CN203950006U - A kind of aircraft wire fault automatic detector based on microprocessor - Google Patents
A kind of aircraft wire fault automatic detector based on microprocessor Download PDFInfo
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- CN203950006U CN203950006U CN201420163937.6U CN201420163937U CN203950006U CN 203950006 U CN203950006 U CN 203950006U CN 201420163937 U CN201420163937 U CN 201420163937U CN 203950006 U CN203950006 U CN 203950006U
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Abstract
A kind of aircraft wire fault automatic detector based on microprocessor.It comprises controls computing machine, primary module and secondary module; Wherein: control computing machine is Measurement &control computer, it detects interface for user provides; Controlling computing machine is connected with primary module by serial communication bus; Primary module and secondary module are the detection control apparatus that is connected to tested wire two ends, and primary module is connected with secondary module by the mode of radio communication.The aircraft wire fault detector that the utility model provides can carry out on-the site analysis and test to each mobile system line fault of aircraft fast, shows the break-make situation between wire accurate and visually, judgement wire state.Greatly improve efficiency and the accuracy of engineering maintenance, avoided the wire life-span that the wrong dismounting in maintenance job causes to reduce problem simultaneously.
Description
Technical field
The utility model belongs to the Intelligent Measurement technical field of indication wire break-make, particularly relates to a kind of aircraft wire fault automatic detector based on microprocessor.
Background technology
In traditional engineering maintenance, for the detection of aircraft wire, continue to use the basic checkout equipments such as artificial use multimeter detects each root and other all wire break-make situations always one by one, shortcoming is that the course of work is numerous and diverse and repeated high, and is unfavorable for the raising of engineering maintenance efficiency and the assurance of detection accuracy.
Summary of the invention
In order to address the above problem, the purpose of this utility model is to provide a kind of aircraft wire fault automatic detector based on microprocessor.
In order to achieve the above object, the aircraft wire fault automatic detector based on microprocessor that the utility model provides comprises: control computing machine, primary module and secondary module; Wherein: control computing machine is Measurement &control computer, it detects interface for user provides; Controlling computing machine is connected with primary module by serial communication bus; Primary module and secondary module are the detection control apparatus that is connected to tested wire two ends, and primary module is connected with secondary module by the mode of radio communication.
Described primary module comprises: serial communication interface, primary module controller, detection output interface and main wireless communication module; Wherein: serial communication interface is connected with control computing machine; Primary module controller is connected with main wireless communication module with serial communication interface, detection output interface respectively; Detecting output interface is connected with tested wire.
Described secondary module comprises: secondary module controller, detection input interface and secondary wireless communication module; Wherein: secondary module controller is connected with secondary wireless communication module with detection input interface respectively; Detecting input interface is connected with tested wire.
Described detection output interface and detection input interface all comprise a plurality of ports, each port that wherein detects output interface is connected with the corresponding ports that detects input interface by a tested wire respectively, with this, realizes many tested wires are detected simultaneously automatically.
Described control computing machine is connected with primary module by USB universal serial bus.
Described primary module controller and secondary module controller all adopt AT89S52 main control chip.
The aircraft wire fault automatic detector based on microprocessor that the utility model provides can be realized the fast detecting to aircraft wire on off operating mode, and by result simply, show intuitively, thereby improve engineering maintenance efficiency, there is obvious actual application value, can widespread use popularization.
The beneficial effects of the utility model are, can to each mobile system line fault of aircraft, carry out on-the site analysis and test fast, show the break-make situation between wire accurate and visually, judgement wire state.Greatly improve efficiency and the accuracy of engineering maintenance, avoided the wire life-span that the wrong dismounting in maintenance job causes to reduce problem simultaneously.
Accompanying drawing explanation
The structural drawing of the aircraft wire fault automatic detector based on microprocessor that Fig. 1 provides for the utility model.
Fig. 2 is the structural drawing of primary module in this detecting device;
Fig. 3 is the structural drawing of secondary module in this detecting device;
Fig. 4 is for controlling the operation interface control chart of computing machine in this detecting device;
Fig. 5 (a)-Fig. 5 (c) is main module circuit schematic diagram in this detecting device;
Fig. 6 (a)-Fig. 6 (c) is secondary modular circuit schematic diagram in this detecting device;
Fig. 7 is the minimum system circuit diagram of primary module controller and secondary module controller in this detecting device.
