CN103323709A - Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine - Google Patents
Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine Download PDFInfo
- Publication number
- CN103323709A CN103323709A CN2013102237394A CN201310223739A CN103323709A CN 103323709 A CN103323709 A CN 103323709A CN 2013102237394 A CN2013102237394 A CN 2013102237394A CN 201310223739 A CN201310223739 A CN 201310223739A CN 103323709 A CN103323709 A CN 103323709A
- Authority
- CN
- China
- Prior art keywords
- test
- connects
- complete machine
- indirect effect
- probe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Testing Electric Properties And Detecting Electric Faults (AREA)
Abstract
Provided is a sweep-frequency measuring system of the thunderbolt indirect effect of a low-level complete machine. The measuring system comprises a signal generation unit, a test receiving unit, a multi-channel transmission unit and a test industrial personal computer. The signal generation unit, the multi-channel transmission unit and the test industrial personal computer are connected with the test receiving unit in a circuit mode. The measuring system can be used for aircraft complete machine grade thunderbolt indirect effect tests, obtains transient response signals of key electronic and electric equipment connectors and cable bunches of aircrafts, and achieves aircraft thunderbolt protection design verification and airworthiness conformity verification.
Description
Technical field
The invention belongs to the Techniques in Electromagnetic Measurement field, be specifically related to a kind of low level complete machine thunder and lightning indirect effect sweep measurement system.
Background technology
Natural thunder and lightning effect can not be ignored, and the thunder and lightning main discharge current can be up to 200kA, and it is extremely strong to hinder and damage power.The thunder and lightning indirect effect refers to that thunder and lightning and aircraft interact and causes producing in the aircraft machine Transient Electromagnetic environment, device damage or interference that the superpotential that is caused in Electrical and Electronic equipment by thunder discharge and excess current cause.Modern aircraft adopts composite technology and microelectronics observation and control technology in a large number, and must have round-the-clock flight and ability to work, makes its easier influence that is subjected to the thunder and lightning indirect effect.So the modern aircraft lightning Protection Design is to guaranteeing that its safety is than seeming even more important in the past.
At present, aspect thunder and lightning indirect effect measurement means and measuring system, domesticly mainly carrying out corresponding research aspect the thunder and lightning indirect effect of device level or component-level, such as at indirect effect test of external electrical electronic equipment etc., time domain impulsive measurement mode is all adopted in test, the test waveform that namely is injected into aircraft surface be the contracting of standard lightning current time domain waveform than waveform, measuring system mainly adopts thunder and lightning waveform generator and oscillograph.University of Electronic Science and Technology's electronics and communication engineering specialty Guo dares to having delivered in November, 2007 engineering master thesis " aircraft thunder and lightning directly, indirect effect research ", and the component-level thunder and lightning indirect effect that paper relates in the laboratory is tested.As testpieces, adopt lightning current E ripple, A ripple to carry out the test of thunder and lightning indirect effect on aircraft forward equipment bay and flap model, measure its inner thunder and lightning electromagnetic field distribution and strength characteristics.The measuring system that adopts in the literary composition mainly comprises thunder and lightning waveform generator and trigger circuit and harmonic circuit.
Aspect the test of complete machine level thunder and lightning indirect effect, domestic relevant patent and the document also do not found at present.Because aircraft partial structurtes or the mutual influence of parts, as reasons such as load effect, electromagnetic coupled, even the critical component of aircraft or crucial electronic electric equipment have passed through the lightning protection designing requirement of device level, complete machine after can not guaranteeing to assemble meets the requirement of lightning protection safety indexes, must verify by overall test.Therefore, must provide a kind of low level complete machine thunder and lightning indirect effect sweep measurement system, be used for the test of aircraft complete machine level thunder and lightning indirect effect, for determining whether aircraft satisfies the lightning protection safety indexes and require to provide research technique.
Summary of the invention
A kind of low level complete machine thunder and lightning indirect effect sweep measurement provided by the invention system, can be used in the test of aircraft complete machine level thunder and lightning indirect effect, obtain the transient response signal of the crucial electronic electric equipment interface of aircraft, bunch of cables, realize the checking of aircraft lightning protection design verification and seaworthiness accordance.
