CN105241668B - Piston aviation engine test bay - Google Patents
Piston aviation engine test bay Download PDFInfo
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- CN105241668B CN105241668B CN201510846701.1A CN201510846701A CN105241668B CN 105241668 B CN105241668 B CN 105241668B CN 201510846701 A CN201510846701 A CN 201510846701A CN 105241668 B CN105241668 B CN 105241668B
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Abstract
The present invention provides piston aviation engine test bay, including motor mounts, the test engine being installed on motor mounts, test engine is connected with propeller, motor mounts are equipped with supporting rod, and supporting rod is equipped with lifting gear, adjust the terrain clearance of test engine, mounting bracket is connected with test bay main body, and test bay main body includes test system, test cell and the lorry for placing test cell.Using lorry as domain, mobility is good, convenience in transport and movement, and supporting rod is equipped with lifting gear, adjusts the terrain clearance of test engine, can conveniently meet the testing requirement of all kinds of piston aviation engines.
Description
Technical field
The present invention relates to aeroengine test field, and in particular to piston aviation engine test bay.
Background technology
Aero-engine is that a kind of technical difficulty is big, operating condition is complicated, maintenance requirement is harsh, it is higher to develop cost of use
Thermodynamic device.It has extremely complex structure, is played for aircraft reliability of operation, security and performance heavy to closing
The effect wanted.Aero-engine is in lifetime, in order to ensure flight safety, by regulation have to periodically to aircraft engine into
Row test run, detects the quality of engine properties.Whether its maintenance quality and technical indicator, which meets the requirements, directly influences
The completion of Flight Training Mission and flight safety, if engine breaks down, harmfulness is very big, is even resulted in when serious great
Aircraft accident.Therefore, strengthen the detection to engine and each department enclosure performance parameter be engineering maintenance personnel focus it
One.
The performance quality of aeroengine test run Integrated Checkout equipment directly affect aero-engine operation security and
Reliability.Engine test belongs to responsibility weight, consume energy high pilot project, and engine working process vibration is big, noise height with
And the interference signal produced, the requirement of higher is all proposed to test run inspection test system.To improve the inspection of aero-engine
Testing level, aero engine manufacturers both domestic and external and relevant unit study and produce many aeroplane engine machine check tests
Equipment.
Had the following disadvantages in terms of engine test performance detection used in the prior art：
Efficiency is low：Ground run detects complex procedures, and the detection of an engine performance parameter usually requires repeatedly to drive,
The consumption such as participation tester more, labor intensity is big, detection time is long, fuel oil are serious, efficiency is low, caused by same misjudgement test leakage
Operate repeatedly and more service life of aeroengine is also lost.
Automation, the level of informatization are low：Equipment does not have special computer record and preserves the data of test, reference record
Not in time, subsequent supplement is inaccurate, does not have data traceability function, and lacks the automatic management and analysis to detection process, moves
State means of testing falls behind.
There is an urgent need for it is a kind of have quick connection, high-speed data acquisition and take up little area, conveniently moving is directed to piston engine
Machine test bay, improve piston-mode motor performance parameter detection efficiency conscientiously, it is ensured that the accuracy of detection.
The content of the invention
It is an object of the invention to provide piston aviation engine test bay, solves the problems, such as said one or multiple.
The present invention provides piston aviation engine test bay, including motor mounts, is installed on motor mounts
On test engine, test engine is connected with propeller, and motor mounts are equipped with supporting rod, and supporting rod, which is equipped with, to be risen
Falling unit, adjusts the terrain clearance of test engine, and mounting bracket is connected with test bay main body, and test bay main body includes test and is
System, test cell and the lorry for placing test cell, are equipped with fuel tank at the top of test cell, be additionally provided with test cell observation window with
Hatch door.Using lorry as domain, mobility is good, convenience in transport and movement, and supporting rod is equipped with lifting gear, adjusts test
The terrain clearance of engine, can conveniently meet the testing requirement of all kinds of piston aviation engines.
