CN106383273B - Aircraft electromagnetic environment Safety Margin code method - Google Patents

Aircraft electromagnetic environment Safety Margin code method Download PDF

Info

Publication number
CN106383273B
CN106383273B CN201610891443.3A CN201610891443A CN106383273B CN 106383273 B CN106383273 B CN 106383273B CN 201610891443 A CN201610891443 A CN 201610891443A CN 106383273 B CN106383273 B CN 106383273B
Authority
CN
China
Prior art keywords
electromagnetic
aircraft
level
safety margin
equipment
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.)
Active
Application number
CN201610891443.3A
Other languages
Chinese (zh)
Other versions
CN106383273A (en
Inventor
方愔
周伟
陶志杰
徐荟翎
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China Aeronautical Radio Electronics Research Institute
Original Assignee
China Aeronautical Radio Electronics Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by China Aeronautical Radio Electronics Research Institute filed Critical China Aeronautical Radio Electronics Research Institute
Priority to CN201410098076.2A priority Critical patent/CN103869191B/en
Priority to CN201610891443.3A priority patent/CN106383273B/en
Publication of CN106383273A publication Critical patent/CN106383273A/en
Application granted granted Critical
Publication of CN106383273B publication Critical patent/CN106383273B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01RMEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/001Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01RMEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08Measuring electromagnetic field characteristics
    • G01R29/0807Measuring electromagnetic field characteristics characterised by the application
    • G01R29/0814Field measurements related to measuring influence on or from apparatus, components or humans, e.g. in ESD, EMI, EMC, EMP testing, measuring radiation leakage; detecting presence of micro- or radiowave emitters; dosimetry; testing shielding; measurements related to lightning
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01RMEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08Measuring electromagnetic field characteristics
    • G01R29/0864Measuring electromagnetic field characteristics characterised by constructional or functional features
    • G01R29/0892Details related to signal analysis or treatment; presenting results, e.g. displays; measuring specific signal features other than field strength, e.g. polarisation, field modes, phase, envelope, maximum value
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01RMEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/005Testing of electric installations on transport means
    • G01R31/008Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels

Abstract

The invention discloses a kind of aircraft electromagnetic environment Safety Margin code methods, and the low level coupled method comprising being suitable for aircraft exterior electromagnetic environment Safety Margin, steps are as follows: (1) confirmation is by assessment system;(2) aircraft exterior electromagnetic ambient level is determined;(3) aircraft low level is scanned in the machine of determination by induced current on test specimen interconnecting cable or the transmission function of installation place external electromagnetic field;(4) induced current or installation place spatial electromagnetic field value on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level are calculated in a manner of linear extrapolation;(5) cable current injection or irradiation and accordance assessment are carried out with the result of the linear extrapolation.The present invention has standardization effect by above-mentioned method, to the work of aircraft electromagnetic environment Safety Margin, and strong operability has good practical directiveness, can significantly improve the working efficiency for carrying out such assessment in engineering, reduction expense.

