CN2904000Y - Spark detector for aircraft CD motor - Google Patents
Spark detector for aircraft CD motor Download PDFInfo
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- CN2904000Y CN2904000Y CN 200520092741 CN200520092741U CN2904000Y CN 2904000 Y CN2904000 Y CN 2904000Y CN 200520092741 CN200520092741 CN 200520092741 CN 200520092741 U CN200520092741 U CN 200520092741U CN 2904000 Y CN2904000 Y CN 2904000Y
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Abstract
An airplane DC motor spark detector is mainly composed of a panel, a shell and a circuit board. The panel is equipped with a switch, a wave-band switch, a liquid crystal screen, an alarming indicator light, a danger indicator light, a normal work indicator light, a fine adjustment button, a power source correct indicator, a power source reversed-phase indicator light, and a power source interface. The panel is arranged on the shell, and the circuit board is arranged inside the shell. The circuit board is mainly composed of a digital power supply circuit, a MCU microprocessor module, an A/D data collection function module, a system self-calibration function module, and a spark simulation testing module. The utility model can realize in-situ testing, the whole testing process only need one person in the machine chamber to operate the buttons in sequence. When need to make detection, only need to plug the detector power supply wire into the working-lamp socket on the front or rear landing gear of the airplane, then the detection can be started, the external power source is not needed. The utility model has simple operation process, which only needs 2-5 minutes to complete a detection of an airplane. The utility model also has advantages of low power consumption, accurate detection, high precision, sound and light alarm, digital display, and also has zeroing and self-calibration functions.
Description
Technical field: the utility model relates to a kind of spark detector, especially a kind of aircraft direct current generator spark detector.
Background technology: direct current and hum bar brush motor owing to have good startup and speed adjusting performance, have a wide range of applications until industry such as household electrical appliance, national defence, civilian industry at steel rolling, traffic, lathe hoisting device, building machinery.But, in such motor operation course, when commutation, tend to produce electric spark, it not only produces harm to the safe operation of motor, and electronic equipment and the communication system of strong electromagnetic interference (EMI) around will influencing, also caused unnecessary energy loss simultaneously, cause serious accident in inflammable and explosive on-the-spot meeting.Because exceeding standard of spark can make the load capacity of motor weaken, aboard, if can not change the motor that grade of spark exceeds standard, when to a certain degree the time, it is malfunctioning to make the quilt of the direct current motor of aircraft drive object.In addition, the electromagnetic wave of spark generation is arranged with the radar of countermeasure aircraft, the operate as normal of communication system.Therefore, the electric spark that exceeds standard is the harmful greatly of aircraft, need effectively judge the grade of spark, in time changes motor.Up to now, also there is not special spark detecting instrument both at home and abroad, basically also only relying on experienced workman with the naked eye estimates, it is interrupted point-like or continuous graininess or not with phenomenons such as ligule spark and quick-fried strong sound that no-spark, spark are arranged under to the brush according to the observation, the judgement grade of spark of subjectivity.So not only human factor is big, detection speed is slow, labour intensity is big, and can't realize state-detection and monitoring are carried out in the operation of motor with computer interconnection.
Summary of the invention: at above-mentioned the deficiencies in the prior art, the utility model provide a kind of easy and simple to handle, volume is little, anti-interference, precision is high, measurement is accurate, can realize the spark detector of in situ detection.
For achieving the above object, the technical scheme that the utility model adopted is: aircraft direct current generator spark detector, mainly form by panel, housing (4) and circuit board.Panel is fixed on the front end of housing (4), switch (1) is arranged on the panel, waver (2), LCDs (3), alarm lamp (5), dangerous pilot lamp (6), normal pilot lamp (7), fine setting button (8), the correct pilot lamp of power supply (9), the anti-phase pilot lamp of power supply (10), power interface (11).Wherein switch (1), fine setting button (8), the correct pilot lamp of power supply (9), the anti-phase pilot lamp of power supply (10), power interface (11) are positioned at the lower end of panel, waver (2) is positioned at the middle part of panel, and LCDs (3), alarm lamp (5), dangerous pilot lamp (6), normal pilot lamp (7) are positioned at the top of panel.Circuit board places in the housing (4).Circuit board is mainly by the digital power circuit, the MCU microprocessor module, and A/D data acquisition function module, system's self-correcting module, spark analog detection module is formed.Power circuit links to each other with each modular circuit, and system's self-correcting module links to each other with spark analog detection module, and spark analog detection module links to each other with A/D data acquisition function module, and A/D data acquisition function module links to each other with the MCU microprocessor module.
