CN110765548A - Shielding attenuation measurement method and device for aircraft wire harness wave-proof sleeve - Google Patents
Shielding attenuation measurement method and device for aircraft wire harness wave-proof sleeve Download PDFInfo
- Publication number
- CN110765548A CN110765548A CN201910968003.7A CN201910968003A CN110765548A CN 110765548 A CN110765548 A CN 110765548A CN 201910968003 A CN201910968003 A CN 201910968003A CN 110765548 A CN110765548 A CN 110765548A
- Authority
- CN
- China
- Prior art keywords
- wire harness
- tested
- wave
- proof sleeve
- flowing
- 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
- 238000000691 measurement method Methods 0.000 title claims description 6
- 238000000034 method Methods 0.000 claims abstract description 17
- 238000012360 testing method Methods 0.000 claims abstract description 12
- 238000002347 injection Methods 0.000 claims description 19
- 239000007924 injection Substances 0.000 claims description 19
- 238000005259 measurement Methods 0.000 claims description 15
- 239000000523 sample Substances 0.000 claims description 9
- 238000001514 detection method Methods 0.000 claims description 2
- 238000012545 processing Methods 0.000 claims description 2
- 230000008878 coupling Effects 0.000 description 7
- 238000010168 coupling process Methods 0.000 description 7
- 238000005859 coupling reaction Methods 0.000 description 7
- 238000013461 design Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 1
- 238000002847 impedance measurement Methods 0.000 description 1
- 230000002633 protecting effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Landscapes
- Testing Relating To Insulation (AREA)
Abstract
The application provides a shielding attenuation measuring method of an aircraft wire harness wave-proof sleeve, which comprises the following steps: applying an input signal to a first tested wire harness and a second tested wire harness respectively, wherein the first tested wire harness is a tested wire harness without a wave-proof sleeve, the second tested wire harness is a tested wire harness with a wave-proof sleeve, the frequency of the input signal is a preset frequency, and the power is a preset power level; measuring the current level I flowing through the first beam under test0(f) And a current level I flowing through the second wire bundle to be tested1(f) (ii) a Using the formula S (f) 20log (I)0(f)/I1(f) And calculating the shielding attenuation S (f) of the wave-proof sleeve of the airplane wire harness.
Description
Technical Field
The invention relates to the field of measurement of shielding attenuation of a wire harness wave-proof sleeve, in particular to a method and a device for measuring shielding attenuation of an aircraft wire harness wave-proof sleeve.
Background
A large number of wire harnesses of an airplane are additionally provided with a wave-proof sleeve nowadays, and the purpose is to effectively inhibit electromagnetic interference generated by space electromagnetic environments (such as high-intensity radiation fields, lightning, static electricity and the like) to an electronic and electrical system of the airplane through cable field line coupling. Although the wave-proof sleeve has a certain electromagnetic shielding and protecting effect on the aircraft wire harness, the weight and the cost of the aircraft are increased. On the premise of meeting the requirement of electromagnetic shielding protection of the aircraft wiring harness, aircraft designers tend to design or select a wave-proof sleeve with light weight and low cost. Therefore, the shielding attenuation characteristic of the aircraft harness is obtained through the shielding attenuation measurement of the aircraft harness wave-proof sleeve, and the over-design and under-design of the electromagnetic shielding protection of the aircraft harness are avoided.
The wire harness wave-proof sleeve shielding attenuation measurement generally refers to the foreign IEC 62153-4-3 and IEC 62153-4-4 standards, and the wave-proof sleeve is placed in a specially-made coupling measuring tube by adopting a three-coaxial method to carry out transfer impedance measurement in a low frequency band and shielding attenuation measurement in a high frequency band. The coupling measuring tube is a limiting condition for carrying out measurement on the shielding attenuation characteristic of the wave-proof sleeve, and when the coupling measuring tube is not used, an airplane designer cannot adopt a three-coaxial method to measure the shielding attenuation characteristic of the wave-proof sleeve.