Description

Aircraft electromagnetic environment Safety Margin code method
[technical field]
The present invention relates to the electromagnetic compatibility tests for being applied to aircraft, particularly relate to aircraft electromagnetic environment Safety Margin Code method.
[background technique]
Before the aircraft development stage is especially formed, need with regard to aircraft to the external electromagnetic environment for actually using experience The safety margin that adaptability and aircraft have this is assessed.It include airborne equipment, system, each level of full machine really Recognize and verify work, has both needed a set of comprehensive elaboration program and carefully planned guidance, be also relied on corresponding complete skill Document, data calculate the support of analysis, test measured result.
The requirement of electromagnetic environment safety margin is generally specified only in aircraft Airworthiness Certification file, Its Relevant Technology Standards, It gets off the plane and how to show in what electromagnetic environment condition, particularly as being in bad electromagnetic environment (with every meter of several volts of electricity Field intensity is measured) under keep how function and performance, without providing operable verifying regulation.Therefore it is led by electromagnetic compatibility The way of domain routine is exactly to require directly to carry out High-Field intense radiation irradiation HIRF test to aircraft by definition.
But the energy-rich radiation level magnitude that the test of aircraft electromagnetic environment safety margin is related to is far beyond current industry Actual tests ability level is difficult to meet these regulations with conventional test methods, there is an urgent need to seek and develop one in the industry A little more simple and feasible alternatives.
[summary of the invention]
It is existing to solve the purpose of the present invention is to provide several aircraft electromagnetic environment Safety Margin code methods Mode experimentation cost and the excessively high problem of research and development of products cost.
Purpose to realize the present invention, the present invention propose a kind of aircraft electromagnetic environment Safety Margin code method, include Suitable for the low level coupled method of aircraft exterior electromagnetic environment Safety Margin, this method comprises the following steps:
(1) confirmation is by assessment system;
(2) aircraft exterior electromagnetic ambient level is determined;
(3) aircraft low level is scanned in the machine of determination by induced current on test specimen interconnecting cable or installation place external electromagnetic field Transmission function;
(4) it is empty to go out induced current or installation place on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level for linear extrapolation Between electromagnetism field value;
(5) cable current injection or irradiation and accordance assessment are carried out with the high level.
According to above-mentioned main feature, wherein the consequence and harm that may cause when there is EMC problem according to equipment to aircraft Degree, to aircraft carry out the influence degree of mission task, the functional characteristic of equipment, hardware inconsistency and it is related not really Qualitative factor establishes each equipment importance rate and corresponding safety margin requirement.
According to above-mentioned main feature, the number that user provides can be directlyed adopt by determining outside aircraft exterior electromagnetic ambient level EMEL According to or Certification requirement, regulations in the much more general some related platform level electromagnetic compatible standards of reference also provide specific The specific quantizating index of application scenarios.
According to above-mentioned main feature, determine that analysis measurement method can be used outside aircraft exterior electromagnetic ambient level EMEL to be determined, I.e. by the various electromagnetic environments that may be met in analysis of aircraft use process, the previous engineering experience of reference, analogy chooses it The most harsh typical scene of middle electromagnetic environment carries out in-site measurement statistics.
According to above-mentioned main feature, determine that simulation calculation can be used outside aircraft exterior electromagnetic ambient level EMEL to be determined, i.e., The typical scene progress most harsh to electromagnetic environment is as true to nature as possible, models in detail.It is all to have the tribute that compare to electromagnetic environment The radiation source offered will consider, determine them transmission power, frequency range, signal waveform, antenna directivity, propagation away from On the basis of participating in the experiment from, polarization direction etc., each field source is calculated with the lossless spatial range formula of electromagnetic wave, communication equation number value Contribution, and carry out vector superposed and synthesize total electromagnetic environment.
According to above-mentioned main feature, this method is applicable in frequency range and divides LLSCI, LLSC and LLSF tri- kinds, and LLSCI is suitable for 10KHz~aircraft 1st resonance frequency, LLSC are suitable for 500kHz~400MHz that cable plays main coupling, and LLSF is applicable in In all influential 100MHz~40GHz of cabinet and cable, the method establishes electromagnetism on the airborne equipment of concern in a manner of surveying Transmission function relationship between effect and aircraft exterior electromagnetic environment, wherein LLSCI, LLSC are induced electricity on apparatus interconnection cable Stream is connected with normalization aircraft exterior electromagnetic environment, and LLSF is equipment installation place field strength and normalization aircraft exterior electromagnetism Environment connects, then transmission function linear extrapolation must be assessed and should be applied to equipment under the aircraft exterior electromagnetic environment of requirement accordingly The interior of aircraft electromagnetic stress added, to carry out substitution indirect test verifying.
Compared with prior art, the present invention realizes aircraft electromagnetic environment Safety Margin by above-mentioned method, This method strong operability has good practical directiveness, can significantly improve the working efficiency that such assessment is carried out in engineering, drop Low expense, the aircraft-level seaworthiness for facilitating the civil aircraft of China's implementation at the startup takes, the development of certification work.
[Detailed description of the invention]
Fig. 1 is the total flow diagram of the present invention.
Fig. 2 is the flow diagram for implementing the first embodiment of the present invention.
Fig. 3 is the flow diagram for implementing the second embodiment of the present invention.
Fig. 4 is the flow diagram for implementing the third embodiment of the present invention.
Fig. 5 is the flow diagram for implementing the fourth embodiment of the present invention.
[specific embodiment]
Refering to Figure 1, the present invention discloses a kind of aircraft electromagnetic environment Safety Margin code method, it is based on outer Several accommodations of portion's electromagnetic environment EME stress to the response of equal value of the EUT galvanomagnetic-effect of equal value generated and/or EUT functional performance Equivalent Test method mainly includes the following steps: (1) confirmation by assessment system;(2) aircraft exterior electromagnetic ambient level is determined; (3) suitable method is selected to determine the transmission function of electromagnetic environment at external electromagnetic environment and internal focus;(4) according to transmitting letter Number determines focus actual electromagnetic field level;(5) each installation electromagnetical Design of Compatibility control level is determined;(6) accordance is assessed. The present invention has standardization effect, strong operability, tool by above-mentioned method, to the work of aircraft electromagnetic environment Safety Margin There is good practical directiveness, the working efficiency for carrying out such assessment in engineering, reduction expense can be significantly improved.As for above-mentioned side The particular content of each step in method, can be with the specific descriptions in four embodiments below.
