CN102435914B - Portable aircraft wire comprehensive performance tester - Google Patents
Portable aircraft wire comprehensive performance tester Download PDFInfo
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- CN102435914B CN102435914B CN 201110316971 CN201110316971A CN102435914B CN 102435914 B CN102435914 B CN 102435914B CN 201110316971 CN201110316971 CN 201110316971 CN 201110316971 A CN201110316971 A CN 201110316971A CN 102435914 B CN102435914 B CN 102435914B
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 18
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Abstract
The invention relates to a portable aircraft wire comprehensive performance tester which comprises an electrical parameter measurement circuit, a high-speed A/D (analog to digital) acquisition circuit, a pulse transmitting circuit, an over-voltage protection circuit, an interface conversion circuit, an impedance matching circuit, a DSP (digital signal processing) control unit, a power supply, anda man-machine interface, wherein the pulse transmitting circuit, the impedance matching circuit, the interface conversion circuit and a tested wire, the over-voltage protection circuit and the high-speed A/D acquisition circuit are successively connected in series; the output end of the high-speed A/D acquisition circuit is connected with the DSP control unit; the pulse transmitting circuit is also connected with the DSP control unit; the tested wire is also connected with the high-speed A/D acquisition circuit through the electrical parameter measurement circuit; and the power supply and theman-machine interface are respectively connected with the DSP control unit. The tester provided by the invention can be used for measuring parameters of the tested wire, such as AC and DC voltage, current, resistance, capacitance and the like and can be also used for diagnosing aircraft wire fault and determining the fault position.
Description
Technical field
The present invention relates to a kind of aircraft lead general performance test.Particularly relate to and a kind ofly can diagnose the aircraft breakdown of conducting wires, determine the portable aircraft lead general performance test of abort situation.
Background technology
The aircraft breakdown of conducting wires is one of most common failure of Aircraft Electrical System, can cause the indicating instrument instability, control consequences such as machinery is not worked, signal is undesired, lead short circuit initiation is caught fire, and is directly connected to aircraft safety.Be to shorten the troubleshooting time of aircraft, save maintenance cost, need a kind of aircraft lead general performance test integration test aircraft lead performance, correctly diagnose the aircraft breakdown of conducting wires, accurately determine aircraft breakdown of conducting wires position.At present, though there is aircraft breakdown of conducting wires orientator to exist, volume is big, electrical source consumption is big, need external power source, the not high weakness of intelligent degree, is unsuitable for extensively promoting the use of in the aircraft maintenance industry, needs a kind of portable aircraft lead general performance test for this reason but exist.
Summary of the invention
Technical matters to be solved by this invention is, parameters such as a kind of combined-voltage that namely can measure tested lead, electric current, resistance, electric capacity are provided, and can also diagnose the aircraft breakdown of conducting wires, determines the portable aircraft lead general performance test of abort situation.
The technical solution adopted in the present invention is: a kind of portable aircraft lead general performance test comprises: electric parameter measurement circuit, high-speed a/d Acquisition Circuit, pulse radiating circuit, overvoltage crowbar, interface conversion circuit, impedance matching circuit, DSP control module, power supply, human-computer interaction interface; Wherein: described pulse radiating circuit, impedance matching circuit, interface conversion circuit, tested lead, overvoltage crowbar and high-speed a/d Acquisition Circuit are connected in series successively; the output terminal of described high-speed a/d Acquisition Circuit connects the DSP control module; described pulse radiating circuit also connects the DSP control module; described tested lead also connects the high-speed a/d Acquisition Circuit by the electric parameter measurement circuit, and described power supply is connected the DSP control module respectively with human-computer interaction interface.
Described DSP control module includes dsp controller and the FLASH storage chip that links to each other with dsp controller respectively, ARM storage chip, and described high-speed a/d Acquisition Circuit, pulse radiating circuit, power supply and human-computer interaction interface are connected the dsp controller in the DSP control module respectively.