In some embodiments, test platform includes testboard and test system, and test system includes fuel system, control
System, data collecting system, data handling system, power-supply system and industrial computer processed；
Fuel system is used to provide fuel oil needed for test engine test process；
Control system and fuel system, data collecting system, power-supply system, data handling system and industrial computer phase
Connection, for controlling whole test process；
Data collecting system includes multiple sensors, and sensor is arranged on test engine and propeller, for gathering
The data of test engine and propeller in operation, by data line transfer to data handling system；
Data handling system includes data storage module, data amplification module and data transmission module, and data preserve mould
Block is used to preserve the data that data collecting system transmission is come in, and work is transmitted to by data amplification module and data transmission module
Industry computer；
Power-supply system is used to provide the electric energy needed for whole test system work；
Industrial computer is used to handle data, the data after processing is preserved and including on industrial computer.By upper
The mutual cooperation of each system is stated, the testing requirement for meeting piston aviation engine is can be very good, substantially increases test
Accuracy, and test are comprehensive.
In some embodiments, fuel service system is used for the offer fuel oil to test engine, and fuel system includes
AFS Auxiliary Fuel Supply System and main oil supply system, AFS Auxiliary Fuel Supply System use the pre- oiling of electric booster pump, and main oil supply system uses gravity
The mode of fuel feeding, AFS Auxiliary Fuel Supply System carries out fuel feeding before test engine starts to test engine, in discharge line
Gas, keep oil circuit it is unimpeded；For main oil supply system in test engine startup and operational process, fuel tank passes through gravity feed oil
Mode to test engine sustainable supply fuel oil, ensure that test engine runs well.Main oil supply system volume of fuel tank is
300L, float-type fuel quantity inductor is equipped with fuel tank, Fuel Remained amount is shown in test run control interface by sensor,
Facilitate test run personnel to grasp the excess oil situation in fuel tank, can be greatly improved using AFS Auxiliary Fuel Supply System and main oil supply system
The efficiency of fuel feeding.
In some embodiments, control system is equipped with throttle control hand lever and mixing ratio joystick, Throttle Opening Control
Handle is used for the amount of fuel for controlling test engine, and then controls the rotating speed of test engine, and mixing ratio joystick is used to control
The lean and fat oil of test engine processed.The manipulation and control of engine testsand, using the control mode similar with aircraft.Surveying
The rotating speed and mixing ratio of engine are only controlled during examination, does not control the displacement of flight attitude and propeller.Using specified negative in test
The constant pitch airscrew of lotus, can so achieve the purpose that engine break-in, facilitate work-up the performance of engine, Throttle Opening Control hand
Handle and mixing ratio joystick the two joysticks are installed on the master console of control room, and tester can convenient one
Engine conditions are observed while adjusting engine speed in side, can so improve the security of test process.
In some embodiments, data collecting system includes atmospheric temperature acquisition system, oil inlet and outlet temperature
Acquisition system, engine cylinder head temperature acquisition system, atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure
Acquisition system, lubricating oil pressure acquisition system, rotating speed acquisition system, fuel flow acquisition system, each acquisition system is by the number of collection
According to being transmitted to industrial computer.
In some embodiments, atmospheric temperature acquisition system includes platinum resistance temperature sensor, the first power supply and the
One conditioning module, reflects the change of ambient temperature, the first power supply is electrically connected with the first conditioning module by the change in resistance of platinum resistance
Connect, for providing electric energy needed for atmospheric temperature acquisition system normal work, platinum resistance temperature sensor gathers the temperature number of air
According to by the temperature data of air after the first conditioning module is amplified and is filtered, exporting the current signal of 4-20mA, current signal
Pass through RS485 bus transfers to industrial computer.