In order to achieve the above object, the invention provides a kind of low level complete machine thunder and lightning indirect effect sweep measurement system, this measuring system comprises signal generating unit, test receiving element, hyperchannel transmission unit and test industrial computer, and signal generating unit, hyperchannel transmission unit and test industrial computer circuit are connected the test receiving element.
Described signal generating unit comprises signal generator, low-frequency power amplifier and injection cable, and the output terminal of signal generator connects the input end of low-frequency power amplifier, injects the output terminal that cable connects low-frequency power amplifier.
Described test receiving element comprises monitoring probe, voltage probe, current probe and vector network analyzer, monitoring probe connects the injection cable, the test cable of monitoring probe connects vector network analyzer, current probe connects the tested cable on the aircraft, and voltage probe connects the tested electronic electric equipment port on the aircraft.
Described hyperchannel transmission unit comprises multichannel optical fiber transmitter module, optical fiber and optic fiber transceiver module, the input end of multichannel optical fiber transmitter module connects voltage probe or current probe, the output terminal of multichannel optical fiber transmitter module is by the input end of optical fiber connection optic fiber transceiver module, and the output terminal of optic fiber transceiver module connects vector network analyzer.
Described test industrial computer connects vector network analyzer.
The present invention has the following advantages:
1, adopt the low level test system applies to the test of complete machine level, the damage of having avoided lightning current signals significantly to cause the crucial electronic electric equipment of aircraft, the output current scope of signal generating unit reaches 0.2A～1A can satisfy testing requirements, greatly reduces empirical risk;
2, low level complete machine thunder and lightning indirect effect sweep measurement system adopts vector network analyzer as the major equipment of test receiving element, compare as receiving equipment with employing oscillograph in traditional time domain measurement method, have highly sensitive, the advantage that dynamic range is big more is conducive to the test to low level signal;
3, test for the complete machine level, the testing site often reaches up to a hundred, the test waveform that low level complete machine thunder and lightning indirect effect sweep measurement system produces is the continuous wave signal of low frequency and continuous frequency sweep or stepping frequency sweep mode, adopt this measuring system to carry out the test of thunder and lightning indirect effect, can obtain the frequency field characteristic of the transient signal of tested cable and equipment interface, test figure and true lightning current waveform frequency spectrum data are multiplied each other, pass through inverse fourier transform again, can obtain cable and equipment interface transient response signal under the true thunder and lightning environment, can realize once testing the transient response that obtains any lightning current waveform, improve the dirigibility of test efficiency and test operation, reduce experimentation cost, the short form test process is conducive to Project Realization.
Description of drawings
Fig. 1 is structured flowchart of the present invention.
Embodiment
Followingly specify preferred embodiment of the present invention according to Fig. 1.
As shown in Figure 1, the invention provides a kind of low level complete machine thunder and lightning indirect effect sweep measurement system, be mainly used in the test of aircraft complete machine level thunder and lightning indirect effect, this measuring system comprises signal generating unit 1, test receiving element 2, hyperchannel transmission unit 3 and test industrial computer 4, and signal generating unit 1, hyperchannel transmission unit 3 and test industrial computer 4 circuit are connected test receiving element 2.
Signal generating unit 1 transmits for generation of the continuous wave of needs; The interface of the tested electronic electric equipment of 2 pairs of aircrafts of test receiving element carries out the transient voltage response signal measurement, tested cable is carried out the transient current response signal measure; Hyperchannel transmission unit 3 is used for the signal of a plurality of test points is carried out synchro measure and data transmission; Test industrial computer 4 is used for realizing measuring robotization control and data acquisition.
In the present embodiment, select the typical test mode of aircraft, namely the electric current injection side is chosen the nose place of aircraft, and electric current goes out the vertical tail of a little choosing aircraft, and electric current goes out a little to be grounding terminals.Before the test, aircraft directly is placed on above the metal ground connection flat board on ground, undercarriage will be taked insulation measures.
Described signal generating unit 1 comprises signal generator 11, low-frequency power amplifier 12 and injects cable 13, and the output terminal of signal generator 11 connects the input end of low-frequency power amplifier 12, injects the output terminal that cable 13 connects low-frequency power amplifier 12.