Disclosure of Invention
The purpose of the invention is: under the condition that three-coaxial method measurement cannot be carried out without a coupling measuring tube, a simple, convenient, easy-to-operate, accurate and efficient aircraft harness wave-proof sleeve shielding attenuation measuring method and device are provided, and the measuring frequency range is 10 kHz-400 MHz.
In a first aspect, the application provides a method for measuring shielding attenuation of an aircraft harness wave-proof sleeve, which comprises the following steps:
applying an input signal to a first tested wire harness and a second tested wire harness respectively, wherein the first tested wire harness is a tested wire harness without a wave-proof sleeve, the second tested wire harness is a tested wire harness with a wave-proof sleeve, the frequency of the input signal is a preset frequency, and the power is a preset power level;
measuring the current level I flowing through the first beam under test0(f) And a current level I flowing through the second wire bundle to be tested1(f)；
Using the formula S (f) 20log (I)0(f)/I1(f) And calculating the shielding attenuation S (f) of the wave-proof sleeve of the airplane wire harness.
Preferably, the applying the input signal to the first measured beam and the second measured beam respectively includes:
the input signal is applied to the first and second beams under test by a signal generator, a power amplifier and an injection probe, respectively.
Preferably, said measuring the current level I flowing through the first measured beam0(f) And a current level I flowing through the second wire bundle to be tested1(f) The method comprises the following steps:
measuring, on a spectrometer, the current level I flowing through the first measured beam0(f) And a current level I flowing through the second wire bundle to be tested1(f)。
Preferably, the predetermined frequency is in the range of 10kHz to 400 MHz.
In a second aspect, the present application provides a shielding attenuation measuring device of an aircraft wire harness wave-proof sleeve, which is characterized in that: the device comprises a signal injection unit, a measurement unit and a calculation unit, wherein:
the device comprises a signal injection unit, a signal detection unit and a signal processing unit, wherein the signal injection unit is used for respectively applying an input signal to a first tested wire harness and a second tested wire harness, the first tested wire harness is a tested wire harness without a wave-proof sleeve, the second tested wire harness is a tested wire harness with a wave-proof sleeve, the frequency of the input signal is a preset frequency, and the power of the input signal is a preset power level;
a measuring unit for measuring the current level I flowing through the first measured beam0(f) And a current level I flowing through the second wire bundle to be tested1(f)；
A calculation unit for using a formula S (f) of 20log (I)0(f)/I1(f) And calculating the shielding attenuation S (f) of the wave-proof sleeve of the airplane wire harness.
Preferably, the signal injection unit includes: a signal generator, a power amplifier and an injection probe.
Preferably, the measuring unit comprises a spectrometer, a coaxial load and an attenuator.
Preferably, the predetermined frequency is in the range of 10kHz to 400 MHz.
The method has the advantages that under the condition that three-coaxial-method measurement cannot be carried out without the coupling measuring tube, aircraft designers and the like can still utilize the measuring method provided by the invention to complete the shielding attenuation measurement of the wire harness wave-proof sleeve of the aircraft, and guide the aircraft designers to select the wire harness wave-proof sleeve which can meet the shielding attenuation requirement and has light weight and low cost.
Drawings
FIG. 1 is a diagram of an injection current test configuration on a tested wire harness without a wave guard sleeve.
FIG. 2 is a diagram of an injection current test configuration on a tested wire harness with a wave guard sleeve.
Detailed Description
The invention provides a method for measuring shielding attenuation of an aircraft wire harness wave-proof sleeve, which has a measurement frequency range of 10 kHz-400 MHz and is characterized in that: applying a signal with a certain power level to the measured wire harness without and with the wave-proof sleeve through the signal generator, the power amplifier and the injection probe, and respectively measuring the current level I flowing through the measured wire harness without and with the wave-proof sleeve on the frequency spectrograph0(f) And I1(f) Finally, using the formula s (f) 20log (I)0(f)/I1(f) And calculating the shielding attenuation S (f) of the wave-proof sleeve. The method can simply, conveniently and quickly measure the shielding attenuation characteristic of the anti-wave sleeve of the aircraft wire harness under the condition that three-coaxial-method measurement cannot be carried out due to the fact that no coupling measuring pipe exists, so that aircraft designers are guided to select the anti-wave sleeve of the wire harness, which can meet the shielding attenuation requirement, is light in weight and low in cost, and over-design and under-design of electromagnetic shielding protection of the aircraft wire harness are effectively avoided.