In some embodiments, oil inlet and outlet temperature acquisition system and engine cylinder head temperature acquisition system
Including thermocouple temperature sensor, second source and the second conditioning module, second source is electrically connected with the second conditioning module, is used
In offer oil inlet and outlet temperature acquisition system and electric energy, heat needed for engine cylinder head temperature acquisition system normal work
Galvanic couple temperature sensor gathers oil inlet and outlet and the temperature data of engine cylinder head, by oil inlet and outlet and hair
The temperature data of engine cylinder head exports the current signal of 6-18mA, electric current letter after the second conditioning module is amplified and is filtered
Number pass through RS485 bus transfers to industrial computer.When thermocouple is that the conductor both ends of two kinds of different components are bonded into circuit, when
When abutment temperature is different, thermoelectrical potential will be produced in circuit, the electromotive force and the temperature value of measurement end that thermocouple produces have
Certain relational expression, electromotive force is raised and increased with the temperature of measurement end, so that the temperature at reaction test end.
In some embodiments, atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure acquisition system,
Lubricating oil pressure acquisition system includes pressure sensor, the 3rd power supply and the 3rd conditioning module, the 3rd power supply and the 3rd conditioning mould
Block is electrically connected, for providing atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure acquisition system and lubricating oil pressure
Electric energy needed for power acquisition system normal work, pressure sensor collection atmospheric pressure, admission pressure, fuel pressure and lubricating oil pressure
The pressure data of power, by the pressure data of atmospheric pressure, admission pressure, fuel pressure and lubricating oil pressure by the 3rd conditioning mould
After block amplifies and filters, the current signal of 5-15mA is exported, current signal passes through RS485 bus transfers to industrial computer.
In some embodiments, rotating speed acquisition system includes speed probe, the 4th power supply and the 4th conditioning module,
4th power supply is electrically connected with the 4th conditioning module, for providing electric energy needed for rotating speed acquisition system normal work, speed probe
The rotary speed data of engine is gathered, by the rotary speed data of engine after the 4th conditioning module is amplified and is filtered, exports 7-
The current signal of 18mA, current signal pass through RS485 bus transfers to industrial computer.Rotating speed is very heavy in aero-engine
The parameter wanted, the method for tachometric survey mainly has centrifugal machinery, hydraulic centrifugal formula, magnetoelectricity pulse in aero-engine
Several rotating speed measurement methods such as formula.Wherein magnetoelectricity pulsed because high certainty of measurement, stablize, and is obtained in aero-engine by output
It is widely applied, so detecting revolution speed of propeller using magneto-electric pulsed velocity sensor.
In some embodiments, fuel flow acquisition system includes flow sensor, the 5th power supply and the 5th conditioning
Module, the 5th power supply are electrically connected with the 5th conditioning module, for providing electric energy needed for fuel flow acquisition system normal work, stream
Quantity sensor gathers the fuel flow data of fuel service system, and the fuel flow data of fuel service system are adjusted by the 5th
After managing module amplification and filtering, the current signal of 5-15mA is exported, current signal is calculated by RS485 bus transfers to industry
Machine.
The present invention changes in the past by the mode of artificial detection engine performance, and solution is existing in the prior art to rely on people
Cycle needed for work test run is longer, labor intensity is larger, cost is higher, and manual testing can not substantially ensure that test run quality, flexibly
Property, reliability, expandability and economy are poor, it is impossible to the problem of meeting technology growth requirement.
Brief description of the drawings
Fig. 1 is the structure diagram of the piston aviation engine test bay of one embodiment of the present invention.
Embodiment
Below in conjunction with the accompanying drawings and specific embodiment the present invention is described in further detail explanation.
The present invention provides piston aviation engine test bay, as shown in Figure 1, including motor mounts 1, is installed on hair
Test engine 2 on motivation mounting bracket 1, test engine 2 are connected with propeller 3, and motor mounts 1 are equipped with supporting rod
4, supporting rod 4 is equipped with lifting gear, adjusts the terrain clearance of test engine 2, the motor mounts 1 and test bay
Main body 5 is connected, and test bay main body 5 includes test platform 53, test cell 51 and the lorry 52 for placing test cell 51, test run
Between 51 top be equipped with fuel tank 54, be additionally provided with observation window 55 and hatch door 56 on test cell 51.Domain is used as using lorry 52, it is mobile
Property good, convenience in transport and movement, supporting rod 4 is equipped with lifting gear, adjusts the terrain clearance of test engine 2, Ke Yifang
Just the testing requirement of all kinds of piston aviation engines is met.
