CN202177688U - Integrated test system for airplane electric accessory motor-type test - Google Patents
Integrated test system for airplane electric accessory motor-type test Download PDFInfo
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- CN202177688U CN202177688U CN201120226298XU CN201120226298U CN202177688U CN 202177688 U CN202177688 U CN 202177688U CN 201120226298X U CN201120226298X U CN 201120226298XU CN 201120226298 U CN201120226298 U CN 201120226298U CN 202177688 U CN202177688 U CN 202177688U
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Abstract
The utility model discloses an integrated test system for an airplane electric accessory motor-type test, which comprises an alternating current parameter measurement circuit, a control circuit, a direct current parameter measurement circuit, a direct current parameter measurement control circuit and a dynamometer main circuit. The integrated test system integrates tests of direct current no-load, alternating current no-load, direct current load and alternating current load of a motor, has functions of a low speed high torque type test and a high speed low torque type test, is fast in speed, high in accuracy, convenient to use and good in reliability, and completely accords with technical requirements of an integrated test for the airplane electric accessory motor-type test.
Description
Technical field
The utility model relates to a kind of test system, particularly a kind of integrated test system of aircraft electric attachments electrical type tests.
Background technology
Motor in the aircraft uses widely in the electric attachments drive system, comprises AC and DC drive unit, rotary actuator, actuating motor etc.So aviation annex maintenance industry is badly in need of a kind of excellent in design, easy to operate, comprehensive degree is high, is used for the property test platform of aircraft accessory machinery check and repair front and back.
For common electrical type tests test macro: by trial product being the rotation of prime motive power drives torque rotary speed sensor, sensor and load generator connection are as load.When being turned round, do not give generator excitatory by trial product, the mechanical friction moment when at this moment being added in moment of torsion on the sensor and being generator idle running, this moment is very little, can through with the supporting torque gauge zeroing deduction of sensor.Just generating thereupon of generator when giving generator excitatory, this electric energy will be consumed by the electric heater of load water tank.We just can reach adjusting by the output torque of trial product through the excitatory size of regulating Dyn. like this, the size of moment of torsion reach at that time rotating speed, power will with the supporting torque gauge of sensor on show.
But there is following shortcoming in system at present: the wheeled kind of drive of (1) belt makes that the whole test platform has serious vibration when big moment or high rotating speed, produces sizable noise, causes experimental enviroment quite abominable in the use; (2) often be high rotating speed by trial product, so two matching used wheels have sizable gap dimensionally, bull wheel has very big swing when rotated, brings very big potential safety hazard easily; (3) loading method is the excitatory of regulator generator; Excitatory variation must bring the load generator change in rotational speed, loads moment of torsion for like this adjusting and brings very big difficulty, is not easy to make load to be stabilized in a point; The test figure accuracy that is produced can reduce, even does not have accuracy and can say; (4) testing range is to the restriction of new product.
The utility model content
The utility model technical matters to be solved provides the test that a kind of direct current of integrated motor is unloaded, exchange zero load, DC load, AC load, possesses the test macro of the function of the little moment of torsion type approval test of low-speed big type approval test and high speed.