Safety margin Margin refers to the difference of actual interference level in sensitive thresholding and environment, and commonly using dB indicates.The electricity of aircraft Magnetic environment safety margin is the sensitive thresholding of airborne most sensitive equipment/system and the difference of environment actual interference level, excessively generally. The specific electromagnetic environment safety margin of each airborne equipment/system is more concerned about in engineering, they are general different, so aircraft Electromagnetic environment safety margin be really minimum value in the electromagnetic environment safety margin of each airborne equipment/system.
1. aircraft exterior electromagnetic environment Safety Margin (fuselage screen is followed)
This is a kind of indirect assessment method.External electromagnetic environment Electromagnetic Environment Level- EMEL refers to the largest enveloping for the full machine external electromagnetic environment level that aircraft is likely to be at outside, substantially it is considered that on aircraft skin Locate equal for same magnitude.Aircraft exterior electromagnetic environment Safety Margin mainly includes following 6 steps:
1) confirmation is by assessment system;
2) aircraft exterior electromagnetic ambient level is determined;
3) the fuselage screen efficiency presented in equipment installation position is determined;
4) each equipment installation position actual electromagnetic field level is determined;
5) each installation electromagnetical Design of Compatibility control level is determined;
6) accordance is assessed.
Estimation flow figure is as shown in Fig. 2, and each step describes in detail sees specific embodiment 1.
2. aircraft exterior electromagnetic environment Safety Margin (high level surface current injection method)
Actual test, verifying are carried out with the substitution HIRF irradiation of Bulk current injection method.Directly to the big electricity of fuselage skin injection Stream generates needed for aircraft exterior electromagnetic environment Safety Margin electromagnetic environment in machine, makes to be in by test specimen and high level outside machine Under the electromagnetic stress of irradiation field equivalence, to generate same response.
Alternate test assessment, advantage first is that an overall test is just completed at the same time to the EMC of all airborne equipments peace Full nargin assessment.Its most effective frequency of use range 10kHz~1st aircraft resonance frequency (generally aircraft maximum dimension 150~ 30 meters of corresponding electromagnetic wave half-wavelengths, 1~5MHz), it can be extended to 400MHz, then high-frequency makes bad stability.Assessment is main Including following 5 steps:
1) confirmation is by assessment system;
2) aircraft exterior electromagnetic ambient level is determined;
3) device-dependent reflux framework is established;
4) Injection Current is calibrated
A) low level scanning and irradiation;
B) low level surface current injection of equal value.
5) high level surface current injection method airworthiness compliance is tested.
Estimation flow figure as shown in figure 3, no longer illustrate in detail in view of length.
3. aircraft exterior electromagnetic environment Safety Margin (low level coupled method)
Belong to alternative, divides LLSCI, LLSC and LLSF tri- kinds by applicable frequency range.LLSCI is suitable for 10KHz~aircraft 1st Resonance frequency, LLSC are suitable for 500kHz~400MHz that cable plays main coupling, and LLSF is suitable for cabinet and cable Influential 100MHz~40GHz.The reason of overlapping of latter two method uses in 100~400MHz frequency range is major electromagnetic Coupling mechanism and field source characteristic, field source/object construction material, field source and target spacing, medium factors are closely related.Usually Cable induced current plays main coupling on flivver, and space electric field plays main coupling on big aircraft.So herein frequently General both of which is used in section, in order to avoid omit harsher electromagnetic environment scene.Pass is established in low level coupling in a manner of surveying Transmission function relationship on the airborne equipment of note between galvanomagnetic-effect and aircraft exterior electromagnetic environment, i.e., LLSCI, LLSC are equipment Induced current is connected with normalization aircraft exterior electromagnetic environment on interconnecting cable, and LLSF is equipment installation place field strength and normalizing Change aircraft exterior electromagnetic environment to connect.Transmission function linear extrapolation must assess the aircraft exterior electromagnetic environment of requirement accordingly again The interior of aircraft electromagnetic stress that equipment should be applied down, to carry out substitution indirect test verifying.Assessment mainly includes following 5 A step:
1) confirmation is by assessment system;
2) aircraft exterior electromagnetic ambient level is determined;
3) aircraft low level scanning (Injection Current, irradiation) is asked in machine by induced current or installation on test specimen interconnecting cable Locate the transmission function of external electromagnetic field;
4) it is empty to go out induced current or installation place on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level for linear extrapolation Between electromagnetism field value;
5) cable current injection or irradiation and accordance assessment are carried out with the high level.
Estimation flow figure is as shown in Fig. 4, no longer illustrates in detail in view of length.
4. interior of aircraft electromagnetic environment is assessed from compatible secure nargin
Refer to aircraft the machine whole machine in internal electromagnetic environment Electromagnetic Environment Level-EMEL On-board electrical electronic system, equipment are powered on the largest enveloping for being formed by full machine electromagnetic ambient level, abundant from compatible secure Degree assessment mainly includes following 4 steps:
(1) confirmation is by assessment system;
(2) practical (or expected) electromagnetic ambient level of each equipment installation position is determined;
(3) each equipment actual electromagnetic Design of Compatibility control level is determined;
(4) accordance is assessed
Estimation flow figure is as shown in Fig. 5, and each step describes in detail sees specific embodiment 4.
For the understanding apparent to above-mentioned method, above-mentioned method is said respectively with specific example below It is bright.
1. aircraft exterior electromagnetic environment Safety Margin of example (fuselage screen is followed)
1) confirmation is by assessment system
Consider all aircrafts of each mission phase, the various operating modes of system, equipment, thus clear interior of aircraft may Most extreme electromagnetic environment.The consequence and the extent of injury that aircraft may cause when there is EMC problem according to equipment simultaneously, to winged Machine carries out the influence degree of mission task, the functional characteristic of equipment, the inconsistency of hardware and related uncertain factor, Establish each equipment importance rate and the requirement of corresponding safety margin, usual safety level is 12dB, task level 6dB, and regular grade is 0dB;.General middle and high degree airspace electromagnetic environment is preferable, and ground or low latitude electromagnetic environment are harsher, and near airports, warship shut down first The electromagnetic environment of plate is harsher.
2) it determines outside aircraft exterior electromagnetic ambient level EMEL
It is the benchmark for carrying out the assessment of external electromagnetic environment compatible secure nargin outside EMEL.It can be used to lower several method to determine.
User requires: directlying adopt the requirement of data or Certification that user provides, general more references are some related flat Regulation in platform level electromagnetic compatible standard also has the specific quantizating index for providing specific application scene.
Analysis actual measurement: the various electromagnetic environments that may be met in analysis of aircraft use process, the previous engineering of reference, analogy Experience chooses the wherein most harsh typical scene of electromagnetic environment, carries out in-site measurement statistics.