Embodiment
The aircraft wire fault automatic detector based on microprocessor the utility model being provided below in conjunction with the drawings and specific embodiments is elaborated.
As shown in Figure 1, the aircraft wire fault automatic detector based on microprocessor that the utility model provides comprises: control computing machine 1, primary module 2 and secondary module 3; Wherein: controlling computing machine 1 is Measurement &control computer, it detects interface for user provides; Controlling computing machine 1 is connected with primary module 2 by serial communication bus; Primary module 2 and secondary module 3 are for being connected to the detection control apparatus at tested wire 4 two ends, and primary module 2 is connected with secondary module 3 by the mode of radio communication.
As shown in Figure 2, described primary module 2 comprises: serial communication interface 21, primary module controller 22, detection output interface 23 and main wireless communication module 24; Wherein: serial communication interface 21 is connected with control computing machine 1; Primary module controller 22 is connected with main wireless communication module 24 with serial communication interface 21, detection output interface 23 respectively; Detecting output interface 23 is connected with tested wire 4.
As shown in Figure 3, described secondary module 3 comprises: secondary module controller 31, detection input interface 32 and secondary wireless communication module 33; Wherein: secondary module controller 31 is connected with secondary wireless communication module 33 with detection input interface 32 respectively; Detecting input interface 32 is connected with tested wire 4.
Described control computing machine 1 is connected with primary module 2 by USB universal serial bus.
Described primary module controller 22 and secondary module controller 31 all adopt AT89S52 main control chip.
Described detection output interface 23 and detection input interface 32 all comprise a plurality of ports, its each port that detects output interface 23 is connected with the corresponding ports that detects input interface 32 by a tested wire 4 respectively, with this, realizes many tested wires 4 are detected simultaneously automatically.
Fig. 4 controls surface chart for controlling the operation of computing machine 1.As shown in Figure 4, interface by system setting, set of time, automatically and manual mode is selected, port is arranged shows and resistance shows and forms.Click " startup system " button, power lights is lighted, and system enters duty.Before measurement, first arrange and control computing machine 1 serial ports, make as the control computing machine 1 of host computer and can proper communications as the primary module 2 of slave computer.Confirm aircraft wire port number, click " dropdown listbox " and select port number, control the correspondingly situation of arranging of display port of computing machine 1 interface.Different type of machines port is arranged may be different, need in controlling computing machine 1, to write the situation that different port is arranged in advance.While selecting " automatic mode " work, system sends order measures primary module 2 automatically successively from 1 to selected port number; Under " automatic mode ", need input lead code clerk in " text box " on " transmission " button the right artificially, measure the resistance between this numbering corresponding ports and wire another side all of the port.
Fig. 5 (a)-Fig. 5 (c) is main module circuit schematic diagram in this detecting device; Fig. 6 (a)-Fig. 6 (c) is secondary modular circuit schematic diagram in this detecting device; As shown in Figure 5, Figure 6, the P1.0 mouth on primary module 2 connects the clk end of analog to digital converter ADC0832; The DI of P1.1 mouth and analog to digital converter ADC0832, DO pin connects.In primary module 2 and secondary module 3, the CH0 pin of analog to digital converter ADC0832 is all the common port of succeeding electrical equipment; And P0.0, P0.1 and P0.2 mouth meet respectively the address end A of code translator 74LS138, B, C; P3.0, P3.1 mouth meet respectively the RXD of wireless module, TXD end.The decoder output of primary module 2 and secondary module 3 is all the selecting side T1-T16 that succeeds electrical equipment, A1-A16.During work, by P0.0, P0.1 and P0.2 mouth, to the address end of code translator, provide level, control the output of code translator; The output low level of code translator is connected connected relay; Simultaneously secondary module 3 receives primary module 2 orders, connects successively relay corresponding to each port of wire another side equally, thereby form the resistance between the measurement port of loop by controlling P0 mouth.