Described signal generator 11 produces the continuous wave signal of low frequency and continuous frequency sweep or stepping frequency sweep mode, after output signal process low-frequency power amplifier 12 power amplifications of signal generator 11, by injecting the injection side that cable 13 is connected to aircraft, an end that injects cable 13 has the clamp type joint, can directly clip on the metal construction of aircraft injection side, make aircraft surface form distribution of current, the simulation thunder and lightning adheres to the state of aircraft.
In the present embodiment, signal generator 1 adopts the model of the AR 40AD1 of company to realize.
The operating frequency range of signal generating unit 1 is 100Hz～50MHz, and output current amplitude minimum reaches 0.2A.
Described test receiving element 2 comprises monitoring probe 21, voltage probe 22, current probe 23 and vector network analyzer 24.
Monitoring probe 21 connects injection cable 13, and the test cable of monitoring probe 21 connects vector network analyzer 24, the tested cable that current probe 23 connects on the aircrafts, the tested electronic electric equipment port that voltage probe 22 connects on the aircrafts.
Current probe 23 is measured the transient current response signal of electronic electric equipment bunch of cables; Voltage probe 22 is measured the transient voltage response signal of electronic electric equipment port, the reception signal of vector network analyzer 24 is two channel signals, wherein, one channel signal is the reference signal that monitoring probe 21 records, and the signal of another passage is the test signal that voltage probe 22, current probe 23 record.
In the present embodiment, voltage probe 22 adopts R﹠amp; The model of the ESH2-Z2 of S company realizes; Current probe 23 adopts R﹠amp; The model of the EZ-17 of S company realizes; Vector network analyzer 24 adopts the model of the Agilent 4395A of company to realize.
Described hyperchannel transmission unit 3 comprises multichannel optical fiber transmitter module 31, optical fiber 32 and optic fiber transceiver module 33, the input end of multichannel optical fiber transmitter module 31 connects voltage probe 22 or current probe 23, the output terminal of multichannel optical fiber transmitter module 31 is by the input end of optical fiber 32 connection optic fiber transceiver modules 33, and the output terminal of optic fiber transceiver module 33 connects vector network analyzer 24.
When the test point of aircraft more for a long time, the quantity of voltage probe 22 or current probe 23 is determined according to the receiving cable number of multichannel optical fiber transmitter module 31.
Described test industrial computer 4 connects vector network analyzer 24, is used for realizing automatic measurement control and the data acquisition of the tested bunch of cables of aircraft, equipment interface transient response signal.
Although content of the present invention has been done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.After those skilled in the art have read foregoing, for multiple modification of the present invention with to substitute all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (5)
1. low level complete machine thunder and lightning indirect effect sweep measurement system, it is characterized in that, this measuring system comprises signal generating unit (1), test receiving element (2), hyperchannel transmission unit (3) and test industrial computer (4), and signal generating unit (1), hyperchannel transmission unit (3) and test industrial computer (4) circuit are connected test receiving element (2).
2. low level complete machine thunder and lightning indirect effect sweep measurement as claimed in claim 1 system, it is characterized in that, described signal generating unit (1) comprises signal generator (11), low-frequency power amplifier (12) and injects cable (13), the output terminal of signal generator (11) connects the input end of low-frequency power amplifier (12), injects the output terminal that cable (13) connects low-frequency power amplifier (12).
3. low level complete machine thunder and lightning indirect effect sweep measurement as claimed in claim 2 system, it is characterized in that, described test receiving element (2) comprises monitoring probe (21), voltage probe (22), current probe (23) and vector network analyzer (24), monitoring probe (21) connects injection cable (13), the test cable of monitoring probe (21) connects vector network analyzer (24), current probe (23) connects the tested cable on the aircraft, and voltage probe (22) connects the tested electronic electric equipment port on the aircraft.
4. low level complete machine thunder and lightning indirect effect sweep measurement as claimed in claim 3 system, it is characterized in that, described hyperchannel transmission unit (3) comprises multichannel optical fiber transmitter module (31), optical fiber (32) and optic fiber transceiver module (33), the input end of multichannel optical fiber transmitter module (31) connects voltage probe (22) or current probe (23), the output terminal of multichannel optical fiber transmitter module (31) is by the input end of optical fiber (32) connection optic fiber transceiver module (33), and the output terminal of optic fiber transceiver module (33) connects vector network analyzer (24).