Simulation calculation: the typical scene progress most harsh to electromagnetic environment is as true to nature as possible, models in detail.It is all to electricity Magnetic environment has the radiation source for the contribution that can compare that will consider, in the transmission power, frequency range, signal waveform, day for determining them On the basis of line directionality, propagation distance, polarization direction etc. are participated in the experiment, with the lossless spatial range formula of electromagnetic wave, communication equation Numerical value calculates the contribution of each field source, and carries out vector superposed and synthesize total electromagnetic environment.
3) the fuselage screen efficiency FSE presented in equipment installation position is determined
Integral body shield effectiveness seems excessively rough in engineering, and the fuselage showed at concerned equipment installation position Shield effectiveness more has practical value.So being defined here whether there is or not when aircraft, sensor received signal level ratio in somewhere is in machine The fuselage screen effect that the point is presented.It is determined with following several method.
Field measurement: to whether there is or not two kinds of situations of aircraft, outside machine different location, orientation antenna with safety equivalence level spoke According to being to measure the ground with (cockpit, equipment compartment etc.) receiving sensor receives at position concerned in machine minimum signal level difference The fuselage screen of point imitates parameter.
Simulation calculation: electromagnetic-field simulation computation software package, such as EM3D, CST, FECO are used, to aircraft external and internal compositions ruler Structure size, material in very little, material, the especially cabin of installation concern equipment, carry out as true to nature as possible, detailed modeling, then select It is resolved with suitable time domain, frequency domain value algorithm.
Empirical analysis: estimating according to engineering experience, and the shielding properties in astomous all-metal cabin is best, generally there is 40dB Above screen effect;There is the shielding properties in the metal cabin of perforation to take second place;The shielding in fenestrate, door metal or non-all-metal cabin Can be worst, generally only 10dB screen effect below even enhances instead in resonance frequency.General fuselage screen effect selection principle is:
0dB screen effect is corresponding without any shielding measure scene, such as non-conductive matrix material structural region, unshielded open zone Domain, structure electrical bonding are without support area etc.;
The corresponding seldom shielding measure scene of 6dB screen effect, the cockpit of the non-conductive matrix material fuselage such as only shielded on a small quantity, Edge, landing gear compartment etc. before and after wing;
12dB screen imitates some corresponding shielding measure scenes, as metal aeroplane band crossing cabin connector from rather than full-closed electronic set Standby cabin, cockpit, without EMI choke groove door and window/instrument board near zone, such as hydraulic tube, cable bundle, metal are led in these regions The current-carrying conductors such as wire casing are not on all fine electrical bonding to the crossing cabin connector passed through.
The corresponding medium shielding measure scene of 20dB screen effect, as current-carrying conductor electrical bonding is good, bunch of cables is close to metal structure The above-mentioned zone of cabling;
The corresponding fine shielding measure scene of 32dB screen effect, as in good full-shield metal cabin.
4) each equipment installation position actual electromagnetic field level is determined
Airframe shield effectiveness FSE is subtracted outside aircraft exterior electromagnetic ambient level EMEL, each equipment installation is just obtained In the level EMEL of position actual electromagnetic field.
In EMEL=outer-FSE of EMEL
5) each installation electromagnetical Design of Compatibility control level is determined
The EMC safety margin of so-called aircraft is too general, and the equipment of different importance rates has the requirement of different safety margins, The equipment of same hierarchically secure margin requirement also has different practical safety margins.So the EMC safety margin of aircraft is final It will specifically implement in each equipment.The electromagnetic Compatibility Design of every equipment controls level, needs from electromagnetic susceptibility electricity Flat Electromagnetic Susceptibility Level-EMSL control and electromagnetic interference level Electromagnetic Interference Level-consider in terms of EMIL control two.It can generally be provided by the EMC test report of equipment.For EMC approved apparatus up to standard, the EMIL control such as more conservative Electromagnetic Launching limit value that may be derived from conducting and radiating in GJB151A, and EMSL control should then be subject to equipment measured value.
6) accordance is assessed
Set about in terms of the external interface-- cabinet and interconnection line of equipment are to radiation and conduction two, respectively by front Each device data that a few section methods obtain, substitution following formula obtains its conduction, radiation safety margin meets implementations.
Electromagnetic interference level EMIL control≤expection is compared with " -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL control >=expection and the " interior+M of actual electromagnetic ambient level EMELIt is required that" compare
If
- 3dB in electromagnetic interference level EMIL control≤actual electromagnetic ambient level EMEL
+ M in electromagnetic susceptibility level EMSL control >=actual electromagnetic ambient level EMELIt is required that
At this moment safety margin M=electromagnetic susceptibility level EMSL controls-is expected the value in actual electromagnetic ambient level EMEL Greater than defined value MIt is required that, then show that evaluated equipment/system is met the requirements.
Here not only consider to be assessed from the electromagnetic susceptibility level of safety margin definition, also add to Electromagnetic Launching The assessment of level, to some safety factors of increase in internal electromagnetic ambient level EMEL.
2. aircraft exterior electromagnetic environment Safety Margin of example (high level surface current injection method)
Experiment process are as follows: configuration suitably by test specimen earthing mode and grounding point position (with practical installation state consistency or Carried out convenient for test), low level irradiation is first carried out, with the induced current in cable caliper measurements apparatus interconnection cable, then to flying Machine fuselage appropriate point injects low level current, is sized, make to monitor on the interconnecting cable of concern equipment induced current with The measured value is identical, thus obtains the transfer function between irradiation field strength and Injection Current.Using linear between low and high level Induced current on aircraft skin under the high level irradiation field of relationship extrapolation standard requirements, this should be directly injected into current value.Most It keeps the Current injection points, earthing mode and grounding point position of aircraft constant afterwards, which is injected to aircraft skin.Inductive step It is rapid as follows:
1) with low Electromagnetic Field Irradiation aircraft outside low level E;
2) induced current of detection concern all interconnecting cables of equipment, is stuck in current clamp away from cable under test at cabinet 50mm On, wherein induced current I irradiates cable low for measurement;
3) to airframe appropriate point (common injection/outflow point pair: head-vertical fin end, head-left/right horizontal tail end, machine Head-left/right wingtip, wingtip-wingtip, keypoint part both sides etc.) injection low level current, it is sized, makes to monitor To concern equipment interconnecting cable induced current I injection cable low with 1)~2) I irradiation cable low it is identical, it is electric to record this injection It flows I and infuses low;
4) above step 1 is repeated)~3) to test full band scan measurement;
5) measurement data is to low outside unit external irradiation field normalization I note low/E;
6) AVHRR NDVI data are subjected to linear extrapolation to desired aircraft exterior electromagnetic field level EMEL outside
I infuses outside high=EMEL × outer the low of I note low/E
7) to airframe injection step 6) obtained high current I note high, realizes what electric current injection irradiated high level Substitution.Continue induced current on the interconnecting cable of monitoring concern equipment, if also keeping linear ratio relation, confirmed electricity simultaneously The equivalence of magnetic environment.