Described interface conversion circuit includes: Chuan Jie 4N26 photoelectrical coupler, adjustable resistance, 74HC14 chip and 555 time base circuits successively, wherein, the input end of described 4N26 photoelectrical coupler connects impedance matching circuit, and the output of described 555 time base circuits connects tested lead.
Portable aircraft lead general performance test of the present invention namely can be measured the parameter such as combined-voltage, electric current, resistance, electric capacity of tested lead, can also diagnose the aircraft breakdown of conducting wires, determines abort situation.Have following characteristics:
1, proposed based on DSP control core, pulse generating circuit and small size LCDs etc. at interior system hardware, for portable aircraft lead general performance test provides the device hardware basis;
2, propose the system software module processing, strengthened extended capability and the portable ability of system;
3, propose reflected signal disposal route based on wavelet analysis method, reduced undesired signal to the influence of measurement result;
4, utilize least square method to judge the position of launching site and trouble spot, accurately fault location point position;
Description of drawings
Fig. 1 is portable aircraft lead general performance test general structure synoptic diagram of the present invention;
Fig. 2 is the formation block diagram of interface conversion circuit of the present invention;
Fig. 3 is portable aircraft lead general performance test control flow chart of the present invention.
Wherein:
1: electric parameter measurement circuit 2: the high-speed a/d Acquisition Circuit
3: low pressure burst pulse radiating circuit 4: overvoltage crowbar
5: interface conversion circuit 6: impedance matching circuit
7:DSP control module 8: power supply
9: human-computer interaction interface 10:FLASH storage chip
11:ARM storage chip 12: tested lead
The 13:DSP controller
Embodiment
Below in conjunction with embodiment and accompanying drawing portable aircraft lead general performance test of the present invention is made a detailed description.
As shown in Figure 1, portable aircraft lead general performance test of the present invention comprises: electric parameter measurement circuit 1, high-speed a/d Acquisition Circuit 2, low pressure burst pulse radiating circuit 3, overvoltage crowbar 4, interface conversion circuit 5, impedance matching circuit 6, DSP control module 7, power supply 8, human-computer interaction interface 9; Wherein: described low pressure burst pulse radiating circuit 3, impedance matching circuit 6, interface conversion circuit 5, tested lead 12, overvoltage crowbar 4 and high-speed a/d Acquisition Circuit 2 are connected in series successively; the output terminal of described high-speed a/d Acquisition Circuit 2 connects DSP control module 7; described low pressure burst pulse radiating circuit 3 also connects DSP control module 7; described tested lead 12 also connects high-speed a/d Acquisition Circuit 2 by electric parameter measurement circuit 1, and described power supply 8 is connected DSP control module 7 respectively with human-computer interaction interface 9.Described DSP control module 7 includes dsp controller 13 and the FLASH storage chip 10 that links to each other with dsp controller 13 respectively, ARM storage chip 11, and described high-speed a/d Acquisition Circuit 2, low pressure burst pulse radiating circuit 3, power supply 8 and human-computer interaction interface 9 are connected the dsp controller 13 in the DSP control module 7 respectively.
In portable aircraft lead general performance test of the present invention:
Electric parameter measurement circuit 1 is that to adopt model be the chip of ICL7139, and the parameter extraction of the combined-voltage of tested lead 12, electric current, impedance, electric capacity is come out, and links to each other with high-speed a/d Acquisition Circuit 2 again, and analog signal conversion is become digital signal;
It is the chip of ADS7844 that high-speed a/d Acquisition Circuit 2 adopts model; it links to each other with overvoltage crowbar 4 with dsp controller 13 in the DSP control module 7; finish mould/number conversion, and transmitting of will collecting given DSP control module 7 with reflected signal and done subsequent treatment.