The digital power circuit structure is as follows: 1 pin of JP1 connects the JTAG_PWR end, and 2 pin connect 3 pin of AS1117, and 3 pin connect the negative pole of diode D1.The positive pole of D2 connects+15V.J
0An end ground connection.One end ground connection of capacitor C 3,2 pin of another termination J3.Capacitor C 4 and C3 parallel connection.The 1 pin ground connection of AS1117,2 pin connecting resistance R3,3 pin connect capacitor C 4.2 pin of one termination AS1117 of capacitor C 5, other end ground connection.Capacitor C 6 and C7 are in parallel with C5.Another termination VCC of R3.The negative pole of diode D3 connects the end of C5, and positive pole meets AVCC+3.3V.One termination VCC JATG of capacitor C 8, other end ground connection.C9 and C8 parallel connection.One termination C9 of resistance R 8, another point connect the AGND end.The negative pole of one termination D3 of capacitor C 10, other end ground connection.Capacitor C 11 and C10 parallel connection.
The structure of MCU microprocessor module is as follows: 1 pin of C8051F330/331 connects 1 end of J5,2 pin ground connection, and 3 pin meet VCC, and 5 pin connect 6 pin of J7,6 pin connect 10 pin of J2, and 7 pin connect 9 pin of J2, and 8 pin connect 7 pin of J2,9 pin connect 2 ends of J7, and 10 pin connect 1 end of J7, and 11 pin connect 5 ends of J6,12 pin connect 4 ends of J6, and 13 pin connect 3 ends of J6, and 14 pin connect 2 ends of J6,15 pin connect 1 end of J6, and 16 pin connect 6 ends of J5, and 17 pin connect 5 ends of J5,18 pin connect 4 ends of J5, and 19 pin connect 3 ends of J5, and 20 pin connect 2 ends of J5.1 pin and 2 pin of J2 meet VCC, 11 pin ground connection, and J2 connects and shows output.The 6 end ground connection of J6, J6 connects and shows output.J5 connects keyboard.
The structure of A/D data acquisition function module is as follows: 1 pin of U3ADS1100 connects 2 pin of J4,2 pin ground connection, and 3 pin connect 19 pin of C8051F330/331, and 4 pin connect 20 pin of C8051F330/331, and 5 pin meet VCC, and 6 pin connect 3 pin of J4.1 pin of J4 meets AVCC, and 4 pin connect AGND end, start to exchange fire respectively 1 pin and 2 pin of JP2 of colored analog detection module of 2 pin and 3 pin.One termination VCC of resistance R 4,3 pin of another termination ADS1100, a termination VCC of resistance R 5,4 pin of another termination ADS1100.
The structure of system's self-correcting module is as follows: the termination TEST VCC end of resistance R 20, the negative pole of another terminating diode D6, the positive pole of D6 connects capacitor C 10, the other end connecting resistance R21 of C10, the other end connecting resistance R22 of R21, the grid of another termination T3 of R22, the source electrode of T3 connect the TEST end, and drain electrode end is connected between C10 and the R21.The source terminal of one termination T3 of resistance R 23, another termination C10.
The structure of spark analog detection module is as follows: 4 pin of POWER IN connect the power supply of direct current generator, are the spark signal input end, and 1 pin and 2 pin connect the positive pole of diode (LED) 1, and 3 pin and 4 pin connect switch SW 1 through FA.The negative pole connecting resistance R1 of LED1, diode (LED) 2 and LED1 series connection.The positive pole of diode D1 meets SW2, and negative pole meets L1, another termination L2 of L1.Capacitor C 1 is connected between L1 and the L2, C2, C3 and C1 parallel connection.R2, C4, C6 parallel connection, R3, C5, C7 parallel connection, R2, C4, one termination of C6+15V, other end ground connection, R3, C5, one termination of C7-15V, other end ground connection.7 pin of U10P07 connect+15V, and 4 pin connect-15V, and 3 pin are through resistance R 11 ground connection, 2 pin connecting resistance R10, and 6 pin are connected between series diode D2 and the D3.The other end ground connection of resistance R 11.Another termination capacitor C 8 of R10, another termination waver SW3 of C8.The positive pole of diode D2 connects the base stage of triode T1, the collector connecting resistance R14 of T1, emitter connecting resistance R13.The negative pole of diode D3 connects the base stage of triode T2, the collector connecting resistance R15 of T2, emitter connecting resistance R12.Resistance R 16 1 termination R10, another termination R17, the positive pole of the terminating diode D4 of R17, the negative pole connecting resistance R19 of D4 and the negative pole of diode D5, the plus earth of D5,1 end of another termination JP2 of R19.Capacitor C 9, resistance R 18 and D5 parallel connection.The 2 end ground connection of JP2.