3. aircraft exterior electromagnetic environment Safety Margin (low level coupled method) of example
Only it is illustrated by taking low level current scanning method LLSC as an example.Experiment process are as follows: configuration is suitably grounded by test specimen Mode and grounding point position (carrying out with practical installation state consistency or convenient for test), first carry out low level irradiation, use strain relief clamp Induced current in pincers measurement interconnecting cable, obtains the transfer function on irradiation field strength and interconnecting cable between induced current.Benefit Induced current in interconnecting cable, that is, incude under the high level irradiation field for standard requirements of being extrapolated with the linear relationship between low and high level Injected value of current.Finally keep constant by the earthing mode of test specimen and grounding point position, it will corresponding magnitude electric current through cable clamp Induction injection is transmitted in interconnecting cable.Induction step is as follows:
1) with low Electromagnetic Field Irradiation outside default low level E by test specimen;
2) it will test current clamp to be stuck in away from interconnecting cable had at cabinet 50mm, measure wherein induced current Ilow;
3) above step 1 is repeated)~2) to test full band scan measurement;
4) measurement data is to low outside unit external irradiation field normalization Ilow/E;
5) high level field strength of the AVHRR NDVI data to code requirement is subjected to linear extrapolation
The outer low of the outer high × Ilow/E of Ihigh=E
Injection step 5 is incuded by electric current clamp to tested interconnecting cable) obtained high level energy, realize electric current injection To the substitution of high level irradiation, test is completed.
4. interior of aircraft electromagnetic environment of example is assessed from compatible secure nargin
1) confirmation is by assessment system
Consider all aircrafts of each mission phase, the various operating modes of system, equipment, thus clear interior of aircraft may Most extreme electromagnetic environment.The consequence and the extent of injury that aircraft may cause when there is EMC problem according to equipment simultaneously, to winged Machine carries out the influence degree of mission task, the functional characteristic of equipment, the inconsistency of hardware and related uncertain factor, Establish each equipment importance rate and the requirement of corresponding safety margin, usual safety level is 12dB, task level 6dB, and regular grade is 0dB;
2) it determines in practical (or expected) the electromagnetic ambient level EMEL of each equipment installation position
It is the benchmark that aircraft is assessed from compatible secure nargin in EMEL, can be used to lower several method and determine.
Field measurement: making whole airborne electronic equipment/electrical equipments operate at full capacity and switches different working modes, main to investigate The limit work such as high-power, the possible most strong transmitting of heavy load equipment, most fast level change rate, most fast power consumption/load switching rate Make state.When frequency f >=100MHz, the area equipments such as head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold are chosen Nearby space is ambient level sampled measurements point to cabinet, with three axis Field probes+receiver measurement focus scanning frequency spectrum;Frequency When f≤400MHz, all connector ends of area equipments such as head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold are chosen Interconnecting cable is ambient level sampled measurements point, with current probe+receiver measurement focus scanning frequency spectrum;To scan frequency spectrum Largest enveloping be in expected electromagnetic ambient level EMEL.
Analysis estimation: system/device level electromagnetic compatible testing standard GJB151A/152A has fully taken into account airborne set The electromagnetic environment being likely encountered during standby installation test, directly takes the examination of conducted susceptibility CS, radiosensitivity RS in standard Limiting level is tested as in expected electromagnetic ambient level EMEL;Or with the test of conducted susceptibility CS, radiosensitivity RS in standard It is worth based on limiting level, depending on installation region situation and neighbouring specific equipment, according to previous practical experience, if increaseing or decreasing Dry measure value is reasonably adjusted.
Analogies of experience: the data with existing of similar airplane equipment scene, or appropriate amendment are selected.
Simulation calculation: Large Electromagnetic simulation calculation software package, such as EM3D, CST, FECO are used, to fuselage interior knot Structure size, material, size, trend, the material of the interior laying interconnecting cable of cabin, installation site, size, the material of airborne equipment, Electrical property of equipment etc. assesses object, environment, boundary condition and carries out as true to nature as possible, detailed modeling.When selecting suitable again Domain, frequency domain value algorithm resolve and obtain a result.The transceiver with antenna can first be considered when calculating by simplifying, by transmitter spoke Power, receiver receiving sensitivity, dual-mode antenna directional diagram and spacing, transmitting-receiving frequency and bandwidth are penetrated, transmitting-receiving fundamental wave, harmonic wave are calculated Between that may be present interfere with each other influence;Transmitter is considered further that other equipment, according to transmitter transmission power, transmitting antenna Directional diagram, transmitting antenna go out to emit signal to equipment installation position, fuselage screen efficiency is paid close attention to using communication distance equation calculation Influence to concern equipment.
3) each equipment actual electromagnetic Design of Compatibility control level is determined
The EMC safety margin of so-called aircraft is too general, and the equipment of different importance rates has the requirement of different safety margins, The equipment of same hierarchically secure margin requirement also has different practical safety margins.So the EMC safety margin of aircraft is final It will specifically implement in each equipment.The electromagnetic Compatibility Design of every equipment controls level, needs from electromagnetic susceptibility electricity Flat Electromagnetic Susceptibility Level-EMSL control and electromagnetic interference level Electromagnetic Interference Level-consider in terms of EMIL control two.It can generally be provided by the EMC test report of equipment.For EMC approved apparatus up to standard, the EMIL control such as more conservative Electromagnetic Launching limit value that may be derived from conducting and radiating in GJB151A, and EMSL control should then be subject to equipment measured value.
4) accordance is assessed
Set about in terms of the external interface-- cabinet and interconnection line of equipment are to radiation and conduction two, respectively by front Each device data that a few section methods obtain, substitution following formula obtains its conduction, radiation safety margin meets implementations.
Electromagnetic interference level EMIL control≤expection is compared with " -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL control >=expection is compared with "+M in actual electromagnetic ambient level EMEL "
If
- 3dB in electromagnetic interference level EMIL control≤actual electromagnetic ambient level EMEL
+ M in electromagnetic susceptibility level EMSL control >=actual electromagnetic ambient level EMELIt is required that
At this moment safety margin M=electromagnetic susceptibility level EMSL controls-is expected the value in actual electromagnetic ambient level EMEL Greater than defined value MIt is required that, then show that evaluated equipment/system is met the requirements.
Here not only consider to be assessed from the electromagnetic susceptibility level of safety margin definition, also add to Electromagnetic Launching The assessment of level, to some safety factors of increase in internal electromagnetic ambient level EMEL.
It, can according to the technique and scheme of the present invention and its hair it is understood that for those of ordinary skills Bright design is subject to equivalent substitution or change, and all these changes or replacement all should belong to the guarantor of appended claims of the invention Protect range.