Test platform 53 includes testboard and test system, and test system includes fuel system, control system, data acquisition
System, data handling system, power-supply system and industrial computer；
Fuel system is used to provide fuel oil needed for 2 test process of test engine；
Control system and fuel system, data collecting system, power-supply system, data handling system and industrial computer phase
Connection, for controlling whole test process；
Data collecting system includes multiple sensors, and sensor is arranged on test engine 2 and propeller 3, for adopting
Collect the data of test engine 2 and propeller 3 in operation, by data line transfer to data handling system；
Data handling system includes data storage module, data amplification module and data transmission module, and data preserve mould
Block is used to preserve the data that data collecting system transmission is come in, and work is transmitted to by data amplification module and data transmission module
Industry computer；
Power-supply system is used to provide the electric energy needed for whole test system work；
Industrial computer is used to handle data, the data after processing is preserved and including on industrial computer.By upper
The mutual cooperation of each system is stated, the testing requirement for meeting piston aviation engine is can be very good, substantially increases test
Accuracy, and test are comprehensive.
Fuel service system is used for the offer fuel oil to test engine 2, and fuel system includes AFS Auxiliary Fuel Supply System and master
Oil supply system, AFS Auxiliary Fuel Supply System use the pre- oiling of electric booster pump, and by the way of gravity feed oil, auxiliary supplies main oil supply system
Oil system carries out fuel feeding before test engine 2 starts to test engine 2, for the gas in discharge line, keeps oil circuit
It is unimpeded；Main oil supply system test engine 2 start and operational process in, fuel tank 54 by way of gravity feed oil to test
2 sustainable supply fuel oil of engine, ensures that test engine 2 runs well.Main oil supply system volume of fuel tank is 300L, in fuel oil
Float-type fuel quantity inductor is housed in case 54, Fuel Remained amount is shown in test run control interface by sensor, facilitates test run
Personnel grasp the excess oil situation in fuel tank 54, and fuel feeding can be greatly improved using AFS Auxiliary Fuel Supply System and main oil supply system
Efficiency.
Control system is equipped with throttle control hand lever and mixing ratio joystick, and throttle control hand lever is used to control test hair
The amount of fuel of motivation 2, and then the rotating speed of test engine 2 is controlled, mixing ratio joystick is used to control the poor of test engine 2
Rich oil.The manipulation and control of engine testsand, using the control mode similar with aircraft.Engine is only controlled in test
Rotating speed and mixing ratio, do not control the displacement of flight attitude and propeller 3.The constant pitch airscrew 3 of rated load is used in test,
It can so achieve the purpose that engine break-in, facilitate work-up the performance of engine, throttle control hand lever and mixing ratio control
The two joysticks of handle are installed on the master console of control room, and tester can be easily while observe engine feelings
Condition can so improve the security of test process while adjustment engine speed.
Data collecting system includes atmospheric temperature acquisition system, oil inlet and outlet temperature acquisition system, engine vapour
Head temperature acquisition system, atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure acquisition system, lubricating oil pressure
Acquisition system, rotating speed acquisition system, fuel flow acquisition system, each acquisition system calculate the data transfer of collection to industry
Machine.
Atmospheric temperature acquisition system includes platinum resistance temperature sensor, the first power supply and the first conditioning module, passes through platinum
The change of the change in resistance reflection ambient temperature of resistance, the first power supply is electrically connected with the first conditioning module, for providing big temperature
Electric energy needed for acquisition system normal work is spent, platinum resistance temperature sensor gathers the temperature data of air, by the temperature number of air
According to after the first conditioning module is amplified and is filtered, the current signal of 4-20mA is exported, current signal passes through RS485 bus transfers
To industrial computer.
