CN109556877A - A kind of exhaust temperature of aircraft engine scaling method - Google Patents
A kind of exhaust temperature of aircraft engine scaling method Download PDFInfo
- Publication number
- CN109556877A CN109556877A CN201811567115.3A CN201811567115A CN109556877A CN 109556877 A CN109556877 A CN 109556877A CN 201811567115 A CN201811567115 A CN 201811567115A CN 109556877 A CN109556877 A CN 109556877A
- Authority
- CN
- China
- Prior art keywords
- engine
- temperature
- exhaust temperature
- aircraft
- electromotive force
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- 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
- G01K15/002—Calibrated temperature sources, temperature standards therefor
-
- 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
- G01K15/005—Calibration
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a kind of exhaust temperature of aircraft engine scaling methods, it is intended to solve the problems, such as that time-consuming, resource consumption is big for existing engine exhaust temperature calibration.The present invention replaces engine thermal galvanic couple to automatically adjust one group of shared standard eleotromotive force signal of device and the output of aircraft parameter acquisition and recording system to engine simultaneously using electromotive force signal output device.The present invention exports multiple standard eleotromotive force signals using high precision electro kinetic potential signal output apparatus, is calibrated, is demarcated to delivery temperature measured value with delivery temperature standard value respectively, and the present invention improves stated accuracy, has preferable practicability.The present invention does not need to carry out the engine exhaust temperature static demarcating method of engine test, engine exhaust temperature can be demarcated in the idle situation of engine, save the fuel consumption of engine test and the working life of engine, human and material resources needed for greatly reducing staking-out work simultaneously, and it is easy to operate.
Description
Technical field
The invention belongs to the technical fields of engine temperature calibration, and in particular to a kind of exhaust temperature of aircraft engine calibration
Method.
Background technique
Exhaust temperature of aircraft engine is an important parameter of engine, and excessive discharge temperature will result directly in engine
Loss, scrap.Therefore, increasingly important is just shown to the accurate monitoring of engine exhaust temperature.By being acquired to aircraft parameter
The engine exhaust temperature of system acquisition is demarcated, and the monitoring of delivery temperature can be made more accurate.Engine exhaust at present
Temperature calibration is by engine test, and engine automatically adjusts device and aircraft parameter acquisition system acquires the temperature of several points respectively
Degree, then using the temperature of engine automatic adjustment device acquisition as standard, school is carried out to the temperature of aircraft parameter acquisition system acquisition
Quasi-, calibration.This scaling method must carry out transmitter test run, need to expend the service life of aircraft fuel oil and a part of engine.
Meanwhile the staking-out work time is long, and a large amount of related personnel is needed to cooperate.
Summary of the invention
The purpose of the present invention is to provide a kind of exhaust temperature of aircraft engine scaling method, the present invention does not need to send out
The engine exhaust temperature static demarcating method of motivation test run, it is intended to solve the calibration of existing engine exhaust temperature time-consuming,
The big problem of resource consumption.
The present invention is achieved through the following technical solutions: a kind of exhaust temperature of aircraft engine scaling method, main to wrap
Include following steps:
Step S100: engine thermal galvanic couple is replaced to automatically adjust device to engine simultaneously and fly using electromotive force signal output device
Machine parameter acquisition records system and exports one group of shared standard eleotromotive force signal；
Step S200: and then the delivery temperature of engine automatic adjustment device calculating is checked by engines ground inspection equipment and is incited somebody to action
The temperature checks the exhaust temperature that aircraft parameter acquisition system calculates as standard value, using aircraft engine parameter detection equipment
Spend measured value；
Step S300: coefficient is resolved to the delivery temperature in aircraft parameter acquisition system according to the standard value that automatic adjustment device resolves
It is modified.
In order to preferably realize the present invention, further, resolution ratio >=0.01mV of the electromotive force signal output device,
And meet K-type thermocouple indexing table.
In order to preferably realize the present invention, further, the electromotive force signal output device exports multiple and different electricity
The delivery temperature of electromotive force signal, the exemplary operation state within the scope of 300 DEG C to 900 DEG C according to engine is chosen.