Claims (6)

1. a kind of aircraft electromagnetic environment Safety Margin code method, it is characterised in that comprising being suitable for aircraft exterior electromagnetism ring The low level coupled method of border Safety Margin, steps are as follows:
(1) confirmation is by assessment system;
(2) aircraft exterior electromagnetic ambient level E is determinedOuter high
(3) low level E is usedOuter lowBy test specimen, measuring machine is interior by the low induced current I on test specimen interconnecting cable for scanninglow
(4) the high induced electricity on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level is calculated in a manner of linear extrapolation Flow IhighOutside=Ehigh×Ilow/EOuter low
(5) with the high induced current IhighCable current injection or irradiation are carried out, so that it is determined that each equipment installation position is expected or real Border electromagnetic ambient level;
(6) each installation electromagnetical Design of Compatibility control level is determined, it includes electromagnetic susceptibility that electromagnetic Compatibility Design, which controls level, Level and electromagnetic interference level;
(7) accordance is assessed: accordance assesses the external interface from equipment, two sides of radiation and conduction including cabinet and interconnection line Face, respectively each device data obtained by abovementioned steps, substitution following formula obtains its conduction, radiation safety margin meets Implementations:
If: electromagnetic interference level≤expection or actual electromagnetic ambient level -3dB
Electromagnetic susceptibility level >=expection or actual desired electromagnetic ambient level+safety margin require MIt is required that
Then: practical safety margin MIt is practical=electromagnetic susceptibility level-expection or actual electromagnetic ambient level
If practical safety margin MIt is practicalM is required greater than defined safety marginIt is required that, then show that evaluated equipment/system satisfaction is wanted It asks.
2. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that: gone out according to equipment The consequence and the extent of injury that may cause when existing EMC problem to aircraft carry out the influence degree of mission task, equipment to aircraft The inconsistency and related uncertain factor of functional characteristic, hardware establish each equipment importance rate and corresponding safety Margin requirement.
3. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that: determine outside aircraft The requirement of data or Certification that portion's electromagnetic ambient level is provided using user, quotes some related platform level electromagnetic compatible marks Regulation in standard also has the specific quantizating index for providing specific application scene.
4. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that: determine outside aircraft Portion's electromagnetic ambient level is determined using analysis measurement method, passes through the various electromagnetism rings that may be met in analysis of aircraft use process Border, the previous engineering experience of reference, analogy choose the wherein most harsh typical scene of electromagnetic environment, carry out in-site measurement statistics.
5. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that: determine outside aircraft Portion's electromagnetic ambient level is determined using simulation calculation.
6. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that: the low level coupling Legal applicable frequency range divides LLSCI, LLSC and LLSF tri- kinds, and LLSCI is suitable for resonance frequency of 10KHz~aircraft, and LLSC is suitable Play 500kHz~400MHz of main coupling for cable, LLSF be suitable for cabinet and all influential 100MHz of cable~ 40GHz, the method establish the biography on the airborne equipment of concern between galvanomagnetic-effect and aircraft exterior electromagnetic environment in a manner of surveying Delivery function relationship, wherein LLSCI, LLSC contact induced current on apparatus interconnection cable and normalization aircraft exterior electromagnetic environment Get up, and LLSF connects equipment installation place field strength with normalization aircraft exterior electromagnetic environment, then transmission function line accordingly Property extrapolate assessment require aircraft exterior electromagnetic environment under should to equipment apply interior of aircraft electromagnetic stress, to carry out Substitute indirect test verifying.
CN201610891443.3A 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method Active CN106383273B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201410098076.2A CN103869191B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method
CN201610891443.3A CN106383273B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610891443.3A CN106383273B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
CN201410098076.2A Division CN103869191B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method