Low pressure burst pulse radiating circuit 3 is that the employing model is the chip of MAX038, for whole portable aircraft lead general performance test provides basis of signals, link to each other, variable-width adjustable for generation of the periodicity amplitude narrow along the high-speed pulse signal respectively with dsp controller 13 in impedance matching circuit 6 and the DSP control module 7;
Overvoltage crowbar 4 links to each other with high-speed a/d Acquisition Circuit 2 and tested lead 12 respectively, thereby has ensured the security performance of system;
Interface conversion circuit 5, adopt current loop circuit, include 555 time base circuits 54,4N26 photoelectrical coupler 51 and 74HC14 chip 53, adjustable resistance 52, as shown in Figure 2,4N26 photoelectrical coupler 51, adjustable resistance 52,74HC14 chip 53 and 555 time base circuits 54 are connected in series successively, and wherein the output of the input end of 4N26 photoelectrical coupler 51 connection impedance matching circuit 6,555 time base circuits 54 connects tested lead 12.Interface conversion circuit 5 links to each other with tested lead 12 with impedance matching circuit 6 respectively, finishes the switching of 12 in impedance matching circuit 6 and tested lead;
Impedance matching circuit 6 adopts adjustable resistance, link to each other with interface conversion circuit 5 with low pressure burst pulse radiating circuit 3 respectively, utilize the R-C coupling principle, according to the output impedance of the characteristic impedance regulating system of lead 12 to be measured, undistorted in transmission course to guarantee signal;
Dsp controller 13 in the DSP control module 7, link to each other with low pressure burst pulse radiating circuit 3, high-speed a/d Acquisition Circuit 2, power supply 8, human-computer interaction interface 9 respectively, it is under the input information control of human-computer interaction interface 9, the data that adopt the signal processing method analysis to collect, come failure judgement type and position by the singular point of seeking data, and demonstrate waveform, in addition, electrical quantity obtains after also can handling through it;
Power supply 8 links to each other with DSP control module 7, supplies with as the power supply of equipment;
Human-computer interaction interface 9 links to each other with dsp controller 13 in the DSP control module 7, is used for showing fault type, locating information and electrical quantity, and realizes the information input to total system;
FLASH storage chip 10 links to each other with dsp controller 13, is used for storage program and partial data information;
RAM storage chip 11 links to each other with dsp controller 13, is used for the outer storage space of expansion DSP sheet.
As shown in Figure 3, when portable aircraft lead general performance test of the present invention is worked, at first each functional module of this tester is carried out initialization, carrying out program subsequently judges, whether Rule of judgment is for being electric parameter measurement, if electric parameter measurement, the A/D Acquisition Circuit is gathered the signal that the electric parameter measurement circuit transmits, the signal that collects is admitted to DSP control core subsequently, and carry out filtering and handle and corresponding mathematical operation, draw the accordingly result of the electrical quantity of surveying, show at little liquid crystal display at last; If judge it is not electric parameter measurement, then the DSP triggering pulse generator is launched required low pressure narrow pulse signal, pulse signal transfers to the place, trouble spot through lead and reflects, reflected signal is gathered via the A/D Acquisition Circuit, send into DSP control core subsequently and carry out corresponding filtering and wavelet de-noising processing, obtain comparatively desirable reflection configuration, can draw fault type according to reflection configuration, reflection configuration is carried out least square method and relevant treatment, can draw position of failure point, equally the gained result is presented on the little liquid crystal display at last.Next program further judges whether to stop this operation, if, end operation then; If not, turn back to the electric parameter measurement judging unit and carry out next time program loop.
Claims (3)
1. portable aircraft lead general performance test, it is characterized in that, comprising: electric parameter measurement circuit (1), high-speed a/d Acquisition Circuit (2), pulse radiating circuit (3), overvoltage crowbar (4), interface conversion circuit (5), impedance matching circuit (6), DSP control module (7), power supply (8), human-computer interaction interface (9); Wherein: described pulse radiating circuit (3); impedance matching circuit (6); interface conversion circuit (5); tested lead (12); overvoltage crowbar (4) and high-speed a/d Acquisition Circuit (2) are connected in series successively; the output terminal of described high-speed a/d Acquisition Circuit (2) connects DSP control module (7); described pulse radiating circuit (3) also connects DSP control module (7); described tested lead (12) also connects high-speed a/d Acquisition Circuit (2) by electric parameter measurement circuit (1); described power supply (8) is connected DSP control module (7) respectively with human-computer interaction interface (9); described electric parameter measurement circuit (1) is that the employing model is the chip of ICL7139; combined-voltage with tested lead (12); electric current; impedance; the parameter extraction of electric capacity comes out; link to each other with high-speed a/d Acquisition Circuit (2) again, analog signal conversion is become digital signal.