The utility model can be realized in situ detection, whole testing process, only need a people according to the order of sequence in the cabin operating electrical machines button can finish detection.This detector need only be plugged on the power lead of detector on the inspection lamp socket of aircraft nose-gear or back undercarriage when detecting, and just can detect dispense with outer connecting power.The utility model operating process is simple, and the detection of finishing an airplane only needs 2～5 minutes.Characteristics that the utility model also has is low in energy consumption, measure accurately, precision is high, but also adopt sound and light alarm digitally show also have zeroing, zero offset capability.
Description of drawings:
Fig. 1 is a structural representation of the present utility model.
Fig. 2 be the utility model A/D data acquisition function module circuit theory diagrams.
Fig. 3 is the circuit theory diagrams of the utility model MCU microprocessor module.
Fig. 4 is the schematic diagram of the utility model digital power circuit.
Fig. 5 be the utility model system self-correcting module circuit theory diagrams.
Fig. 6 be the utility model spark analog detection module circuit theory diagrams.
Fig. 7 is a circuit working theory diagram of the present utility model.
Fig. 8 is the principle of work block diagram of spark analog detection module.
Embodiment:
As Fig. 1-shown in Figure 8, aircraft direct current generator spark detector mainly is made up of panel, housing 4 and circuit board.Panel is fixed on the front end of housing 4, and switch 1 is arranged on the panel, waver 2, LCDs 3, alarm lamp 5, dangerous pilot lamp 6, normal pilot lamp 7, fine setting button 8, the correct pilot lamp 9 of power supply, the anti-phase pilot lamp 10 of power supply, power interface 11.Wherein switch 1, fine setting button 8, the correct pilot lamp 9 of power supply, the anti-phase pilot lamp 10 of power supply, power interface 11 are positioned at the lower end of panel, waver 2 is positioned at the middle part of panel, and LCDs 3, alarm lamp 5, dangerous pilot lamp 6, normal pilot lamp 7 are positioned at the top of panel.Circuit board places in the housing 4.Circuit board is mainly by the digital power circuit, the MCU microprocessor module, and A/D data acquisition function module, system's self-correcting module, spark analog detection module is formed.Power circuit links to each other with each modular circuit, and system's self-correcting module links to each other with spark analog detection module, and spark analog detection module links to each other with A/D data acquisition function module, and A/D data acquisition function module links to each other with the MCU microprocessor module
The digital power circuit structure is as follows: 1 pin of JP1 connects the JTAG_PWR end, and 2 pin connect 3 pin of AS1117, and 3 pin connect the negative pole of diode D1.The positive pole of D2 connects+15V.J
0An end ground connection.One end ground connection of capacitor C 3,2 pin of another termination J3.Capacitor C 4 and C3 parallel connection.The 1 pin ground connection of AS1117,2 pin connecting resistance R3,3 pin connect capacitor C 4.2 pin of one termination AS1117 of capacitor C 5, other end ground connection.Capacitor C 6 and C7 are in parallel with C5.Another termination VCC of R3.The negative pole of diode D3 connects the end of C5, and positive pole meets AVCC+3.3V.One termination VCC JATG of capacitor C 8, other end ground connection.C9 and C8 parallel connection.One termination C9 of resistance R 8, another point connect the AGND end.The negative pole of one termination D3 of capacitor C 10, other end ground connection.Capacitor C 11 and C10 parallel connection.
The structure of MCU microprocessor module is as follows: 1 pin of C8051F330/331 connects 1 end of J5,2 pin ground connection, and 3 pin meet VCC, and 5 pin connect 6 pin of J7,6 pin connect 10 pin of J2, and 7 pin connect 9 pin of J2, and 8 pin connect 7 pin of J2,9 pin connect 2 ends of J7, and 10 pin connect 1 end of J7, and 11 pin connect 5 ends of J6,12 pin connect 4 ends of J6, and 13 pin connect 3 ends of J6, and 14 pin connect 2 ends of J6,15 pin connect 1 end of J6, and 16 pin connect 6 ends of J5, and 17 pin connect 5 ends of J5,18 pin connect 4 ends of J5, and 19 pin connect 3 ends of J5, and 20 pin connect 2 ends of J5.1 pin and 2 pin of J2 meet VCC, 11 pin ground connection, and J2 connects and shows output.The 6 end ground connection of J6, J6 connects and shows output.J5 connects keyboard.