Publications (2)

Publication Number Publication Date
CN106383273A CN106383273A (en) 2017-02-08
CN106383273B true CN106383273B (en) 2019-05-24

Family

ID=50907938

Family Applications (4)

Application Number Title Priority Date Filing Date
CN201610891443.3A Active CN106383273B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method
CN201610892279.8A Active CN106546841B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method
CN201410098076.2A Active CN103869191B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method
CN201610892277.9A Active CN106314822B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method

Family Applications After (3)

Application Number Title Priority Date Filing Date
CN201610892279.8A Active CN106546841B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method
CN201410098076.2A Active CN103869191B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method
CN201610892277.9A Active CN106314822B (en) 2014-03-17 2014-03-17 Aircraft electromagnetic environment Safety Margin code method

Country Status (1)

Country Link
CN (4) CN106383273B (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105197253B (en) * 2015-08-14 2017-12-12 中国航空工业集团公司西安飞机设计研究所 A kind of wing Material Stiffened Panel margin of safety computational methods
CN105676020A (en) * 2015-12-31 2016-06-15 陕西海泰电子有限责任公司 System-level radiation safety margin test system and method
CN107918703B (en) * 2017-11-10 2021-04-20 天津航天机电设备研究所 Design method for wide-band radio frequency receiving satellite unintentional radiation emission limit value
CN108196132B (en) * 2017-11-21 2020-03-17 中国船舶重工集团公司第七一0研究所 Method for evaluating electromagnetic compatibility in system
CN108646110B (en) * 2018-05-10 2020-08-18 中国人民解放军陆军工程大学 Method for testing and evaluating safety margin of strong-field electromagnetic radiation of actual electric explosion device
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
CN109655671A (en) * 2018-11-21 2019-04-19 上海无线电设备研究所 Low level scans the high high radiation field effect test system and test method of electric current
CN110581730A (en) * 2019-08-30 2019-12-17 中国航空工业集团公司沈阳飞机设计研究所 Electromagnetic spectrum distribution diagram and generation method and device thereof
CN110441618A (en) * 2019-09-04 2019-11-12 上海无线电设备研究所 A kind of system and method for flight route HIRF environmental data collecting and processing