Oil inlet is passed with outlet temperature acquisition system with engine cylinder head temperature acquisition system including electric thermo-couple temperature
Sensor, second source and the second conditioning module, second source are electrically connected with the second conditioning module, for provide oil inlet with
Outlet temperature acquisition system is adopted with electric energy, thermocouple temperature sensor needed for engine cylinder head temperature acquisition system normal work
Collect oil inlet and outlet and the temperature data of engine cylinder head, by oil inlet and outlet and the temperature of engine cylinder head
Data export the current signal of 6-18mA after the second conditioning module is amplified and is filtered, and current signal is passed by RS485 buses
Transport to industrial computer.When thermocouple is that the conductor both ends of two kinds of different components are bonded into circuit, when abutment temperature is different,
Thermoelectrical potential will be produced in circuit, the electromotive force and the temperature value of measurement end that thermocouple produces have certain relational expression, electronic
Gesture is raised and increased with the temperature of measurement end, so that the temperature at reaction test end.
Atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure acquisition system, lubricating oil pressure acquisition system bag
Pressure sensor, the 3rd power supply and the 3rd conditioning module are included, the 3rd power supply is electrically connected with the 3rd conditioning module, big for providing
Atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure acquisition system and lubricating oil pressure acquisition system normal work
Required electric energy, pressure sensor gather the pressure data of atmospheric pressure, admission pressure, fuel pressure and lubricating oil pressure, will be big
Atmospheric pressure, admission pressure, the pressure data of fuel pressure and lubricating oil pressure are defeated after the 3rd conditioning module is amplified and is filtered
Go out the current signal of 5-15mA, current signal passes through RS485 bus transfers to industrial computer.
Rotating speed acquisition system includes speed probe, the 4th power supply and the 4th conditioning module, and the 4th power supply and the 4th adjust
Manage module to be electrically connected, for providing electric energy needed for rotating speed acquisition system normal work, speed probe gathers the rotating speed of engine
Data, by the rotary speed data of engine after the 4th conditioning module is amplified and is filtered, export the current signal of 7-18mA, electric current
Signal passes through RS485 bus transfers to industrial computer.Rotating speed is a very important parameter in aero-engine, in aviation
The method of tachometric survey mainly has several tachometric survey sides such as centrifugal machinery, hydraulic centrifugal formula, magnetoelectricity pulsed in engine
Method.Wherein magnetoelectricity pulsed because high certainty of measurement, stablize, and is had been widely used in aero-engine by output, so
3 rotating speed of propeller is detected using magneto-electric pulsed velocity sensor.
Fuel flow acquisition system includes flow sensor, the 5th power supply and the 5th conditioning module, the 5th power supply and
Five conditioning modules are electrically connected, for providing electric energy needed for fuel flow acquisition system normal work, flow sensor collection fuel oil
The fuel flow data of supply system, the fuel flow data of fuel service system are amplified and filtered by the 5th conditioning module
Afterwards, the current signal of 5-15mA is exported, current signal passes through RS485 bus transfers to industrial computer.
The basic function of test system seeks to the requirement for meeting piston-mode motor test run outline, and complete coupled engines is each
The measurement of item parameter, these parameters include:Cylinder-Head Temperature, oil temperature, lubricating oil pressure, rotating speed, fuel flow, fuel oil pressure
Multiple measurement parameters such as power, atmospheric temperature, atmospheric pressure, engine charge pressure, amount of fuel.
The system can also can be pocessed and preserve, print to the related data in commissioning process while test, with
Realize " with no paper " of trial run work.It can be shown by upper industrial personal computer and supporting data processing software, print various charts.
Facilitate the analysis and maintenance in later stage.
Piston aviation engine test bay operating instruction is as follows：
Every time before use, check fuel tank 54 be grounded whether reliably, be connected securely to ground stud；
Every time before use, checking accumulator electrolyte height whether between minimum liquid level and highest liquid level；
Every time before use, checking the state of each test point sensor erection joint, cleaning no-sundries and corrosion should be kept；
, should be correct every time before use, the function of each electric switch should be checked；
, should intact, flawless, no significant defect every time before use, the state of engine connection bolt should be checked；It is periodically right
Bolt carries out magnetic particle testing, replaces the bolt for having crackle in time；
Every time before use, catch, the position of leveling installation frame should have been kept off, and lock；
Test engine 2 is installed on test bay mounting bracket 1, passes through the ground of engine mounting bracket supported underneath bar 4
Lock adjusts Support Position, is connected all the sensors with Engine Block Test interface after supporting to place；Connect all ground cables；Connect
Logical test bay general supply and starter start storage battery, and opening operation platform total power switch is powered to sensor and acquisition system, stepped on
Enter test interface after the acquisition system calibration system of land；
Open fuel system control valve and give whole fuel pipe fuel feeding；
Check that all preparations prepare startup engine and tested in place；
Throttle lever is placed in 1/4 position, mixing ratio bar is placed in FULL positions, presses starter button, should be opened in 10 seconds
Dynamic engine, the stopping startup of starter button should be unclamped more than 10 seconds prevents damage starter；
After engine start and normal work, provide to be detected the parameters of engine according to handbook.