The present invention will be described in further detail with reference to the accompanying drawings and examples.
In the embodiment, the shielding attenuation characteristic of the braided belt wave shield sleeve with the type number of 103-.
Before the measurement is started, two measured wire harnesses are manufactured, namely a wire harness with the length of 1m and 2 wire cores (namely the measured wire harness 8 without the wave-proof sleeve) and a wire harness with the length of 1m and 2 wire cores (namely the measured wire harness 9 with the wave-proof sleeve) wrapped by the wave-proof sleeve.
The shielding attenuation measurement method of the aircraft wire harness wave-proof sleeve adopted by the embodiment comprises the following steps:
firstly, configuring a tested wire bundle 8 connected with a testing device and without a wave-proof sleeve according to the test of fig. 1, wherein an output port of a signal generator 1 is connected with an input port of a power amplifier 2, an output port of the power amplifier 2 is connected with an input port of a directional coupler 3, an output port of the directional coupler 3 is connected with an injection probe 7, the injection probe 7 is clamped on the tested wire bundle 8 without the wave-proof sleeve, one end of the tested wire bundle 8 without the wave-proof sleeve is connected with a coaxial load 4, the other end of the tested wire bundle is connected with an input port of an attenuator 5, the output port of the attenuator 5 is connected with an input port 62 of a spectrometer 6, and a forward power output port 31 of the directional coupler 3 is connected with an input port;
step two, adjusting the signal generator 1 to 10kHz, not modulating, increasing the applied signal level until the spectrometer 6 displays the forward power level P of the directional coupler 3 corresponding to the input interface 61w30 dBm;
step three, recording the current level I which flows through the measured wire bundle 8 without the wave-proof sleeve and corresponds to the input interface 62 of the frequency spectrograph 60(f)，f＝10kHz；
Step four, scanning the signal generator in the frequency range of 10 kHz-400 MHz, and keeping the forward power level P of the directional coupler 3wAt 30dBm, the current level I flowing through the measurement beam 8 without a sheath is recorded for the input interface 62 of the spectrometer 60(f)，f∈(10kHz,400MHz]；
Step five, connecting the test equipment and the tested wire bundle 9 with the wave-proof sleeve according to the test configuration of fig. 2, wherein the output port of the signal generator 1 is connected with the input port of the power amplifier 2, the output port of the power amplifier 2 is connected with the input port of the directional coupler 3, the output port of the directional coupler 3 is connected with the injection probe 7, the injection probe 7 is clamped on the tested wire bundle 9 with the wave-proof sleeve, one end of the tested wire bundle 9 with the wave-proof sleeve is connected with the coaxial load 4, the other end of the tested wire bundle is connected with the input port of the attenuator 5, the output port of the attenuator 5 is connected with the input port 62 of the spectrometer 6, and the forward power output port 31 of the directional coupler 3 is connected with the input port;
step six, step six is the repetition step two;
step seven, recording the current level I which flows through the measured wire bundle 9 with the wave-proof sleeve and corresponds to the input interface 62 of the frequency spectrograph 61(f)，f＝10kHz；
Step eight, scanning the signal generator in the frequency range of 10 kHz-400 MHz, and keeping the forward power level P of the directional coupler 3wAt 30dBm, the current level I flowing through the measurement beam 9 with the wave-protection sleeve, which corresponds to the input interface 62 of the spectrometer 6, is recorded1(f)，f∈(10kHz,400MHz]；
Step nine, calculating the shielding attenuation S (f) of each scanning frequency point of the wave-proof sleeve in the frequency range of 10 kHz-400 MHz as 20log (I)0(f)/I1(f) And the unit of S (f) is dB, the unit of f is MHz, and a shielding attenuation curve of the measured wave-proof sleeve is drawn in the frequency range of 10 kHz-400 MHz.