In order to preferably realize the present invention, further, the exemplary operation state includes slow train, training, maximum, fight
It is maximum.
In order to preferably realize the present invention, further, engine automatic adjustment device and aircraft ginseng in the step S200
Number acquisition and recording systems receive high precision electro kinetic potential signal output apparatus to electromotive force signal after, it is electronic to calculate separately out standard
The corresponding temperature of gesture signal.
In order to preferably realize the present invention, further, set in the step S300 using aircraft engine parameter detecting
The standby measured value resolved on the basis of the standard value for automatically adjusting device resolving to aircraft parameter acquisition system is calibrated, is demarcated.
In order to preferably realize the present invention, further, after completing first outlet air temperature calibration, according to given
Standard eleotromotive force corresponding to normal temperature completes the calibration of second outlet air temperature；It loops back and forth like this, until completing institute
There are defined temperature value calibration, calibration.
The technical scheme adopted by the invention is that: according to the working principle of engine exhaust temperature thermocouple, i.e., in thermoelectricity
In the case that even cold junction temperature remains unchanged, engine exhaust temperature is higher, and it is higher that thermocouple exports electromotive force.Meanwhile thermoelectricity
Even output electromotive force meets K-type thermocouple indexing table, directly can obtain thermocouple output by inquiring K-type thermocouple indexing table
Electric thermo-couple temperature corresponding to electromotive force.
This programme is indexed using high precision electro kinetic potential signal output apparatus (resolution ratio >=0.01mV) according to K-type thermocouple
Table automatically adjusts device to engine simultaneously instead of engine thermal galvanic couple and one group of aircraft parameter acquisition and recording system output is (multiple
Different electromotive force signals carries out within the scope of 300 DEG C to 900 DEG C according to the delivery temperature of the several exemplary operation states of engine
Choose) shared standard eleotromotive force signal.Engine automatic adjustment device and aircraft parameter acquisition and recording system receive high precision electro
After the electromotive force signal that electromotive force signal output device is given, the corresponding temperature of standard electromotive force signal is calculated separately out.Then, pass through
Engines ground checks the delivery temperature that equipment checks that engine automatic adjustment device calculates and using the temperature as standard value, makes
The delivery temperature measured value that aircraft parameter acquisition system calculates is checked with aircraft engine parameter detection equipment.Finally, using
What aircraft engine parameter detection equipment resolved aircraft parameter acquisition system on the basis of the standard value for automatically adjusting device resolving
Measured value is calibrated, is demarcated, i.e., the standard value resolved according to automatic adjustment device is to the exhaust temperature in aircraft parameter acquisition system
Degree resolves coefficient and is modified.To guarantee stated accuracy, this method is exported multiple using high precision electro kinetic potential signal output apparatus
Standard eleotromotive force signal is respectively calibrated delivery temperature measured value with delivery temperature standard value, is demarcated.
Beneficial effects of the present invention:
(1) present invention do not need carry out engine test engine exhaust temperature static demarcating method, can engine not
Engine exhaust temperature is demarcated in the case where work, saves the fuel consumption of engine test and the work of engine
Service life, while human and material resources needed for greatly reducing staking-out work, and it is easy to operate.
(2) present invention exports multiple standard eleotromotive force signals using high precision electro kinetic potential signal output apparatus, respectively with row
Gas standard temperature is calibrated delivery temperature measured value, is demarcated, and the present invention improves stated accuracy, has preferable practical
Property.
(3) thermocouple direct feeling engine exhaust temperature and electromotive force is converted into when opposite front engine is driven
Signal automatically adjusts device to engine simultaneously in the several different working conditions of engine (slow train, maximum, the fight maximum of training etc.)
One group of (multiple and different electromotive force signals) electromotive force signal is exported with aircraft parameter acquisition and recording system.
Detailed description of the invention
Fig. 1 is exhaust temperature of aircraft engine static demarcating schematic diagram of the invention.