The present invention changes in the past by the mode of artificial detection engine performance, and solution is existing in the prior art to rely on people
Cycle needed for work test run is longer, labor intensity is larger, cost is higher, and manual testing can not substantially ensure that test run quality, flexibly
Property, reliability, expandability and economy are poor, it is impossible to the problem of meeting technology growth requirement.Utilize the present invention, Ke Yiji
Mitigate cost of labor in big degree, accuracy rate is high, conveniently moving, is adapted to various field tests to use.
The above is only the preferred embodiment of the present invention, it is noted that to those skilled in the art, not
On the premise of departing from the invention design, some similar modification and improvement can also be made, these also should be regarded as the present invention
Protection domain within.
Claims (1)
1. piston aviation engine test bay, it is characterised in that including motor mounts (1), be installed on the engine
Test engine (2) on mounting bracket (1), the test engine (2) are connected with propeller (3), the motor mounts
(1) supporting rod (4) is equipped with, the supporting rod (4) is equipped with lifting gear, adjusts the liftoff of the test engine (2)
Highly, the motor mounts (1) are connected with test bay main body (5), and the test bay main body (5) includes test platform
(53), test cell (51) and the lorry (52) for placing the test cell (51), test cell (51) top are equipped with combustion
Fuel tank (54), observation window (55) and hatch door (56) are additionally provided with the test cell (51), and the test platform (53) includes test
Platform and test system, the test system include fuel service system, control system, data collecting system, data handling system,
Power-supply system and industrial computer；
The fuel service system is used to provide fuel oil needed for the test engine (2) test process；
The control system and the fuel service system, data collecting system, power-supply system, data handling system and industry
Computer is connected, for controlling whole test process；
The data collecting system includes multiple sensors, and the sensor is arranged on the test engine (2) and the spiral shell
Revolve on paddle (3), for gathering the data of the test engine (2) and the propeller (3) in operation, pass through data cable
It is transferred to the data handling system；
The data handling system includes data storage module, data amplification module and data transmission module, and the data are protected
Storing module is used to preserve the data that the data collecting system transmission is come in, and passes through data amplification module and data transmission module
It is transmitted to industrial computer；
The power-supply system is used to provide the electric energy needed for whole test system work；
The industrial computer is used to handle data, the data after processing is preserved and including on industrial computer；
The fuel service system is used to provide the test engine (2) fuel oil, and the fuel service system includes auxiliary
Oil supply system and main oil supply system, the AFS Auxiliary Fuel Supply System use the pre- oiling of electric booster pump, and the main oil supply system uses
The mode of gravity feed oil, the AFS Auxiliary Fuel Supply System the test engine (2) start before to the test engine (2) into
Row fuel feeding, for the gas in discharge line, keeps oil circuit unimpeded；The main oil supply system is opened in the test engine (2)
In dynamic and operational process, the fuel tank (54) fires the test engine (2) sustainable supply by way of gravity feed oil
Oil, ensures that the test engine (2) runs well, and the control system is equipped with throttle control hand lever and mixing ratio control hand
Handle, the throttle control hand lever is used for the amount of fuel for controlling the test engine (2), and then controls the test engine
(2) rotating speed, the mixing ratio joystick are used for the lean and fat oil for controlling the test engine (2), the data acquisition system