5. low level complete machine thunder and lightning indirect effect sweep measurement as claimed in claim 4 system is characterized in that, described test industrial computer (4) connects vector network analyzer (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102237394A CN103323709A (en) | 2013-06-04 | 2013-06-04 | Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102237394A CN103323709A (en) | 2013-06-04 | 2013-06-04 | Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103323709A true CN103323709A (en) | 2013-09-25 |
Family
ID=49192576
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013102237394A Pending CN103323709A (en) | 2013-06-04 | 2013-06-04 | Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103323709A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105158562A (en) * | 2015-10-27 | 2015-12-16 | 上海无线电设备研究所 | Time-frequency domain data processing method for whole machine lightning indirect effect experiments |
| CN107402328A (en) * | 2016-05-20 | 2017-11-28 | 空中客车运营简化股份公司 | For evaluating the mobile system of thunderbolt seriousness |
| CN109655670A (en) * | 2018-11-21 | 2019-04-19 | 上海无线电设备研究所 | The high high radiation field effect test system and test method that low level directly drives |
| CN111239520A (en) * | 2020-02-07 | 2020-06-05 | 吉林大学 | Method for evaluating high-power microwave protection efficiency of protection circuit module |
| CN112114218A (en) * | 2020-09-22 | 2020-12-22 | 上海无线电设备研究所 | High-level test system for HIRF test and verification method |
| CN112946379A (en) * | 2021-01-15 | 2021-06-11 | 中汽研汽车检验中心（天津）有限公司 | Electromagnetic signal injection vehicle-mounted Ethernet wire harness and test method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002048829A (en) * | 2000-08-03 | 2002-02-15 | Mitsubishi Electric Corp | Impulse voltage measuring device |
| CN102081356A (en) * | 2011-01-27 | 2011-06-01 | 西北工业大学 | Flight test robust determination method for equivalent man-machine closed loop characteristic of statically unstable aircraft |
| CN102087322A (en) * | 2010-11-19 | 2011-06-08 | 北京航空航天大学 | Lightning effect test device for dynamic airplane |
| JP2011185773A (en) * | 2010-03-09 | 2011-09-22 | Japan Aerospace Exploration Agency | Optical air data sensor |
| US20120293188A1 (en) * | 2011-05-19 | 2012-11-22 | NeoVision, LLC | Apparatus and method of using impedance resonance sensor for thickness measurement |
-
2013
- 2013-06-04 CN CN2013102237394A patent/CN103323709A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002048829A (en) * | 2000-08-03 | 2002-02-15 | Mitsubishi Electric Corp | Impulse voltage measuring device |
| JP2011185773A (en) * | 2010-03-09 | 2011-09-22 | Japan Aerospace Exploration Agency | Optical air data sensor |
| CN102087322A (en) * | 2010-11-19 | 2011-06-08 | 北京航空航天大学 | Lightning effect test device for dynamic airplane |
| CN102081356A (en) * | 2011-01-27 | 2011-06-01 | 西北工业大学 | Flight test robust determination method for equivalent man-machine closed loop characteristic of statically unstable aircraft |
| US20120293188A1 (en) * | 2011-05-19 | 2012-11-22 | NeoVision, LLC | Apparatus and method of using impedance resonance sensor for thickness measurement |
Non-Patent Citations (4)
| Title |
|---|
| DOMINIQUE LEMAIRE: "A unified approach for lightning and low frequencies HIRF Transfer Functions Measurements on A380", 《ELECTROMAGNETIC COMPATIBILITY-EMC EURAPE》, 31 December 2009 (2009-12-31) * |
| 王万富等: "飞机雷电间接效应试验中的仿真技术探索", 《微波学报》, no. 3, 31 August 2012 (2012-08-31), pages 312 - 314 * |
| 胡平道: "机载电子电气系统雷电间接效应防护与验证", 《飞机设计》, vol. 29, no. 6, 31 December 2009 (2009-12-31), pages 48 - 51 * |
| 陈奇平等: "整机雷电间接效应防护试验的若干技术探讨", 《微波学报》, no. 3, 31 August 2012 (2012-08-31), pages 305 - 308 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105158562A (en) * | 2015-10-27 | 2015-12-16 | 上海无线电设备研究所 | Time-frequency domain data processing method for whole machine lightning indirect effect experiments |