Specific embodiment
Embodiment 1:
A kind of exhaust temperature of aircraft engine scaling method, as shown in Figure 1, mainly comprising the steps that
Step S100: engine thermal galvanic couple is replaced to automatically adjust device to engine simultaneously and fly using electromotive force signal output device
Machine parameter acquisition records system and exports one group of shared standard eleotromotive force signal；
Step S200: and then the delivery temperature of engine automatic adjustment device calculating is checked by engines ground inspection equipment and is incited somebody to action
The temperature checks the exhaust temperature that aircraft parameter acquisition system calculates as standard value, using aircraft engine parameter detection equipment
Spend measured value；
Step S300: coefficient is resolved to the delivery temperature in aircraft parameter acquisition system according to the standard value that automatic adjustment device resolves
It is modified.
The present invention do not need carry out engine test engine exhaust temperature static demarcating method, can engine not
Engine exhaust temperature is demarcated in the case where work, saves the fuel consumption of engine test and the work of engine
Service life, while human and material resources needed for greatly reducing staking-out work, and it is easy to operate.The present invention uses high precision electro kinetic potential
Signal output apparatus exports multiple standard eleotromotive force signals, carries out school to delivery temperature measured value with delivery temperature standard value respectively
Quasi-, calibration, the present invention improve stated accuracy, have preferable practicability.
Embodiment 2:
The present embodiment is to optimize on the basis of embodiment 1, the resolution ratio of the electromotive force signal output device >=
0.01mV, and meet K-type thermocouple indexing table.The electromotive force signal output device exports multiple and different electromotive force signals,
The delivery temperature of exemplary operation state within the scope of 300 DEG C to 900 DEG C according to engine is chosen.The exemplary operation shape
State includes slow train, training, maximum, fight maximum.
Thermocouple direct feeling engine exhaust temperature and electromotive force letter is converted into when opposite front engine is driven
Number, in the several different working conditions of engine (slow train, maximum, the fight maximum of training etc.) simultaneously to engine automatic adjustment device and
Aircraft parameter acquisition and recording system exports one group of (multiple and different electromotive force signals) electromotive force signal.The present invention uses high-precision
Electromotive force signal output device exports multiple standard eleotromotive force signals, respectively with delivery temperature standard value to delivery temperature measured value
It calibrated, demarcated, the present invention improves stated accuracy, has preferable practicability.
The other parts of the present embodiment are same as Example 1, and so it will not be repeated.
Embodiment 3:
The present embodiment is optimized on the basis of embodiment 1 or 2, and engine automatically adjusts device and flies in the step S200
Machine parameter acquisition record system receive high precision electro kinetic potential signal output apparatus to electromotive force signal after, calculate separately out standard
The corresponding temperature of electromotive force signal.Using aircraft engine parameter detection equipment to automatically adjust device resolving in the step S300
Standard value on the basis of measured value that aircraft parameter acquisition system is resolved calibrated, demarcated.
The present invention do not need carry out engine test engine exhaust temperature static demarcating method, can engine not
Engine exhaust temperature is demarcated in the case where work, saves the fuel consumption of engine test and the work of engine
Service life, while human and material resources needed for greatly reducing staking-out work, and it is easy to operate.The present invention uses high precision electro kinetic potential
Signal output apparatus exports multiple standard eleotromotive force signals, carries out school to delivery temperature measured value with delivery temperature standard value respectively
Quasi-, calibration, the present invention improve stated accuracy, have preferable practicability.
The other parts of the present embodiment are identical as above-described embodiment 1 or 2, and so it will not be repeated.
Embodiment 4:
A kind of exhaust temperature of aircraft engine scaling method, as shown in Figure 1, arranging in the idle situation of engine engine
Temperature degree is demarcated.Thermocouple direct feeling engine exhaust temperature and electricity is converted into when opposite front engine is driven
Electromotive force signal is adjusted to engine automatically simultaneously in the several different working conditions of engine (slow train, maximum, the fight maximum of training etc.)