System include atmospheric temperature acquisition system, oil inlet and outlet temperature acquisition system, engine cylinder head temperature acquisition system, greatly
Atmospheric pressure acquisition system, admission pressure acquisition system, fuel pressure acquisition system, lubricating oil pressure acquisition system, rotating speed collection system
System, fuel flow acquisition system, each acquisition system adopt the data transfer of collection to the industrial computer, the atmospheric temperature
Collecting system includes platinum resistance temperature sensor, the first power supply and the first conditioning module, and first power supply is adjusted with described first
Manage module to be electrically connected, for providing electric energy needed for the atmospheric temperature acquisition system normal work, the platinum resistance temperature sensing
Device gathers the temperature data of air, defeated by the temperature data of the air after first conditioning module is amplified and is filtered
Go out the current signal of 4-20mA, the current signal passes through RS485 bus transfers to the industrial computer, the oil inlet
Include thermocouple temperature sensor, second source with outlet temperature acquisition system and the engine cylinder head temperature acquisition system
And second conditioning module, the second source are electrically connected with second conditioning module, for provide the oil inlet with
Outlet temperature acquisition system and electric energy, the electric thermo-couple temperature needed for engine cylinder head temperature acquisition system normal work
Sensor gathers oil inlet and outlet and the temperature data of engine cylinder head, by the oil inlet and outlet and engine
The temperature data of cylinder head exports the current signal of 6-18mA, the electricity after second conditioning module is amplified and is filtered
Flow signal and pass through RS485 bus transfers to the industrial computer, the atmospheric pressure acquisition system, admission pressure collection
System, the fuel pressure acquisition system, the lubricating oil pressure acquisition system include pressure sensor, the 3rd power supply and the 3rd
Conditioning module, the 3rd power supply are electrically connected with the 3rd conditioning module, for providing the atmospheric pressure acquisition system, institute
State admission pressure acquisition system, the fuel pressure acquisition system and electricity needed for lubricating oil pressure acquisition system normal work
Can, the pressure sensor gathers the pressure data of atmospheric pressure, admission pressure, fuel pressure and lubricating oil pressure, by described in
Atmospheric pressure, admission pressure, the pressure data of fuel pressure and lubricating oil pressure amplify and filter by the 3rd conditioning module
After ripple, export the current signal of 5-15mA, the current signal by RS485 bus transfers to the industrial computer, it is described
Rotating speed acquisition system includes speed probe, the 4th power supply and the 4th conditioning module, and the 4th power supply is adjusted with the described 4th
Manage module to be electrically connected, for providing electric energy needed for the rotating speed acquisition system normal work, the speed probe collection is started
The rotary speed data of machine, by the rotary speed data of the engine after the 4th conditioning module is amplified and is filtered, exports 7-
The current signal of 18mA, the current signal pass through RS485 bus transfers to the industrial computer, the fuel flow collection
System includes flow sensor, the 5th power supply and the 5th conditioning module, the 5th power supply and the 5th conditioning module electricity
Connection, for providing electric energy needed for the fuel flow acquisition system normal work, the flow sensor gathers fuel supply
The fuel flow data of system, by the fuel flow data of the fuel service system by the 5th conditioning module amplification and
After filtering, the current signal of 5-15mA is exported, the current signal passes through RS485 bus transfers to the industrial computer.