In order to solve above-mentioned technical matters, the technical scheme of the utility model is: a kind of integrated test system that is used for aircraft electric attachments electrical type tests, and it comprises:
-AC parameter measuring circuit: first experiment power supply is connected with AC parameter measuring instrument through air switch QF1, A.C. contactor KM5 normally opened contact; Second experiment power supply is connected with AC parameter measuring instrument through A.C. contactor KM6 normally opened contact, A.C. contactor KM7 normally opened contact respectively, and A.C. contactor KM6 normally opened contact is parallelly connected with A.C. contactor KM7 normally opened contact;
-control circuit: power circuit is with power switch SK1, emergency stop switch SE1 and the series connection of sub-control circuit; Said sub-control circuit is supplied control circuit, is stopped control circuit and the positive and reverse rotation control circuit parallel connection constitutes by experiment power supply; Normally closed push button switch SB1, normally open push button switch SB2, two grades of switch SA2 series connection constitute experiment power supply supply control circuit; Two grades of switch SA2 are connected with signal lamp HR4, signal lamp HR5 respectively, normally open push button switch SB2, signal lamp HR5 respectively with A.C. contactor KM5 normally opened contact, A.C. contactor KM5 coils from parallel connection of coils; Normally closed push button switch SB3, normally open push button switch SB4 and the series connection of A.C. contactor KM8 coil, normally open push button switch SB4 is parallelly connected with A.C. contactor KM8 normally opened contact; Two grades of switch SA4 connect and compose positive and reverse rotation control circuit with A.C. contactor KM6 coil, A.C. contactor KM7 coil respectively, and A.C. contactor KM6 coil, A.C. contactor KM7 coil are parallelly connected with signal lamp HR6, signal lamp HR7 respectively;
-DC parameter metering circuit: first shunt, second shunt, the 3rd shunt are connected with the DC parameter measuring instrument through switch KA1, switch KA2, switch KA3 respectively; Offset supply, the parallelly connected output of DC parameter measuring instrument with external power source;
-DC parameter circuit of measurement and control: A.C. contactor KM8 normally opened contact is connected with signal lamp HR4 and is parallelly connected with the rheotrope circuit; Third gear rheotrope SA3 is connected with signal lamp HR1, signal lamp HR2, signal lamp HR3 respectively, and signal lamp HR1, signal lamp HR2, signal lamp HR3 are parallel with switch KA1 coil, switch KA2 coil, switch KA3 coil respectively;
-dynamometer machine main circuit: working power is connected with frequency converter through the second air switch QF2, A.C. contactor KM8 normally opened contact, and frequency converter exports dynamometer machine to, and the 5 two grade of switch, pull-up resistor are connected with frequency converter.
Native system comprises for the low-speed big type approval test with for the little moment of torsion type approval test of high speed.Wherein the low-speed big type approval test is mainly used in test AC driving device, and the little moment of torsion type approval test of high speed is mainly used in the test direct-drive motor.
This electrical type tests test macro is on the basis of having summed up domestic existing aviation electric attachments maintenance electrical type tests equipment, to improve design.This system adopts industrial computer and induction dynamometer control, and the test that the direct current of integrated motor is unloaded, exchange zero load, DC load, AC load possesses the function of the little moment of torsion type approval test of low-speed big type approval test and high speed.This system testing speed is fast, precision is high, easy to use, good reliability, and this equipment meets the technical requirement of aircraft electric attachments electrical type tests integration test fully.
Description of drawings
Below in conjunction with accompanying drawing and embodiment the present invention is done further detailed explanation.
Fig. 1 is an AC parameter measuring circuit diagram in the low-speed big type approval test.
Fig. 2 is control circuit figure in the low-speed big type approval test.
Fig. 3 is DC parameter metering circuit figure in the little moment of torsion type approval test of high speed.
Fig. 4 is DC parameter circuit of measurement and control figure in the little moment of torsion type approval test of high speed.
Fig. 5 is the dynamometer machine main circuit diagram.
Fig. 6 is the aviation plug synoptic diagram.
Embodiment
The utility model integrated test system comprises:
(1) AC parameter measuring circuit.As shown in Figure 1, first experiment power supply is connected with AC parameter measuring instrument through air switch QF1, A.C. contactor KM5 normally opened contact; Second experiment power supply is connected with AC parameter measuring instrument through A.C. contactor KM6 normally opened contact, A.C. contactor KM7 normally opened contact respectively, and A.C. contactor KM6 normally opened contact is parallelly connected with A.C. contactor KM7 normally opened contact.
(2) control circuit.As shown in Figure 2, power circuit is with power switch SK1, emergency stop switch SE1 and the series connection of sub-control circuit; Said sub-control circuit is supplied control circuit, is stopped control circuit and the positive and reverse rotation control circuit parallel connection constitutes by experiment power supply; Normally closed push button switch SB1 (being stop button), normally open push button switch SB2 (for start button), two grades of switch SA2 (direct current, AC switch) series connection constitute experiment power supply supply control circuit; Two grades of switch SA2 are connected with signal lamp HR4 (direct current signal lamp), signal lamp HR5 (AC signal lamp) respectively, normally open push button switch SB2, signal lamp HR5 respectively with A.C. contactor KM5 normally opened contact, A.C. contactor KM5 coils from parallel connection of coils; Normally closed push button switch SB3, normally open push button switch SB4 and the series connection of A.C. contactor KM8 coil, normally open push button switch SB4 is parallelly connected with A.C. contactor KM8 normally opened contact; Two grades of switch SA4 are connected with signal lamp HR6 (signal lamp of just transferring the letter), signal lamp HR7 (reverse signal lamp) respectively, signal lamp HR6, signal lamp HR7 respectively with A.C. contactor KM6 coil, A.C. contactor KM7 coils from parallel connection of coils, constitute positive and reverse rotation control circuit.
