CN206270470U - A kind of aircraft starter-generator testboard - Google Patents
A kind of aircraft starter-generator testboard Download PDFInfo
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- CN206270470U CN206270470U CN201621346655.5U CN201621346655U CN206270470U CN 206270470 U CN206270470 U CN 206270470U CN 201621346655 U CN201621346655 U CN 201621346655U CN 206270470 U CN206270470 U CN 206270470U
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- aircraft starter
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Abstract
The utility model is related to a kind of aircraft starter-generator testboard, startup power test cell, including is separately positioned on torque speed sensor and electric eddy current brake in aircraft starter-generator rotating shaft to be measured；Generated output test cell, load resistance box and electrodeless regulating load motor including being connected in parallel on aircraft starter-generator carbon plate pressure regulator two ends to be measured, the first ammeter being connected on aircraft generator output loop to be measured and the voltmeter for being connected in parallel on aircraft starter-generator carbon plate pressure regulator two ends to be measured, are connected on the second ammeter on loop where electrodeless regulating load motor；Control display unit, including controller and control display panel, wherein, the input of controller is connected with torque speed sensor and electric eddy current brake, and output end is connected with the drive circuit of aircraft generator to be measured and the drive circuit of electrodeless regulating load motor.By the technical solution of the utility model, can improve aircraft starter-generator start test set and generating test equipment integrated level.
Description
Technical field
The utility model is related to aircraft starter-generator automatization testing technique field, and in particular to a kind of aircraft starts hair
Electromechanical testing platform.
Background technology
Aircraft maintenance unit needs periodically carry out performance test to the starter-generator of aircraft on ground, before installation really
Fixed its state quality.The performance test includes starting state performance test and generating state performance test.The startup of legacy equipment
State verification and generating state test are two equipment, and level of integrated system is poor, safeguard that unit needs to carry two equipment during test,
Hand labor intensity is big, and is not easy to the use management of equipment.
Utility model content
In view of this, the purpose of this utility model is to overcome the deficiencies in the prior art, there is provided a kind of aircraft starts generating
Machine testboard, with improve aircraft starter-generator start test set and generating test equipment integrated level.
To realize object above, the utility model is adopted the following technical scheme that：
A kind of aircraft starter-generator testboard, including：
Startup power test cell, including：The moment of torsion rotating speed being separately positioned in aircraft starter-generator rotating shaft to be measured is passed
Sensor and electric eddy current brake；
Generated output test cell, including：It is connected in parallel on the load electricity at aircraft starter-generator carbon plate pressure regulator two ends to be measured
Resistance case and electrodeless regulating load motor, the first ammeter being connected on aircraft generator output loop to be measured and be connected in parallel on it is to be measured
The voltmeter at aircraft starter-generator carbon plate pressure regulator two ends, is connected on loop where the electrodeless regulating load motor the
Two ammeters, wherein, the load resistance box is used to shunt the output current of aircraft starter-generator to be measured, the nothing
Regulating load motor in pole is used to carry out shunting fine setting to the output current of aircraft starter-generator to be measured；
Control display unit, including：Controller and the control display panel being connected with the controller, wherein, the control
The input of device processed is connected with the torque speed sensor and electric eddy current brake, output end respectively with aircraft generator to be measured
Drive circuit and the electrodeless regulating load motor drive circuit connection；
Power supply unit, including：0~30V continuously adjustabes voltage-stabilized power supply and high-speed induction motor, wherein, described 0~
The external 380V industrial powers of 30V continuously adjustabe voltage-stabilized power supplies, for being powered for the startup power test cell；The high speed becomes
Frequency motor is used to provide power for aircraft starter-generator to be measured.
Preferably, it is provided with the control display panel and is surveyed with the startup power test cell, generated output respectively
The button module of the drive circuit connection of examination unit, power supply unit and aircraft starter-generator to be measured, the button module
Including multiple control buttons.
Preferably, it is additionally provided with the touch-screen being connected with the controller on the control display panel.
Preferably, the load resistance box and electrodeless regulating load motor pass through 125mm2High flexible cable is connected in parallel on to be measured flying
Machine starter-generator carbon plate pressure regulator two ends.
Preferably, 0~30V continuously adjustabes voltage-stabilized power supply output 28V direct currents are aircraft starter-generator to be measured confession
Electricity.