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| CN201510846701.1A CN105241668B (en) | 2015-11-28 | 2015-11-28 | Piston aviation engine test bay |
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| CN106514142B (en) * | 2016-11-07 | 2018-11-30 | 沈阳航天新光集团有限公司 | The manufacturing method of simulator stand stratochamber |
| CN106989927B (en) * | 2016-12-21 | 2019-03-01 | 中国燃气涡轮研究院 | A kind of engine installation automatization process based on suspension type ground test stand |
| CN106840683B (en) * | 2017-04-01 | 2023-12-19 | 昆山航理机载设备股份有限公司 | Aviation turboshaft engine test bed |
| CN109115506B (en) * | 2018-10-05 | 2020-06-19 | 北京航天三发高科技有限公司 | Use method of air inlet system of engine test bed |
| CN112595517A (en) * | 2020-11-12 | 2021-04-02 | 西安爱生技术集团公司 | Unmanned aerial vehicle piston engine test bed frame with clutch and method |
| CN117367810B (en) * | 2023-12-07 | 2024-03-08 | 保定市玄云涡喷动力设备研发有限公司 | Integrated test bench for aero-engine |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1195593A1 (en) * | 2000-10-05 | 2002-04-10 | Techspace Aero S.A. | Test installation for testing aircraft engines |
| CN101701874A (en) * | 2009-10-29 | 2010-05-05 | 西安西航集团航空航天地面设备有限公司 | Mobile test bed system for test run in external field |
| CN201666850U (en) * | 2009-12-29 | 2010-12-08 | 成都飞机设计研究所 | Model airplane engine test stand |
| CN102507204A (en) * | 2011-11-18 | 2012-06-20 | 北京航空航天大学 | Movable micro turbine jet engine test bed |
| CN202693314U (en) * | 2012-06-15 | 2013-01-23 | 北京中陆航星机械动力科技有限公司 | Turbojet engine test bed |
| CN202928799U (en) * | 2012-10-12 | 2013-05-08 | 成都赛腾自动化工程有限公司 | Engine comprehensive parameters detection system used for performance analysis |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN104198190A (en) * | 2014-09-11 | 2014-12-10 | 中国人民解放军海军航空工程学院青岛校区 | Aero-engine comprehensive testing system |
| CN204085892U (en) * | 2014-02-18 | 2015-01-07 | 中国人民解放军总参谋部陆航研究所 | The data monitoring device of portable turboshaft engine test bay |
| CN204286804U (en) * | 2014-12-08 | 2015-04-22 | 中国航天空气动力技术研究院 | A kind of turbo oar engine ground run bench frame apparatus |
| CN204758298U (en) * | 2015-07-19 | 2015-11-11 | 中国人民解放军空军第一航空学院 | Engine test bed |
-
2015
- 2015-11-28 CN CN201510846701.1A patent/CN105241668B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1195593A1 (en) * | 2000-10-05 | 2002-04-10 | Techspace Aero S.A. | Test installation for testing aircraft engines |
| CN101701874A (en) * | 2009-10-29 | 2010-05-05 | 西安西航集团航空航天地面设备有限公司 | Mobile test bed system for test run in external field |
| CN201666850U (en) * | 2009-12-29 | 2010-12-08 | 成都飞机设计研究所 | Model airplane engine test stand |
| CN102507204A (en) * | 2011-11-18 | 2012-06-20 | 北京航空航天大学 | Movable micro turbine jet engine test bed |
| CN202693314U (en) * | 2012-06-15 | 2013-01-23 | 北京中陆航星机械动力科技有限公司 | Turbojet engine test bed |
| CN202928799U (en) * | 2012-10-12 | 2013-05-08 | 成都赛腾自动化工程有限公司 | Engine comprehensive parameters detection system used for performance analysis |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN204085892U (en) * | 2014-02-18 | 2015-01-07 | 中国人民解放军总参谋部陆航研究所 | The data monitoring device of portable turboshaft engine test bay |
| CN104198190A (en) * | 2014-09-11 | 2014-12-10 | 中国人民解放军海军航空工程学院青岛校区 | Aero-engine comprehensive testing system |
| CN204286804U (en) * | 2014-12-08 | 2015-04-22 | 中国航天空气动力技术研究院 | A kind of turbo oar engine ground run bench frame apparatus |
| CN204758298U (en) * | 2015-07-19 | 2015-11-11 | 中国人民解放军空军第一航空学院 | Engine test bed |
Non-Patent Citations (1)
| Title |
|---|
| 航空活塞发动机试车台设计及测试系统开发;麦海波;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20120315(第3期);C031-114-1-36 * |
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Denomination of invention: Piston type aero-engine test stand Effective date of registration: 20200722 Granted publication date: 20180508 Pledgee: Nantong Jiangsu rural commercial bank Limited by Share Ltd. Pledgor: CHINA AIRCRAFT MAINTENANCE & ENGINEERING Co.,Ltd. Registration number: Y2020980004277 |
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