The structure of A/D data acquisition function module is as follows: 1 pin of U3ADS1100 connects 2 pin of J4,2 pin ground connection, and 3 pin connect 19 pin of C8051F330/331, and 4 pin connect 20 pin of C8051F330/331, and 5 pin meet VCC, and 6 pin connect 3 pin of J4.1 pin of J4 meets AVCC, and 4 pin connect AGND end, start to exchange fire respectively 1 pin and 2 pin of JP2 of colored analog detection module of 2 pin and 3 pin.One termination VCC of resistance R 4,3 pin of another termination ADS1100, a termination VCC of resistance R 5,4 pin of another termination ADS1100.
The structure of system's self-correcting module is as follows: the termination TEST VCC end of resistance R 20, the negative pole of another terminating diode D6, the positive pole of D6 connects capacitor C 10, the other end connecting resistance R21 of C10, the other end connecting resistance R22 of R21, the grid of another termination T3 of R22, the source electrode of T3 connect the TEST end, and drain electrode end is connected between C10 and the R21.The source terminal of one termination T3 of resistance R 23, another termination C10.
The structure of spark analog detection module is as follows: 4 pin of POWER IN connect the power supply of direct current generator, are the spark signal input end, and 1 pin and 2 pin connect the positive pole of diode (LED) 1, and 3 pin and 4 pin connect switch SW 1 through FA.The negative pole connecting resistance R1 of LED1, diode (LED) 2 and LED1 series connection.The positive pole of diode D1 meets SW2, and negative pole meets L1, another termination L2 of L1.Capacitor C 1 is connected between L1 and the L2, C2, C3 and C1 parallel connection.R2, C4, C6 parallel connection, R3, C5, C7 parallel connection, R2, C4, one termination of C6+15V, other end ground connection, R3, C5, one termination of C7-15V, other end ground connection.7 pin of U10P07 connect+15V, and 4 pin connect-15V, and 3 pin are through resistance R 11 ground connection, 2 pin connecting resistance R10, and 6 pin are connected between series diode D2 and the D3.The other end ground connection of resistance R 11.Another termination capacitor C 8 of R10, another termination waver SW3 of C8.The positive pole of diode D2 connects the base stage of triode T1, the collector connecting resistance R14 of T1, emitter connecting resistance R13.The negative pole of diode D3 connects the base stage of triode T2, the collector connecting resistance R15 of T2, emitter connecting resistance R12.Resistance R 16 1 termination R10, another termination R17, the positive pole of the terminating diode D4 of R17, the negative pole connecting resistance R19 of D4 and the negative pole of diode D5, the plus earth of D5,1 end of another termination JP2 of R19.Capacitor C 9, resistance R 18 and D5 parallel connection.The 2 end ground connection of JP2.
When the power switch of instrument was disconnected, the instrument power source plug inserted on the inspection lamp socket of nose-gear, if the anti-phase pilot lamp of power supply is glittering, should immediately plug be pulled up tuning.When the correct pilot lamp of power supply is bright, open instrument switch, measure.
Waver is allocated to " SELF TEST " self-correcting shelves, system start-up self-correcting circuit, this moment, LCDs showed the self-correcting value.The self-correcting value is normal in 0.3～0.6 scope, and can carry out motor and detect this moment.
During detection, type according to motor, the rotation waver is to corresponding gear, the power supply of aircraft direct current generator is inserted power interface, and this moment, spark signal was imported spark analog detection module through POWER IN, and a spark signal part is through rectification, LC filtering, the voltage stabilizing of diode, dividing potential drop by high-power resistance, it is divided into+15V and-the 15V direct supply, be used to provide the power supply of mimic channels such as operational amplifier and self-correcting module, wherein+15V also offers digital circuit part power supply.+ 15V inserts the digital power circuit of Fig. 4, through diode rectification, after AS1117 voltage stabilizing of voltage stabilizing chip and the filter capacitor filtering, produces the direct supply of 3.3V, for digital circuit partly provides power supply; Another part of spark signal is through filtering, and precision is amplified, shaping, and pulse keeps, and send A/D data acquisition function module.Become digital signal to send MCU microprocessor module through A/D data acquisition function module converts.The MCU microprocessor module is handled and is adjusted data, and the liquor charging crystal display screen shows.Can directly read to locate the equivalent coefficient of spark on LCDs, if the grade of spark coefficient is normal, then normal pilot lamp 7 is glittering, exceeds standard as the grade of spark coefficient, and then alarm lamp 5 is glittering, is between the two as equivalent coefficient, and then dangerous pilot lamp 6 is glittering.Detection finishes, and turns off power switch, and waver returns to SELF TEST retaining, pulls up the instrument plug, and instrument restores to the original state.