Fig. 7 is the minimum system circuit diagram of primary module controller and secondary module controller in this detecting device, and wherein single-chip minimum system adopts 11.0592MHz quartz oscillator, in order to carry out internal processes instruction, and EA termination Vcc.During crystal oscillator work, RST pin continues 2 machine cycle high level makes monolithic processor resetting.AT89S52 main control chip has one for forming the high-gain inverting amplifier of internal oscillator, and pin XTAL1 and XTAL2 are respectively input end and the output terminals of this amplifier.This amplifier forms self-excited oscillator together with quartz crystal outside sheet as feedback element or ceramic resonator.The backfeed loop that external quartz crystal (or ceramic resonator) and capacitor C 1, C2 are connected on amplifier forms parallel oscillatory circuit.Here electric capacity is used 30pF ± 10pF.
Testing process: primary module 2 and secondary module 3 connect respectively the two ends of tested wire 4, both communicate by wireless mode, thereby realize the Quick Measurement to resistance between aircraft wire port under wireless environment, and carry out analyzing and processing by controlling computing machine 1, by wire break-make result simply, on interface, show intuitively.
Claims (6)
1. the aircraft wire fault automatic detector based on microprocessor, is characterized in that: it comprises: control computing machine (1), primary module (2) and secondary module (3); Wherein: controlling computing machine (1) is Measurement &control computer, it detects interface for user provides; Controlling computing machine (1) is connected with primary module (2) by serial communication bus; Primary module (2) and secondary module (3) are for being connected to the detection control apparatus at tested wire (4) two ends, and primary module (2) is connected with secondary module (3) by the mode of radio communication.
2. the aircraft wire fault automatic detector based on microprocessor according to claim 1, is characterized in that: described primary module (2) comprising: serial communication interface (21), primary module controller (22), detection output interface (23) and main wireless communication module (24); Wherein: serial communication interface (21) is connected with control computing machine (1); Primary module controller (22) is connected with main wireless communication module (24) with serial communication interface (21), detection output interface (23) respectively; Detecting output interface (23) is connected with tested wire (4).
3. the aircraft wire fault automatic detector based on microprocessor according to claim 1, is characterized in that: described secondary module (3) comprising: secondary module controller (31), detection input interface (32) and secondary wireless communication module (33); Wherein: secondary module controller (31) is connected with secondary wireless communication module (33) with detection input interface (32) respectively; Detecting input interface (32) is connected with tested wire (4).
4. the aircraft wire fault automatic detector based on microprocessor according to claim 1, it is characterized in that: described detection output interface (23) and detection input interface (32) all comprise a plurality of ports, each port that wherein detects output interface (23) is connected with the corresponding ports that detects input interface (32) by a tested wire (4) respectively, with this, realizes many tested wires (4) are detected simultaneously automatically.
5. the aircraft wire fault automatic detector based on microprocessor according to claim 1, is characterized in that: described control computing machine (1) is connected with primary module (2) by USB universal serial bus.
6. the aircraft wire fault automatic detector based on microprocessor according to claim 1, is characterized in that: described primary module controller (22) and secondary module controller (31) all adopt AT89S52 main control chip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420163937.6U CN203950006U (en) | 2014-04-04 | 2014-04-04 | A kind of aircraft wire fault automatic detector based on microprocessor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420163937.6U CN203950006U (en) | 2014-04-04 | 2014-04-04 | A kind of aircraft wire fault automatic detector based on microprocessor |
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| Publication Number | Publication Date |
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| CN203950006U true CN203950006U (en) | 2014-11-19 |
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| CN201420163937.6U Expired - Fee Related CN203950006U (en) | 2014-04-04 | 2014-04-04 | A kind of aircraft wire fault automatic detector based on microprocessor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106646082A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Airplane wire harness conduction detection device based on wireless router |
| CN110456185A (en) * | 2019-07-19 | 2019-11-15 | 成都承芯科技有限公司 | Electron key test macro and test method |
-
2014
- 2014-04-04 CN CN201420163937.6U patent/CN203950006U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106646082A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Airplane wire harness conduction detection device based on wireless router |
| CN110456185A (en) * | 2019-07-19 | 2019-11-15 | 成都承芯科技有限公司 | Electron key test macro and test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141119 Termination date: 20150404 |
|
| EXPY | Termination of patent right or utility model |