It saves device and aircraft parameter acquisition and recording system exports one group of (multiple and different electromotive force signals) electromotive force signal；
Engine automatic adjustment device and aircraft parameter acquisition and recording system receive thermocouple to electromotive force signal after, calculate separately
The corresponding temperature of thermocouple electromotive force signal out.Then, check that equipment checks that engine automatically adjusts device by engines ground
The delivery temperature that calculates and using the temperature as standard value, checks that aircraft parameter is adopted using aircraft engine parameter detection equipment
The delivery temperature measured value that collecting system calculates；
Finally, being adopted on the basis of the standard value for automatically adjusting device resolving to aircraft parameter using aircraft engine parameter detection equipment
The measured value that collecting system resolves is calibrated, is demarcated, and this programme saves the fuel consumption of engine test and the work of engine
Make the service life, while human and material resources needed for greatly reducing staking-out work, and easy to operate.
Working principle: the plug of engine thermal thermocouple sensor is disconnected, high precision electro kinetic potential signal output apparatus is used
It is connected instead of engine thermal galvanic couple with the acting thermocouple plug at aircraft end.Connect engines ground inspection and the inspection of aircraft engine parameter
Measurement equipment, aircraft power on.Using electromotive force signal output device, a standard eleotromotive force signal, engine automatic adjustment are exported
Device and aircraft parameter acquisition system respectively resolve the electromotive force signal.It checks that equipment is checked using engines ground to start
The machine delivery temperature that calculates of automatic adjustment device and using the temperature as normal temperature, to using aircraft engine parameter detecting to set
The exhaust observed temperature that the aircraft parameter acquisition system for future reference seen resolves is calibrated, is demarcated.
After completing first outlet air temperature calibration, according to given normal temperature (several typical cases according to engine
The actual exhaust air temperature of working condition is chosen) corresponding to standard eleotromotive force, complete the calibration of second outlet air temperature.
It loops back and forth like this, until completing all defined temperature value calibrations, calibration.
The present invention do not need carry out engine test engine exhaust temperature static demarcating method, can engine not
Engine exhaust temperature is demarcated in the case where work, saves the fuel consumption of engine test and the work of engine
Service life, while human and material resources needed for greatly reducing staking-out work, and it is easy to operate.The present invention uses high precision electro kinetic potential
Signal output apparatus exports multiple standard eleotromotive force signals, carries out school to delivery temperature measured value with delivery temperature standard value respectively
Quasi-, calibration, the present invention improve stated accuracy, have preferable practicability.
The above is only presently preferred embodiments of the present invention, not does limitation in any form to the present invention, it is all according to
According to technical spirit any simple modification to the above embodiments of the invention, equivalent variations, protection of the invention is each fallen within
Within the scope of.
Claims (7)
1. a kind of exhaust temperature of aircraft engine scaling method, which is characterized in that mainly comprise the steps that
Step S100: engine thermal galvanic couple is replaced to automatically adjust device to engine simultaneously and fly using electromotive force signal output device
Machine parameter acquisition records system and exports one group of shared standard eleotromotive force signal；
Step S200: and then the delivery temperature of engine automatic adjustment device calculating is checked by engines ground inspection equipment and is incited somebody to action
The temperature checks the exhaust temperature that aircraft parameter acquisition system calculates as standard value, using aircraft engine parameter detection equipment
Spend measured value；
Step S300: coefficient is resolved to the delivery temperature in aircraft parameter acquisition system according to the standard value that automatic adjustment device resolves
It is modified.
2. a kind of exhaust temperature of aircraft engine scaling method according to claim 1, which is characterized in that the electromotive force
Resolution ratio >=0.01mV of signal output apparatus, and meet K-type thermocouple indexing table.
3. a kind of exhaust temperature of aircraft engine scaling method according to claim 2, which is characterized in that the electromotive force
Signal output apparatus exports multiple and different electromotive force signals, according to the exemplary operation of engine within the scope of 300 DEG C to 900 DEG C
The delivery temperature of state is chosen.