This part obtains power supply through socket DY1, also can parallelly connected socket DY2 in the circuit, DY3 is subsequent use.
(3) DC parameter metering circuit.As shown in Figure 4, first shunt, second shunt, the 3rd shunt are connected with the DC parameter measuring instrument through switch KA1, switch KA2, switch KA3 respectively; Offset supply, the parallelly connected output of DC parameter measuring instrument with external power source.First shunt, second shunt, the 3rd shunt are respectively 800A shunt, 300A shunt, 50A shunt.
(4) DC parameter circuit of measurement and control.As shown in Figure 4; A.C. contactor KM8 normally opened contact is connected with signal lamp HR4 and is parallelly connected with the rheotrope circuit; Third gear rheotrope SA3 is connected with signal lamp HR1, signal lamp HR2, signal lamp HR3 respectively, and signal lamp HR1, signal lamp HR2, signal lamp HR3 are parallel with switch KA1 coil, switch KA2 coil, switch KA3 coil respectively.Signal lamp HR1, signal lamp HR2, signal lamp HR3 are respectively 800A shunt, 300A shunt, 50A shunt working signal lamp.This part is supplied power by the 24V Switching Power Supply.
(5) dynamometer machine main circuit.As shown in Figure 5, working power is connected with frequency converter through the second air switch QF2, A.C. contactor KM8 normally opened contact, and frequency converter exports dynamometer machine to, and the 5 two grade of switch, pull-up resistor are connected with frequency converter.
For the low-speed big type approval test, undertaken by following step:
(1) system wiring: three-phase supply is received the testing power supply input end, AC220V, the 50HZ single phase poaer supply is received working power end;
(2) correctly choose AC/DC, just change/reverse, and whether viewing lamp indicates normally;
(3) after power lead connected, closed main cabinet air switch was opened the system power supply input with key switch, opens scram button and each instrument, and it is normal to check that each instrument shows;
(4) open the electrical type tests testing system software, set each parameter, click " power initiation " button and just can carry out type approval test.
For the little moment of torsion type approval test of high speed, undertaken by following step:
(1) system wiring: a. receives the testing power supply input end with three-phase supply, AC220V, and the 50HZ single phase poaer supply is received working power end; B. power supply compensation input end is received in the direct supply compensation, pull-up resistor is received the pull-up resistor end; C. dc power anode is received the power input under the corresponding current gear, notice that institute's electric current gear that connects is corresponding with the corresponding current gear;
(2) correctly choose AC/DC, just change/reverse, and whether viewing lamp indicates normally;
(3) after power lead connected, closed main cabinet air switch was opened the system power supply input with key switch, opens scram button and each instrument, and it is normal to check that each instrument shows;
(4) open the electrical type tests testing system software, set each parameter;
(5) open direct supply, DC voltage is transferred to motor operating voltage, observe motor steering, make motor steering and induction dynamometer switched in opposite;
(6) when direct current generator turns to the induction dynamometer switched in opposite; Start direct current generator; Open dynamometer machine start button (being normally open push button switch SB4), torque output and open (i.e. two grades of switch SA5); Dynamometer Control appearance VG2218A is regulated the excitation gear get to " manually " shelves, regulator potentiometer can carry out load test to direct current generator, and corresponding data and curve are drawn by software.
Above-mentioned normally closed push button switch SB1 can be in series with and start box S1, and normally open push button switch SB2 is parallel with and starts box S2, starts on box S1, the startup box S2 aviation plug can be set, and is as shown in Figure 6.
The foregoing description limits the utility model never in any form, and every employing is equal to the technical scheme that replacement or the mode of equivalent transformation obtain and all drops in the protection domain of the utility model.
