sensor with the environment temperature estimated value obtained in the step I, indicating that the data of the surface temperature sensor is normal within the given temperature deviation, otherwise indicating that the surface temperature sensor works abnormally;
step two, carrying out a surface temperature sensor loading test, which comprises the following specific steps:
step S21, self-checking the temperature loading device;
step S22, setting the temperature loading device to the temperature required by the test;
s23, recording an initial temperature value of a point to be measured on the surface of the aircraft body;
s24, heating the aircraft surface temperature sensor by using a temperature loading device, wherein the heating time is subject to the test operation regulation, and the heating process is a continuous process;
step S25, recording a temperature value measured by the surface temperature sensor to be measured when the loading is finished;
step S26, judging whether the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured are within the specified deviation range when the loading is finished; if the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured are within the specified deviation range after the loading is finished, the surface temperature sensor to be measured works normally, otherwise, the surface temperature sensor to be measured works abnormally;
and step S27, repeating the fourth step to the sixth step until all the surface temperature sensor tests are completed.
3. The method for testing the aircraft skin temperature sensor test system according to claim 2, wherein the specific determination method for comparing the measured value of the aircraft skin temperature sensor in the first step with the estimated value of the ambient temperature obtained in the first step comprises:
if the measured value of the surface temperature sensor and the estimated value of the environment temperature are within the deviation range, the following steps are carried out:
it is judged that the surface temperature sensor is operating normally, where TiIs the measurement of the ith surface temperature sensor,
is an ambient temperature estimate, Δ T is a prescribed temperature range deviation amount;
calculating the mean value E (T) of all the surface temperature sensor measurements
Calculating the standard deviation sigma of all the surface temperature sensor measurement values by using the calculated mean value E (T)
Wherein, TiIs the ith surface temperature sensor measurement, n is the number of surface temperature sensors; if the data of the surface temperature sensor are distributed within 3 sigma, but the deviation between the mean value E (T) and the environment temperature estimated value is larger, the standard thermometer is indicated to be in fault;
if the measured value of the surface temperature sensor exceeds a given deviation limit, but the deviation between the actual measured value and the environment temperature estimated value is in a white noise state, the deviation limit is set to be too small;
the other cases determine that the surface temperature sensor data is abnormal.
4. The method for testing the aircraft surface temperature sensor test system according to claim 2, wherein the temperature value and the temperature measured by the surface temperature sensor to be tested at the end of loading are determined in the second stepWhether the change gradient value is in a specified deviation range or not, if the temperature value and the temperature change gradient value measured by the surface temperature sensor to be measured are in the specified deviation range after the loading is finished, namely:
it is judged that the surface temperature sensor is operating normally, where Ti eIs the temperature value at the end of the loading of the ith surface temperature sensor, Ti SIs the initial temperature value of the ith surface temperature sensor, t is the loading duration, and is the given deviation range; the other cases determine that the surface temperature sensor is operating abnormally.
5. The testing method of the aircraft surface temperature sensor testing system according to claim 2, wherein in the second step, if the temperature data of the surface temperature sensor to be tested is found to be abnormal in the loading test, the loading test and the data interpretation are repeated for the abnormal surface temperature sensor; if the two times of continuous abnormity, confirming that the surface temperature sensor to be measured works abnormally; and if the second test data is normal, carrying out third repeated loading test and data interpretation, and if the data is normal, determining that the surface temperature sensor works normally, and if the data is abnormal, determining that the surface temperature sensor works abnormally.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102183312A (en) * | 2011-03-16 | 2011-09-14 | 北京航空航天大学 | Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft |
| CN102353469A (en) * | 2011-09-29 | 2012-02-15 | 西北工业大学 | Online measurement device of high temperature of outer surface of high-speed aircraft, and preparation and measurement methods thereof |
| WO2015145085A1 (en) * | 2014-03-27 | 2015-10-01 | Snecma | Method for assessing whether or not a measured value of a physical parameter of an aircraft engine is normal |
| CN105083588A (en) * | 2015-08-17 | 2015-11-25 | 华南农业大学 | Performance test platform and method for multi-rotor unmanned aerial vehicle |
| CN106932121A (en) * | 2017-02-14 | 2017-07-07 | 中国科学院力学研究所 | A kind of platinum film resistor heat flow transducer caliberating device |
| CN107436200A (en) * | 2017-07-31 | 2017-12-05 | 北京临近空间飞行器系统工程研究所 | A kind of temperature survey path ground test method based on thermocouple sensor |
| CN107776912A (en) * | 2017-09-15 | 2018-03-09 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft ground TT＆C system net of center control |
| CN108088617A (en) * | 2016-11-23 | 2018-05-29 | 北京空间技术研制试验中心 | Aerodynamics force measurement sensor integrated test facility |
| CN110186581A (en) * | 2019-06-25 | 2019-08-30 | 北京临近空间飞行器系统工程研究所 | A kind of aircraft surface temperature sensor and sensor probe |
| CN110260928A (en) * | 2019-07-24 | 2019-09-20 | 河北斐然科技有限公司 | Aircraft telemetry system |
-
2020
- 2020-09-14 CN CN202010960630.9A patent/CN112179522A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102183312A (en) * | 2011-03-16 | 2011-09-14 | 北京航空航天大学 | Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft |
| CN102353469A (en) * | 2011-09-29 | 2012-02-15 | 西北工业大学 | Online measurement device of high temperature of outer surface of high-speed aircraft, and preparation and measurement methods thereof |
| WO2015145085A1 (en) * | 2014-03-27 | 2015-10-01 | Snecma | Method for assessing whether or not a measured value of a physical parameter of an aircraft engine is normal |
| CN105083588A (en) * | 2015-08-17 | 2015-11-25 | 华南农业大学 | Performance test platform and method for multi-rotor unmanned aerial vehicle |
| CN108088617A (en) * | 2016-11-23 | 2018-05-29 | 北京空间技术研制试验中心 | Aerodynamics force measurement sensor integrated test facility |
| CN106932121A (en) * | 2017-02-14 | 2017-07-07 | 中国科学院力学研究所 | A kind of platinum film resistor heat flow transducer caliberating device |
| CN107436200A (en) * | 2017-07-31 | 2017-12-05 | 北京临近空间飞行器系统工程研究所 | A kind of temperature survey path ground test method based on thermocouple sensor |
| CN107776912A (en) * | 2017-09-15 | 2018-03-09 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft ground TT＆C system net of center control |
| CN110186581A (en) * | 2019-06-25 | 2019-08-30 | 北京临近空间飞行器系统工程研究所 | A kind of aircraft surface temperature sensor and sensor probe |
| CN110260928A (en) * | 2019-07-24 | 2019-09-20 | 河北斐然科技有限公司 | Aircraft telemetry system |
Non-Patent Citations (1)
| Title |
|---|
| 李艳华等, 中国宇航出版社 * |
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