Claims (6)
1, aircraft direct current generator spark detector, mainly by panel, housing (4) and circuit board are formed, panel is fixed on the front end of housing (4), switch (1) is arranged on the panel, waver (2), LCDs (3), alarm lamp (5), dangerous pilot lamp (6), normal pilot lamp (7), fine setting button (8), the correct pilot lamp of power supply (9), the anti-phase pilot lamp of power supply (10), power interface (11), switch (1) wherein, fine setting button (8), the correct pilot lamp of power supply (9), the anti-phase pilot lamp of power supply (10), power interface (11) is positioned at the lower end of panel, waver (2) is positioned at the middle part of panel, LCDs (3), alarm lamp (5), dangerous pilot lamp (6), normal pilot lamp (7) is positioned at the top of panel, and circuit board places in the housing (4), it is characterized in that, circuit board is mainly by power circuit, MCU microprocessor module, A/D data acquisition function module, system's self-correcting module, spark analog detection module is formed; Power circuit links to each other with each modular circuit, and system's self-correcting module links to each other with spark analog detection module, and spark analog detection module links to each other with A/D data acquisition function module, and A/D data acquisition function module links to each other with the MCU microprocessor module.
2, aircraft direct current generator spark detector as claimed in claim 1, it is characterized in that, the structure of spark analog detection module is as follows: 4 pin of POWER IN connect the power supply of direct current generator, be the spark signal input end, 1 pin and 2 pin connect the positive pole of diode (LED) 1, and 3 pin and 4 pin connect switch SW 1 through FA, the negative pole connecting resistance R1 of LED1, diode (LED) 2 and LED1 series connection, the positive pole of diode D1 meets SW2, and negative pole meets L1, another termination L2 of L1, capacitor C 1 is connected between L1 and the L2, C2, C3 and C1 parallel connection, R2, C4, C6 parallel connection, R3, C5, the C7 parallel connection, R2, C4, one termination of C6+15V, other end ground connection, R3, C5, one termination of C7-15V, other end ground connection, 7 pin of U10P07 connect+15V, and 4 pin connect-15V, 3 pin are through resistance R 11 ground connection, 2 pin connecting resistance R10,6 pin are connected between series diode D2 and the D3, the other end ground connection of resistance R 11, another termination capacitor C 8 of R10, another termination waver SW3 of C8, the positive pole of diode D2 connects the base stage of triode T1, the collector connecting resistance R14 of T1, emitter connecting resistance R13, the negative pole of diode D3 connects the base stage of triode T2, the collector connecting resistance R15 of T2, emitter connecting resistance R12, resistance R 16 1 termination R10, another termination R17, the positive pole of the terminating diode D4 of R17, the negative pole connecting resistance R19 of D4 and the negative pole of diode D5, the plus earth of D5,1 end of another termination JP2 of R19, capacitor C 9, resistance R 18 and D5 parallel connection, the 2 end ground connection of JP2.
3, aircraft direct current generator spark detector as claimed in claim 1, it is characterized in that the structure of system's self-correcting module is as follows: the termination TEST VCC end of resistance R 20, the negative pole of another terminating diode D6, the positive pole of D6 connects capacitor C 10, the other end connecting resistance R21 of C10, the other end connecting resistance R22 of R21, the grid of another termination T3 of R22, the source electrode of T3 connects the TEST end, drain electrode end is connected between C10 and the R21, the source terminal of a termination T3 of resistance R 23, another termination C10.
4, aircraft direct current generator spark detector as claimed in claim 1, it is characterized in that, the structure of A/D data acquisition function module is as follows: 1 pin of U3ADS1100 connects 2 pin of J4,2 pin ground connection, 3 pin connect 19 pin of C8051F330/331,4 pin connect 20 pin of C8051F330/331,5 pin meet VCC, and 6 pin connect 3 pin of J4, and 1 pin of J4 meets AVCC, 4 pin connect the AGND end, start to exchange fire respectively 1 pin and 2 pin of JP2 of colored analog detection module of 2 pin and 3 pin, a termination VCC of resistance R 4,3 pin of another termination ADS1100, one termination VCC of resistance R 5,4 pin of another termination ADS1100.