Claims (2)
1. integrated test system that is used for aircraft electric attachments electrical type tests is characterized in that comprising:
-AC parameter measuring circuit: first experiment power supply is connected with AC parameter measuring instrument through air switch QF1, A.C. contactor KM5 normally opened contact; Second experiment power supply is connected with AC parameter measuring instrument through A.C. contactor KM6 normally opened contact, A.C. contactor KM7 normally opened contact respectively, and A.C. contactor KM6 normally opened contact is parallelly connected with A.C. contactor KM7 normally opened contact;
-control circuit: power circuit is with power switch SK1, emergency stop switch SE1 and the series connection of sub-control circuit; Said sub-control circuit is supplied control circuit, is stopped control circuit and the positive and reverse rotation control circuit parallel connection constitutes by experiment power supply; Normally closed push button switch SB1, normally open push button switch SB2, two grades of switch SA2 series connection constitute experiment power supply supply control circuit; Two grades of switch SA2 are connected with signal lamp HR4, signal lamp HR5 respectively, normally open push button switch SB2, signal lamp HR5 respectively with A.C. contactor KM5 normally opened contact, A.C. contactor KM5 coils from parallel connection of coils; Normally closed push button switch SB3, normally open push button switch SB4 and the series connection of A.C. contactor KM8 coil, normally open push button switch SB4 is parallelly connected with A.C. contactor KM8 normally opened contact; Two grades of switch SA4 connect and compose positive and reverse rotation control circuit with A.C. contactor KM6 coil, A.C. contactor KM7 coil respectively, and A.C. contactor KM6 coil, A.C. contactor KM7 coil are parallelly connected with signal lamp HR6, signal lamp HR7 respectively;
-DC parameter metering circuit: first shunt, second shunt, the 3rd shunt are connected with the DC parameter measuring instrument through switch KA1, switch KA2, switch KA3 respectively; Offset supply, the parallelly connected output of DC parameter measuring instrument with external power source;
-DC parameter circuit of measurement and control: A.C. contactor KM8 normally opened contact is connected with signal lamp HR4 and is parallelly connected with the rheotrope circuit; Third gear rheotrope SA3 is connected with signal lamp HR1, signal lamp HR2, signal lamp HR3 respectively, and signal lamp HR1, signal lamp HR2, signal lamp HR3 are parallel with switch KA1 coil, switch KA2 coil, switch KA3 coil respectively;
-dynamometer machine main circuit: working power is connected with frequency converter through the second air switch QF2, A.C. contactor KM8 normally opened contact, and frequency converter exports dynamometer machine to, and the 5 two grade of switch, pull-up resistor are connected with frequency converter.
2. a kind of integrated test system that is used for aircraft electric attachments electrical type tests according to claim 1 is characterized in that: said normally closed push button switch SB1 is in series with and starts box S1, and normally open push button switch SB2 is parallel with and starts box S2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120226298XU CN202177688U (en) | 2011-06-30 | 2011-06-30 | Integrated test system for airplane electric accessory motor-type test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120226298XU CN202177688U (en) | 2011-06-30 | 2011-06-30 | Integrated test system for airplane electric accessory motor-type test |
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| CN202177688U true CN202177688U (en) | 2012-03-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201120226298XU Expired - Fee Related CN202177688U (en) | 2011-06-30 | 2011-06-30 | Integrated test system for airplane electric accessory motor-type test |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102759703A (en) * | 2012-07-11 | 2012-10-31 | 深圳珈伟光伏照明股份有限公司 | Testing method and related device for reliability of circuit |
| CN103308868A (en) * | 2013-07-09 | 2013-09-18 | 南昌航空大学 | Airplane power source system control and protection experiment device |
| CN104345243A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Electrical performance check tester for fuel system |
| CN104569810A (en) * | 2013-10-29 | 2015-04-29 | 北京精密机电控制设备研究所 | Load testing system for high-speed motor |
-
2011
- 2011-06-30 CN CN201120226298XU patent/CN202177688U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102759703A (en) * | 2012-07-11 | 2012-10-31 | 深圳珈伟光伏照明股份有限公司 | Testing method and related device for reliability of circuit |
| CN102759703B (en) * | 2012-07-11 | 2015-03-04 | 深圳珈伟光伏照明股份有限公司 | Testing method and related device for reliability of circuit |
| CN103308868A (en) * | 2013-07-09 | 2013-09-18 | 南昌航空大学 | Airplane power source system control and protection experiment device |
| CN103308868B (en) * | 2013-07-09 | 2015-09-16 | 南昌航空大学 | Aircraft power system control and protection experimental provision |
| CN104345243A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Electrical performance check tester for fuel system |
| CN104569810A (en) * | 2013-10-29 | 2015-04-29 | 北京精密机电控制设备研究所 | Load testing system for high-speed motor |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120328 Termination date: 20160630 |