2. portable aircraft lead general performance test according to claim 1, it is characterized in that, described DSP control module (7) includes dsp controller (13) and the FLASH storage chip (10) that links to each other with dsp controller (13) respectively, ARM storage chip (11), and described high-speed a/d Acquisition Circuit (2), pulse radiating circuit (3), power supply (8) and human-computer interaction interface (9) are connected the dsp controller (13) in the DSP control module (7) respectively.
3. portable aircraft lead general performance test according to claim 1, it is characterized in that, described interface conversion circuit (5) includes: Chuan Jie 4N26 photoelectrical coupler (51), adjustable resistance (52), 74HC14 chip (53) and 555 time base circuits (54) successively, wherein, the input end of described 4N26 photoelectrical coupler (51) connects impedance matching circuit (6), and the output of described 555 time base circuits (54) connects tested lead (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110316971 CN102435914B (en) | 2011-10-18 | 2011-10-18 | Portable aircraft wire comprehensive performance tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110316971 CN102435914B (en) | 2011-10-18 | 2011-10-18 | Portable aircraft wire comprehensive performance tester |
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| CN102435914A CN102435914A (en) | 2012-05-02 |
| CN102435914B true CN102435914B (en) | 2013-09-25 |
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| CN 201110316971 Expired - Fee Related CN102435914B (en) | 2011-10-18 | 2011-10-18 | Portable aircraft wire comprehensive performance tester |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105652196A (en) * | 2016-03-11 | 2016-06-08 | 正泰电气股份有限公司 | Circuit breaker oscillation testing device and testing method thereof |
| CN107015119B (en) * | 2017-05-12 | 2019-05-07 | 中广核核电运营有限公司 | A kind of signal cable Circuit fault diagnosis device and method |
| CN108152646B (en) * | 2017-12-01 | 2020-10-23 | 瑞斯康达科技发展股份有限公司 | Telephone interface testing device and method |
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|---|---|---|---|---|
| CN2433635Y (en) * | 1999-10-26 | 2001-06-06 | 南航(集团)汕头航空有限公司 | Testing instrument for fault of conducting wire |
| CN1700026A (en) * | 2004-05-18 | 2005-11-23 | Lg电子有限公司 | Apparatus and method of detecting breakdown of conducting wires |
| CN201583616U (en) * | 2009-12-01 | 2010-09-15 | 江苏精达里亚阿尔岗琴工程线有限公司 | Composite conductor short circuit tester |
| CN201740837U (en) * | 2010-06-25 | 2011-02-09 | 广州励丰声光科技有限公司 | Multifunctional conducting wire detecting instrument |
-
2011
- 2011-10-18 CN CN 201110316971 patent/CN102435914B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2433635Y (en) * | 1999-10-26 | 2001-06-06 | 南航(集团)汕头航空有限公司 | Testing instrument for fault of conducting wire |
| CN1700026A (en) * | 2004-05-18 | 2005-11-23 | Lg电子有限公司 | Apparatus and method of detecting breakdown of conducting wires |
| CN201583616U (en) * | 2009-12-01 | 2010-09-15 | 江苏精达里亚阿尔岗琴工程线有限公司 | Composite conductor short circuit tester |
| CN201740837U (en) * | 2010-06-25 | 2011-02-09 | 广州励丰声光科技有限公司 | Multifunctional conducting wire detecting instrument |
Non-Patent Citations (10)
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| 一种便携式智能电缆故障测试仪;高风波等;《测控技术》;20031231;第22卷(第12期);第21-23页 * |
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