| CN107402328A (en) * | 2016-05-20 | 2017-11-28 | 空中客车运营简化股份公司 | For evaluating the mobile system of thunderbolt seriousness |
| CN107402328B (en) * | 2016-05-20 | 2021-05-07 | 空中客车运营简化股份公司 | Airborne system for assessing lightning strike severity |
| CN109655670A (en) * | 2018-11-21 | 2019-04-19 | 上海无线电设备研究所 | The high high radiation field effect test system and test method that low level directly drives |
| CN109655670B (en) * | 2018-11-21 | 2021-04-02 | 上海无线电设备研究所 | Low-level direct-drive high-intensity radiation field effect test system and test method |
| CN111239520A (en) * | 2020-02-07 | 2020-06-05 | 吉林大学 | Method for evaluating high-power microwave protection efficiency of protection circuit module |
| CN112114218A (en) * | 2020-09-22 | 2020-12-22 | 上海无线电设备研究所 | High-level test system for HIRF test and verification method |
| CN112114218B (en) * | 2020-09-22 | 2024-02-23 | 上海无线电设备研究所 | High-level test system for HIRF test and verification method |
| CN112946379A (en) * | 2021-01-15 | 2021-06-11 | 中汽研汽车检验中心（天津）有限公司 | Electromagnetic signal injection vehicle-mounted Ethernet wire harness and test method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103323709A (en) | Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine | |
| Song et al. | Detection and location of multiple wiring faults via time–frequency-domain reflectometry | |
| CN205103389U (en) | High frequency partial discharge detector verification system | |
| CN101504432A (en) | Transient electromagnetic field measuring method for transforming plant | |
| CN103954858B (en) | Airborne antenna lightning effects test macro and method | |
| CN205333789U (en) | Impulse voltage test system | |
| CN109307816A (en) | Power equipment test method based on substation's hybrid electromagnetic interference simulation | |
| CN111510230A (en) | Lightning electromagnetic pulse damage effect determination method for airborne VHF communication radio station | |
| Reuter et al. | The influence of network impedance on conducted disturbances within the high-voltage traction harness of electric vehicles | |
| CN103499757A (en) | Method of detecting anti-electromagnetic interference capacity of secondary equipment of series capacitor compensation device | |
| CN104698265A (en) | High-voltage direct current transmission line corona loss measurement system | |
| CN109212358B (en) | Method for simulating electromagnetic interference generated by ground potential rise of transformer substation | |
| Shi et al. | Application of augmented spread spectrum time domain reflectometry for detection and localization of soft faults on a coaxial cable | |
| CN105158562A (en) | Time-frequency domain data processing method for whole machine lightning indirect effect experiments | |
| CN204462246U (en) | A kind of HVDC (High Voltage Direct Current) transmission line corona loss measuring system | |
| RU2656095C2 (en) | Emc test bench comprising item of equipment under test which is intended to be loaded on board aircraft | |
| CN201107357Y (en) | Ground network ground impedance test device | |
| CN107561368A (en) | A kind of measuring system and measuring method of large scale electrical power unit wideband impedance operator | |
| CN208334615U (en) | A kind of calibration equipment of Bulk current injection pilot system | |
| CN103067241A (en) | CAN bus signal transmission device and test system | |
| CN104360299A (en) | On-site wireless inspection device and method for capacitive type device on-line monitoring system | |
| CN207148223U (en) | A kind of measuring system of large scale electrical power unit wideband impedance operator | |
| CN109782101A (en) | A kind of calibration equipment and method of calibration for the test of automotive electronics conducted immunity | |
| CN204556784U (en) | A kind of circuit module measures switching device | |
| CN203012053U (en) | Testing device for impedance characteristics of high-voltage power equipment port |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130925 |