4. a kind of exhaust temperature of aircraft engine scaling method according to claim 3, which is characterized in that typical case's work
It include slow train, training, maximum, fight maximum as state.
5. a kind of exhaust temperature of aircraft engine scaling method according to claim 1-4, which is characterized in that institute
It states engine automatic adjustment device and aircraft parameter acquisition and recording system in step S200 and receives high precision electro kinetic potential signal output dress
Set to electromotive force signal after, calculate separately out the corresponding temperature of standard electromotive force signal.
6. a kind of exhaust temperature of aircraft engine scaling method according to claim 5, which is characterized in that the step
Aircraft parameter is acquired on the basis of the standard value for automatically adjusting device resolving using aircraft engine parameter detection equipment in S300
The measured value that system resolves is calibrated, is demarcated.
7. a kind of exhaust temperature of aircraft engine scaling method according to claim 6, which is characterized in that complete first
After a outlet air temperature calibration, according to standard eleotromotive force corresponding to given normal temperature, second outlet air temperature is completed
Calibration；It loops back and forth like this, until completing all defined temperature value calibrations, calibration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811567115.3A CN109556877A (en) | 2018-12-21 | 2018-12-21 | A kind of exhaust temperature of aircraft engine scaling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811567115.3A CN109556877A (en) | 2018-12-21 | 2018-12-21 | A kind of exhaust temperature of aircraft engine scaling method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109556877A true CN109556877A (en) | 2019-04-02 |
Family
ID=65870720
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811567115.3A Pending CN109556877A (en) | 2018-12-21 | 2018-12-21 | A kind of exhaust temperature of aircraft engine scaling method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109556877A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110646212A (en) * | 2019-10-23 | 2020-01-03 | 成都飞机工业（集团）有限责任公司 | Novel method for calibrating aircraft engine |
| CN112098108A (en) * | 2020-08-19 | 2020-12-18 | 西北工业大学 | Gas rotation temperature calibration and verification method on rotating disc |
| CN112179513A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Multipoint temperature measuring device for thermal fatigue test and operation method thereof |
| WO2022052824A1 (en) * | 2020-09-09 | 2022-03-17 | 追觅创新科技(苏州)有限公司 | Power control method and apparatus for blower, and temperature control parameter calibration method and apparatus for blower |
| CN117885256A (en) * | 2024-03-14 | 2024-04-16 | 成都飞机工业（集团）有限责任公司 | Part curing temperature monitoring method for temperature hysteresis area in margin line |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2771815A1 (en) * | 1997-12-02 | 1999-06-04 | Renault | Exhaust gas temperature estimation process |
| CN101929895A (en) * | 2009-06-22 | 2010-12-29 | 博格华纳贝鲁系统有限公司 | The method of machines motor vehicle engine delivery temperature |
| CN102562239A (en) * | 2011-11-13 | 2012-07-11 | 哈尔滨工业大学 | Method for monitoring exhaust temperature of aircraft engine |
| CN102928232A (en) * | 2012-11-21 | 2013-02-13 | 中国民用航空飞行学院 | Prediction method for complete machine performance decline trend of aeroengine |
| CN204514504U (en) * | 2014-11-30 | 2015-07-29 | 中航贵州飞机有限责任公司 | A kind of portable delivery temperature caliberating device |
| CN106679983A (en) * | 2017-02-14 | 2017-05-17 | 成都飞机工业（集团）有限责任公司 | Parameter calibration method for airplane turbofan engine |
-
2018
- 2018-12-21 CN CN201811567115.3A patent/CN109556877A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2771815A1 (en) * | 1997-12-02 | 1999-06-04 | Renault | Exhaust gas temperature estimation process |
| CN101929895A (en) * | 2009-06-22 | 2010-12-29 | 博格华纳贝鲁系统有限公司 | The method of machines motor vehicle engine delivery temperature |