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101436221A (en) * 2008-12-02 2009-05-20 北京航空航天大学 Airplane complete machine electromagnetic compatible digitalization model system
CN101710160A (en) * 2009-12-25 2010-05-19 中国舰船研究设计中心 Method for measuring electromagnetic compatibility margin of electronic and electric equipment
CN102156234A (en) * 2011-03-28 2011-08-17 中国舰船研究设计中心 Method for measuring electromagnetic safety margin of electric initiating explosive device in radar scanning environment
CN102981064A (en) * 2012-10-09 2013-03-20 中国人民解放军63892部队 Aircraft external radio frequency electromagnetic environment prediction method and prediction system
CN103308801A (en) * 2013-06-04 2013-09-18 上海无线电设备研究所 Ground test method for full-aircraft electromagnetic compatibility of commercial aircraft
CN103455680A (en) * 2013-07-01 2013-12-18 陕西海泰电子有限责任公司 Prediction analysis system and analysis method for EMC (Electro Magnetic Compatibility) in system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0516265A1 (en) * 1991-05-09 1992-12-02 Siemens Plessey Electronic Systems Limited Improvements in or relating to aircraft landing systems
US5490090A (en) * 1994-06-14 1996-02-06 The United States Of America As Represented By The Secretary Of The Army Two tone test method for determining frequency domain transfer
US6037782A (en) * 1998-02-20 2000-03-14 Hewlett-Packard Company Automatic adjustment of cables which aids in set-up of equipment under test for electromagnetic compatibility measurements
CN103616595B (en) * 2013-11-29 2015-12-02 中国航空无线电电子研究所 Return flow line method to set up in a kind of aircraft surfaces pulse current injectingt test

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101436221A (en) * 2008-12-02 2009-05-20 北京航空航天大学 Airplane complete machine electromagnetic compatible digitalization model system
CN101710160A (en) * 2009-12-25 2010-05-19 中国舰船研究设计中心 Method for measuring electromagnetic compatibility margin of electronic and electric equipment
CN102156234A (en) * 2011-03-28 2011-08-17 中国舰船研究设计中心 Method for measuring electromagnetic safety margin of electric initiating explosive device in radar scanning environment
CN102981064A (en) * 2012-10-09 2013-03-20 中国人民解放军63892部队 Aircraft external radio frequency electromagnetic environment prediction method and prediction system
CN103308801A (en) * 2013-06-04 2013-09-18 上海无线电设备研究所 Ground test method for full-aircraft electromagnetic compatibility of commercial aircraft
CN103455680A (en) * 2013-07-01 2013-12-18 陕西海泰电子有限责任公司 Prediction analysis system and analysis method for EMC (Electro Magnetic Compatibility) in system

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
EMC安全裕度评估方法探讨;宋文武 等;《舰船电子工程》;19981231(第4期);48-52、44
低电平耦合技术在飞机级试验中的应用;胡平道;《微波学报》;20100831;58-61
飞行器外部电磁环境分析与辐射安全裕度试验方法研究;张学宇 等;《遥测遥控》;20100331;第31卷(第2期);7-11

Also Published As

Publication number Publication date
CN106314822B (en) 2018-08-10
CN106314822A (en) 2017-01-11
CN103869191B (en) 2018-04-17
CN106383273A (en) 2017-02-08
CN106546841B (en) 2019-12-03
CN103869191A (en) 2014-06-18
CN106546841A (en) 2017-03-29

Similar Documents

Publication Publication Date Title
Chung et al. Application of phase detection frequency domain reflectometry for locating faults in an F-18 flight control harness
Song et al. Detection and location of multiple wiring faults via time–frequency-domain reflectometry
CN102749539A (en) Fast electromagnetic compatibility test and diagnosis system with quantization electromagnetic interference
JP3006383B2 (en) Radio immunity test apparatus, radio immunity evaluation method, and radio wave irradiation unit
Grassi et al. Use of double bulk current injection for susceptibility testing of avionics
CN104155536B (en) The system and method that integrity test is carried out to the power grid in aircraft
Hill et al. Radiated emissions and immunity of microstrip transmission lines: Theory and reverberation chamber measurements
RU2414053C2 (en) Apparatus and method of determining interference field strength in aeroplane
US8143903B2 (en) Resonance scanning system and method for testing equipment for electromagnetic resonances
CN101533049B (en) Current radiation transmitting device for measuring cable
US10829243B2 (en) Lightning protection for aircraft antenna avionics
Jobava et al. Simulation of low-frequency magnetic fields in automotive EMC problems
CN108132390B (en) Method and system for improving field intensity in reverberation room and simulating composite field electromagnetic environment
CN105929252B (en) The method and apparatus that external radiation disturbance assessment is carried out to vehicle
CN105281016B (en) A kind of unmanned aerial vehicle onboard antenna arrangement design and verification method
Foged et al. Bringing numerical simulation and antenna measurements together
RU106393U1 (en) Mobile automated complex of simulation of radio electronic situation and control of parameters of radio interference station and radio-electronic exploration complexes
CN103308801A (en) Ground test method for full-aircraft electromagnetic compatibility of commercial aircraft
Armstrong et al. Investigation of the electromagnetic interference threat posed by a wireless network inside a passenger aircraft
US7915898B1 (en) Integrated cable/connector shielding surveillance system
CN102176689A (en) Method for determining isolation between antennas
US9459300B2 (en) Internal line replaceable unit high intensity radiated field detector
Rasek et al. Correlation of direct current injection (DCI) and free-field illumination for HIRF certification
CN106872831B (en) Interference source determines method in highly sensitive antenna of receiving device band in microwave load satellite
CN102510313A (en) Method for measuring communication 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
GR01 Patent grant
GR01 Patent grant