Claims (8)
1. A shielding attenuation measuring method of an aircraft wire harness wave-proof sleeve is characterized by comprising the following steps: the method comprises the following steps:
applying an input signal to a first tested wire harness and a second tested wire harness respectively, wherein the first tested wire harness is a tested wire harness without a wave-proof sleeve, the second tested wire harness is a tested wire harness with a wave-proof sleeve, the frequency of the input signal is a preset frequency, and the power is a preset power level;
measuring the current level I flowing through the first beam under test0(f) And a current level I flowing through the second wire bundle to be tested1(f)；
Using the formula S (f) 20log (I)0(f)/I1(f) And calculating the shielding attenuation S (f) of the wave-proof sleeve of the airplane wire harness.
2. The shield attenuation measurement method according to claim 1, characterized in that: the applying the input signal to the first tested beam and the second tested beam respectively specifically comprises:
the input signal is applied to the first and second beams under test by a signal generator, a power amplifier and an injection probe, respectively.
3. The shield attenuation measurement method according to claim 1, characterized in that: said measuring the current level I flowing through the first beam under test0(f) And a current level I flowing through the second wire bundle to be tested1(f) The method comprises the following steps:
measuring, on a spectrometer, the current level I flowing through the first measured beam0(f) And a current level I flowing through the second wire bundle to be tested1(f)。
4. The shield attenuation measurement method according to claim 1, characterized in that: the preset frequency range is 10 kHz-400 MHz.
5. The utility model provides a shielding decay measuring device of wave cover is prevented to aircraft pencil which characterized in that: the device comprises a signal injection unit, a measurement unit and a calculation unit, wherein:
the device comprises a signal injection unit, a signal detection unit and a signal processing unit, wherein the signal injection unit is used for respectively applying an input signal to a first tested wire harness and a second tested wire harness, the first tested wire harness is a tested wire harness without a wave-proof sleeve, the second tested wire harness is a tested wire harness with a wave-proof sleeve, the frequency of the input signal is a preset frequency, and the power of the input signal is a preset power level;
a measuring unit for measuring the current level I flowing through the first measured beam0(f) And a current level I flowing through the second wire bundle to be tested1(f)；
A calculation unit for using a formula S (f) of 20log (I)0(f)/I1(f) And calculating the shielding attenuation S (f) of the wave-proof sleeve of the airplane wire harness.
6. The shield attenuation measuring device according to claim 5, characterized in that: the signal injection unit includes: a signal generator, a power amplifier and an injection probe.
7. The shield attenuation measuring device according to claim 5, characterized in that: the measuring unit comprises a frequency spectrograph, a coaxial load and an attenuator.