5, aircraft direct current generator spark detector as claimed in claim 1 is characterized in that the structure of MCU microprocessor module is as follows: 1 pin of C8051F330/331 connects 1 end of J5,2 pin ground connection, 3 pin meet VCC, and 5 pin connect 6 pin of J7,6 pin connect 10 pin of J2, and 7 pin connect 9 pin of J2, and 8 pin connect 7 pin of J2,9 pin connect 2 ends of J7,10 pin connect 1 end of J7, and 11 pin connect 5 ends of J6, and 12 pin connect 4 ends of J6,13 pin connect 3 ends of J6,14 pin connect 2 ends of J6, and 15 pin connect 1 end of J6, and 16 pin connect 6 ends of J5,17 pin connect 5 ends of J5,18 pin connect 4 ends of J5, and 19 pin connect 3 ends of J5, and 20 pin connect 2 ends of J5,1 pin and 2 pin of J2 meet VCC, 11 pin ground connection, J2 connects and shows output, the 6 end ground connection of J6, J6 connects and shows output, and J5 connects keyboard.
6, aircraft direct current generator spark detector as claimed in claim 1 is characterized in that the digital power circuit structure is as follows: 1 pin of JP1 connects the JTAG_PWR end, and 2 pin connect 3 pin of AS1117, and 3 pin connect the negative pole of diode D1, and the positive pole of D2 connects+15V, J
0An end ground connection, an end ground connection of capacitor C 3,2 pin of another termination J3, capacitor C 4 and C3 parallel connection, the 1 pin ground connection of AS1117,2 pin connecting resistance R3,3 pin connect capacitor C 4,2 pin of one termination AS1117 of capacitor C 5, other end ground connection, capacitor C 6 and C7 are in parallel with C5, another termination VCC of R3, the negative pole of diode D3 connects the end of C5, positive pole meets AVCC+3.3V, a termination VCC JATG of capacitor C 8, other end ground connection, C9 and C8 parallel connection, one termination C9 of resistance R 8, another point connect AGND end, the negative pole of a termination D3 of capacitor C 10, other end ground connection, capacitor C 11 and C10 parallel connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200520092741 CN2904000Y (en) | 2005-09-29 | 2005-09-29 | Spark detector for aircraft CD motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200520092741 CN2904000Y (en) | 2005-09-29 | 2005-09-29 | Spark detector for aircraft CD motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2904000Y true CN2904000Y (en) | 2007-05-23 |
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ID=38079414
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200520092741 Expired - Fee Related CN2904000Y (en) | 2005-09-29 | 2005-09-29 | Spark detector for aircraft CD motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2904000Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101813733A (en) * | 2010-05-11 | 2010-08-25 | 成都华太航空科技有限公司 | MSP85 mode panel-selecting driving tester |
| CN102062833A (en) * | 2010-12-03 | 2011-05-18 | 北京统合万方科技有限公司 | Programmable airplane power supply characteristic comprehensive test apparatus |
| CN102103170B (en) * | 2009-12-17 | 2012-12-26 | 上海凯迪克航空工程技术有限公司 | In-situ detection device of anti-skidding electrical control system |
-
2005
- 2005-09-29 CN CN 200520092741 patent/CN2904000Y/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102103170B (en) * | 2009-12-17 | 2012-12-26 | 上海凯迪克航空工程技术有限公司 | In-situ detection device of anti-skidding electrical control system |
| CN101813733A (en) * | 2010-05-11 | 2010-08-25 | 成都华太航空科技有限公司 | MSP85 mode panel-selecting driving tester |
| CN101813733B (en) * | 2010-05-11 | 2011-12-21 | 成都华太航空科技有限公司 | MSP85 mode panel-selecting driving tester |
| CN102062833A (en) * | 2010-12-03 | 2011-05-18 | 北京统合万方科技有限公司 | Programmable airplane power supply characteristic comprehensive test apparatus |
| CN102062833B (en) * | 2010-12-03 | 2015-05-20 | 北京航天万方科技有限公司 | Programmable airplane power supply characteristic comprehensive test apparatus |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20070523 Termination date: 20091029 |