Preferably, 0~30V continuously adjustabes voltage-stabilized power supply passes through 125mm2High flexible cable is that aircraft to be measured starts generating
Machine is powered.
Preferably, the rated power of 0~30V continuously adjustabes voltage-stabilized power supply and high-speed induction motor is all 40kVA.
Preferably, the torque speed sensor uses crystallite variable torque sensor.
The utility model uses above technical scheme, at least possesses following beneficial effect：
The aircraft starter-generator testboard that the utility model is provided, controller is according to moment of torsion in generated output test cell
Speed probe and electric eddy current brake output signal, the various performance parameters for calculating aircraft starter-generator to be measured (for example turn
Speed, torque and power etc.), and the performance parameter that will be calculated enters with the parameter of dispatching from the factory corresponding to aircraft starter-generator to be measured
Whether row is compared, good with the startability for judging starter-generator, so as to realize the startup to aircraft starter-generator to be measured
Performance test.
In addition, user can be by controlling display panel and being sent out to aircraft to be measured with the controller for controlling display panel to be connected
The drive circuit conveying control instruction of motor, so that aircraft generator to be measured is generated electricity, and by the first ammeter, the second electricity
Flow table and voltmeter observe the voltage and current size of aircraft generator output to be measured, so as to realize starting aircraft to be measured generate electricity
The power generation performance test of machine.
Compared to existing technology, the utility model provide this aircraft starter-generator testboard by startability test and
Power generation performance test is integrated, and improves the integrated level of equipment, facilitates user to carry, further, since the external line of equipment
It is few, facilitate user to use management and maintenance management to equipment.
Brief description of the drawings
In order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or the accompanying drawing to be used needed for description of the prior art is briefly described, it should be apparent that, drawings in the following description are only
It is some embodiments of the present utility model, for those of ordinary skill in the art, is not paying the premise of creative work
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
The schematic block diagram of the aircraft starter-generator testboard that Fig. 1 is provided for the embodiment of the utility model one.
Specific embodiment
To make the purpose of this utility model, technical scheme and advantage clearer, below will be to technology of the present utility model
Scheme is described in detail.Obviously, described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not before creative work is made
Resulting all other implementation method is put, the scope that the utility model is protected is belonged to.
Below by drawings and Examples, the technical solution of the utility model is described in further detail.
Referring to a kind of aircraft starter-generator testboard that Fig. 1, the embodiment of the utility model one are provided, including：
Startup power test cell 1, including：The moment of torsion rotating speed being separately positioned in aircraft starter-generator rotating shaft to be measured is passed
Sensor 11 and electric eddy current brake 12；
Generated output test cell 2, including：It is connected in parallel on the load electricity at aircraft starter-generator carbon plate pressure regulator two ends to be measured
Resistance case 21 and electrodeless regulating load motor 22, are connected on the first ammeter 23 and parallel connection on aircraft generator output loop to be measured
In the voltmeter 24 at aircraft starter-generator carbon plate pressure regulator two ends to be measured, it is connected on where the electrodeless regulating load motor 22
The second ammeter 25 on loop, wherein, the load resistance box 21 is used for the output current to aircraft starter-generator to be measured
Shunted, it is micro- that the electrodeless regulating load motor 22 carries out shunting for the output current to aircraft starter-generator to be measured
Adjust；
Control display unit 3, including：Controller 31 and the control display panel 32 being connected with the controller 31, wherein,
The input of the controller 31 is connected with the torque speed sensor 11 and electric eddy current brake 12, output end respectively with treat
Survey the drive circuit connection of the drive circuit and the electrodeless regulating load motor of aircraft generator；
Power supply unit 4, including：0~30V continuously adjustabes voltage-stabilized power supply 41 and high-speed induction motor 42, wherein, it is described
The external 380V industrial powers of 0~30V continuously adjustabes voltage-stabilized power supply 41, for being powered for the startup power test cell 1；It is described
High-speed induction motor 42 is used to provide power for aircraft starter-generator to be measured.
It is understood that being shunted using load resistance box, electrodeless regulating load motor is to aircraft starter-generator to be measured
Output current carry out shunting fine setting, advantage is to produce additional heat few, and dump power is big, makes parts life-span long, working stability,
Measuring accuracy is high.