8. The shield attenuation measuring device according to claim 5, characterized in that: the preset frequency range is 10 kHz-400 MHz.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910968003.7A CN110765548A (en) | 2019-10-12 | 2019-10-12 | Shielding attenuation measurement method and device for aircraft wire harness wave-proof sleeve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910968003.7A CN110765548A (en) | 2019-10-12 | 2019-10-12 | Shielding attenuation measurement method and device for aircraft wire harness wave-proof sleeve |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110765548A true CN110765548A (en) | 2020-02-07 |
Family
ID=69331681
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910968003.7A Pending CN110765548A (en) | 2019-10-12 | 2019-10-12 | Shielding attenuation measurement method and device for aircraft wire harness wave-proof sleeve |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110765548A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114264851A (en) * | 2021-12-22 | 2022-04-01 | 北京大泽科技有限公司 | Electromagnetic shielding attenuation measurement method for shielded cable |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102752061A (en) * | 2012-06-14 | 2012-10-24 | 北京无线电计量测试研究所 | Device and method for generating reference signal of phase-locked amplifier of millimeter wave attenuation measurement system |
| CN103701538A (en) * | 2013-12-20 | 2014-04-02 | 北京无线电计量测试研究所 | Attenuation measuring method for waveguide system |
| CN109375020A (en) * | 2018-11-09 | 2019-02-22 | 中国汽车技术研究中心有限公司 | A kind of test device and method of new-energy automobile high-tension cable shield effectiveness |
-
2019
- 2019-10-12 CN CN201910968003.7A patent/CN110765548A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102752061A (en) * | 2012-06-14 | 2012-10-24 | 北京无线电计量测试研究所 | Device and method for generating reference signal of phase-locked amplifier of millimeter wave attenuation measurement system |
| CN103701538A (en) * | 2013-12-20 | 2014-04-02 | 北京无线电计量测试研究所 | Attenuation measuring method for waveguide system |
| CN109375020A (en) * | 2018-11-09 | 2019-02-22 | 中国汽车技术研究中心有限公司 | A kind of test device and method of new-energy automobile high-tension cable shield effectiveness |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114264851A (en) * | 2021-12-22 | 2022-04-01 | 北京大泽科技有限公司 | Electromagnetic shielding attenuation measurement method for shielded cable |
| CN114264851B (en) * | 2021-12-22 | 2023-08-04 | 北京大泽科技有限公司 | Electromagnetic shielding attenuation measurement method for shielded cable |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103913661B (en) | Method for estimating influences on telecommunication cable E1 wire by electromagnetic disturbance | |
| Crovetti et al. | A critical assessment of the closed-loop bulk current injection immunity test performed in compliance with ISO 11452-4 | |
| Jiang et al. | A capacitive strip sensor for detecting partial discharge in 110-kV XLPE cable joints | |
| CN110596501A (en) | Performance test system of power filter under simulated actual working state | |
| Meng et al. | Fast prediction of transmission line radiated emissions using the Hertzian dipole method and line-end discontinuity models | |
| CN110261739B (en) | Cable soft fault positioning device and positioning method | |
| CN109709435B (en) | Method for measuring shielding effectiveness of high-voltage shielding cable of electric automobile | |
| CN103323709A (en) | Sweep-frequency measuring system of thunderbolt indirect effect of low-level complete machine | |
| CN110765548A (en) | Shielding attenuation measurement method and device for aircraft wire harness wave-proof sleeve | |
| CN111239520A (en) | Method for evaluating high-power microwave protection efficiency of protection circuit module | |
| CN111722015A (en) | Three-coaxial testing method for bare wire of aviation airborne shielding cable | |
| Li et al. | An experimental analysis of the effects of wiring harness during bulk current injection (BCI) test | |
| Hähner et al. | Screening effectiveness of unscreened balanced pairs | |
| Nicolae et al. | Using GTEM cells for immunity tests on electronic boards with microcontroller | |
| Johns et al. | Simulating Crosstalk and EMI in Cables. | |
| CN106405398A (en) | GIS-used partial discharge signal attenuation characteristic test system and method | |
| Schulze et al. | Improved transmission-line model for a cable with an attached suppression ferrite | |
| Jullien et al. | EMC harness design applied to helicopter engine from the model to the measurement validation | |
| CN106645875B (en) | The test macro of field wire coupled level under wide-band stationary field | |
| CN110531170A (en) | Shielded cable shielding attenuation measurement method | |
| Heidemann et al. | Using TEM waveguides according to the new IEC 61000-4-20 | |
| CN114264851B (en) | Electromagnetic shielding attenuation measurement method for shielded cable | |
| Knighten et al. | Experimental analysis of common mode currents on fibre channel cable shields due to skew imbalance of differential signals operating at 1.0625 Gb/s | |
| CN116973829B (en) | Chip pin injection waveform calibration method and device | |
| Antonini et al. | Experimental validation of circuit models for bulk current injection (BCI) test on shielded coaxial cables |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221018 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519090 AVIC general aviation industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
|
| TA01 | Transfer of patent application right |