| CN102562239A (en) * | 2011-11-13 | 2012-07-11 | 哈尔滨工业大学 | Method for monitoring exhaust temperature of aircraft engine |
| CN102928232A (en) * | 2012-11-21 | 2013-02-13 | 中国民用航空飞行学院 | Prediction method for complete machine performance decline trend of aeroengine |
| CN204514504U (en) * | 2014-11-30 | 2015-07-29 | 中航贵州飞机有限责任公司 | A kind of portable delivery temperature caliberating device |
| CN106679983A (en) * | 2017-02-14 | 2017-05-17 | 成都飞机工业（集团）有限责任公司 | Parameter calibration method for airplane turbofan engine |
Non-Patent Citations (1)
| Title |
|---|
| 李相国等: "飞机发动机排气温度标校方法研究", 《探索 创新 交流——第五届中国航空学会青年科技论坛文集(第5集)》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110646212A (en) * | 2019-10-23 | 2020-01-03 | 成都飞机工业（集团）有限责任公司 | Novel method for calibrating aircraft engine |
| CN112098108A (en) * | 2020-08-19 | 2020-12-18 | 西北工业大学 | Gas rotation temperature calibration and verification method on rotating disc |
| CN112098108B (en) * | 2020-08-19 | 2022-03-15 | 西北工业大学 | Gas rotation temperature calibration and verification method on rotating disc |
| WO2022052824A1 (en) * | 2020-09-09 | 2022-03-17 | 追觅创新科技(苏州)有限公司 | Power control method and apparatus for blower, and temperature control parameter calibration method and apparatus for blower |
| CN112179513A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Multipoint temperature measuring device for thermal fatigue test and operation method thereof |
| CN112179513B (en) * | 2020-09-18 | 2023-01-17 | 中国航发四川燃气涡轮研究院 | Multipoint temperature measuring device for thermal fatigue test and operation method thereof |
| CN117885256A (en) * | 2024-03-14 | 2024-04-16 | 成都飞机工业（集团）有限责任公司 | Part curing temperature monitoring method for temperature hysteresis area in margin line |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109556877A (en) | A kind of exhaust temperature of aircraft engine scaling method | |
| CN104198190B (en) | Aeromotor integrated test system | |
| CN108572280A (en) | A kind of large range high precision explosive device resistance tester | |
| CN208270656U (en) | A kind of large range high precision explosive device resistance tester | |
| CN109781268A (en) | Keypoint part temperature monitoring system in a kind of switchgear based on the infrared thermovision technology of low cost | |
| CN109870650A (en) | Battery cell monitoring method and system | |
| CN110714909A (en) | Test system of air compressor of fuel cell | |
| CN104481608B (en) | Temperature measuring equipment, whirlpool oar aero-engine and thermometry | |
| CN206805286U (en) | A kind of device of DCS system simulations amount signal acquisition browsing real-time data | |
| CN109470389A (en) | Strain-type torch measuring system and method | |
| CN104279113A (en) | Engine ignition energy testing device for vehicle | |
| CN211086505U (en) | Reliability state detection device for IGBT in power electronic transformer substation | |
| CN111044830A (en) | Zinc oxide arrester operating characteristic live monitoring device | |
| CN107543574B (en) | Automatic detector for high-temperature aging test of airborne sensor and operation method | |
| CN106525436B (en) | A kind of engine test long-range exhaust system collecting and distributing type parameter measurement system and method | |
| CN105137254A (en) | Submersible transformer automatic detection system based on PLC and embedded system | |
| CN108225599A (en) | A kind of super capacitor temp detecting controller | |
| CN213275769U (en) | Novel low-voltage loop resistance tester | |
| CN211577410U (en) | System for checking electric energy error of direct current charger | |
| CN210835070U (en) | Bus duct impedance measuring device | |
| CN211955739U (en) | Portable quick intermediate relay calibration equipment | |
| CN114088231A (en) | Temperature testing device for rotor part of low-pressure turbine in complete state of aircraft engine | |
| CN113432743A (en) | Acquisition circuit and method for improving acquisition precision of temperature sensor | |
| CN105866727A (en) | Real-time checking system for electric energy meter calibrating device | |
| CN210664758U (en) | Vibration meter for fan of electronic cabin of airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190402 |