It is understood that electric eddy current brake is compared to traditional magnetic powder brake, and its advantage is：Working speed is high, saves
Decelerator has been removed, the vibrations and noise produced by decelerator have been reduced, structure has been simplified, job stability has been improve.The electric whirlpool
Stream brake rating torque 400N.m, maximum speed can reach 9000r/min, also for the measurement of other models leave it is remaining
Amount.
Electric eddy current brake be the principle using eddy-current loss come absorbed power, be that aircraft starter-generator to be measured applies
Specified opposing torque and reach the change of power consumption.By electric eddy current brake, controller and sensor group into complete measurement of power,
The output torque and rotating speed for being tested machinery can be measured, so as to draw power.
It is understood that the aircraft starter-generator testboard that the utility model is provided, controller is according to generated output
Torque speed sensor and electric eddy current brake output signal in test cell, calculate the various property of aircraft starter-generator to be measured
Energy parameter (such as rotating speed, torque and power etc.), and the performance parameter that will be calculated is right with aircraft starter-generator to be measured institute
Whether the parameter of dispatching from the factory answered is compared, good with the startability for judging starter-generator, so as to realize opening aircraft to be measured
The startability test of dynamic generator.
In addition, user can be by controlling display panel and being sent out to aircraft to be measured with the controller for controlling display panel to be connected
The drive circuit conveying control instruction of motor, so that aircraft generator to be measured is generated electricity, and by the first ammeter, the second electricity
Flow table and voltmeter observe the voltage and current size of aircraft generator output to be measured, so as to realize starting aircraft to be measured generate electricity
The power generation performance test of machine.
Compared to existing technology, the utility model provide this aircraft starter-generator testboard by startability test and
Power generation performance test is integrated, and improves the integrated level of equipment, facilitates user to carry, further, since the external line of equipment
It is few, facilitate user to use management and maintenance management to equipment.
Preferably, it is described control display panel 32 on be provided with respectively with the startup power test cell 1, generated output
The button module of the drive circuit connection of test cell 2, power supply unit 4 and aircraft starter-generator to be measured, the button
Module includes multiple control buttons.
It is understood that in order to preferably extend this aircraft starter-generator testboard that the utility model is provided
Reliability, control display unit is divided into manual control and computer monitoring two ways is available, and operating personnel can be with root
According to oneself use habit start and power generation performance is tested, two ways is separate, and one way in which breaks down another
A kind of outer mode still can normal work.Control directly perceived, reliability high manually；Computer monitoring mode is simple, intelligence.
Preferably, it is additionally provided with the touch-screen being connected with the controller 31 on the control display panel 32.
Preferably, the load resistance box 21 and electrodeless regulating load motor 22 pass through 125mm2High flexible cable is connected in parallel on to be treated
Survey aircraft starter-generator carbon plate pressure regulator two ends.
Preferably, the output 28V of 0~30V continuously adjustabes voltage-stabilized power supply 41 direct currents are aircraft starter-generator to be measured
Power supply.
Preferably, 0~30V continuously adjustabes voltage-stabilized power supply 41 passes through 125mm2High flexible cable is that aircraft to be measured starts hair
Motor is powered.
Preferably, the rated power of 0~30V continuously adjustabes voltage-stabilized power supply 41 and high-speed induction motor 42 is all
40kVA。
Preferably, the torque speed sensor 11 uses crystallite variable torque sensor.
It is understood that torque speed sensor uses crystallite variable torque sensor, compared to traditional phase difference
Torque speed sensor measurement range is wider, and structure is more simple.The transmission of the sensor energy and signal all employs non-connecing
The mode of touching, sensor bearing uses high-speed bearing, is adapted to for a long time, rotation speed operation high, peak torque：400N.m, it is maximum
Rotating speed：10000r/min, precision is 0.5%F.S；Be similarly extension other models leave enough surpluses.(aircraft to be measured starts hair
Rated motor load torque 156.8N.m, maximum (top) speed 9000r/min).
The above, specific embodiment only of the present utility model, but protection domain of the present utility model do not limit to
In this, any one skilled in the art can readily occur in change in the technical scope that the utility model is disclosed
Or replace, should all cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with the power
The protection domain that profit is required is defined.Term " first ", " second " are only used for describing purpose, and it is not intended that indicating or implying phase
To importance.Term " multiple " refers to two or more, unless otherwise clearly restriction.
Claims (8)
1. a kind of aircraft starter-generator testboard, it is characterised in that including：
Startup power test cell, including：It is separately positioned on the torque speed sensor in aircraft starter-generator rotating shaft to be measured
And electric eddy current brake；
Generated output test cell, including：It is connected in parallel on the load resistance box at aircraft starter-generator carbon plate pressure regulator two ends to be measured
With electrodeless regulating load motor, the first ammeter being connected on aircraft generator output loop to be measured and aircraft to be measured is connected in parallel on
The voltmeter at starter-generator carbon plate pressure regulator two ends, is connected on the second electricity on loop where the electrodeless regulating load motor
Flow table, wherein, the load resistance box is used to shunt the output current of aircraft starter-generator to be measured, the electrodeless tune
Section load motor is used to carry out shunting fine setting to the output current of aircraft starter-generator to be measured；
Control display unit, including：Controller and the control display panel being connected with the controller, wherein, the controller
Input be connected with the torque speed sensor and electric eddy current brake, output end respectively with the drive of aircraft generator to be measured
The drive circuit connection of dynamic circuit and the electrodeless regulating load motor；
Power supply unit, including：0~30V continuously adjustabes voltage-stabilized power supply and high-speed induction motor, wherein, the 0~30V connects
The external 380V industrial powers of continuous adjustable stabilized voltage supply, for being powered for the startup power test cell；The high speed variable-frequency electric
Machine is used to provide power for aircraft starter-generator to be measured.
2. aircraft starter-generator testboard according to claim 1, it is characterised in that set on the control display panel
It is equipped with to start with the startup power test cell, generated output test cell, power supply unit and aircraft to be measured respectively and sends out
The button module of the drive circuit connection of motor, the button module includes multiple control buttons.
3. aircraft starter-generator testboard according to claim 2, is additionally provided with and institute on the control display panel
State the touch-screen of controller connection.
4. aircraft starter-generator testboard according to claim 1, it is characterised in that the load resistance box and electrodeless
Regulating load motor passes through 125mm2High flexible cable is connected in parallel on aircraft starter-generator carbon plate pressure regulator two ends to be measured.
5. aircraft starter-generator testboard according to claim 1, it is characterised in that 0~30V continuously adjustabes are steady
Voltage source exports 28V direct currents for aircraft starter-generator to be measured is powered.
6. aircraft starter-generator testboard according to claim 5, it is characterised in that 0~30V continuously adjustabes are steady
Voltage source passes through 125mm2High flexible cable is powered for aircraft starter-generator to be measured.
7. the aircraft starter-generator testboard according to any one of claim 1~6, it is characterised in that the 0~30V
The rated power of continuously adjustabe voltage-stabilized power supply and high-speed induction motor is all 40kVA.
8. the aircraft starter-generator testboard according to any one of claim 1~6, it is characterised in that the torque axis
Fast sensor uses crystallite variable torque sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621346655.5U CN206270470U (en) | 2016-12-08 | 2016-12-08 | A kind of aircraft starter-generator testboard |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621346655.5U CN206270470U (en) | 2016-12-08 | 2016-12-08 | A kind of aircraft starter-generator testboard |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206270470U true CN206270470U (en) | 2017-06-20 |
Family
ID=59044833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621346655.5U Active CN206270470U (en) | 2016-12-08 | 2016-12-08 | A kind of aircraft starter-generator testboard |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206270470U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109188270A (en) * | 2018-08-02 | 2019-01-11 | 沈阳工程学院 | A kind of main driving magneto performance test feedback system of electric airplane |
| CN109342945A (en) * | 2018-11-22 | 2019-02-15 | 武汉市恒信泰采油设备制造有限公司 | A kind of motor rapid detection system |
-
2016
- 2016-12-08 CN CN201621346655.5U patent/CN206270470U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109188270A (en) * | 2018-08-02 | 2019-01-11 | 沈阳工程学院 | A kind of main driving magneto performance test feedback system of electric airplane |
| CN109342945A (en) * | 2018-11-22 | 2019-02-15 | 武汉市恒信泰采油设备制造有限公司 | A kind of motor rapid detection system |
| CN109342945B (en) * | 2018-11-22 | 2023-11-10 | 武汉市恒信泰采油设备制造有限公司 | Motor rapid detection system |
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