CN106546841B - Aircraft electromagnetic environment Safety Margin code method - Google Patents

Aircraft electromagnetic environment Safety Margin code method Download PDF

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Publication number
CN106546841B
CN106546841B CN201610892279.8A CN201610892279A CN106546841B CN 106546841 B CN106546841 B CN 106546841B CN 201610892279 A CN201610892279 A CN 201610892279A CN 106546841 B CN106546841 B CN 106546841B
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electromagnetic
level
aircraft
safety margin
equipment
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CN106546841A (en
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方愔
侯典国
储燕
胡超
王庆国
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China Aeronautical Radio Electronics Research Institute
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China Aeronautical Radio Electronics Research Institute
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/001—Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/0807—Measuring electromagnetic field characteristics characterised by the application
    • G01R29/0814—Field 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
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/0864—Measuring electromagnetic field characteristics characterised by constructional or functional features
    • G01R29/0892—Details 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
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/005—Testing of electric installations on transport means
    • G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels

Abstract

A kind of aircraft electromagnetic environment Safety Margin code method, the high level surface current injection 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) device-dependent reflux framework is established；(4) Injection Current is calibrated comprising low level scanning and irradiation and low level surface current of equal value inject；(5) high level surface current injection method airworthiness compliance is tested.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 high level surface current injection 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) device-dependent reflux framework is established；
(4) Injection Current is calibrated comprising low level scanning and irradiation and low level surface current of equal value inject；
(5) high level surface current injection method airworthiness compliance is tested.
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, aircraft exterior electromagnetic ambient level EMEL is determinedOutsideThe number that user provides can be directlyed adopt 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, aircraft exterior electromagnetic ambient level EMEL is determinedOutsideAnalysis measurement method can be used to determine, i.e., By the various electromagnetic environments that may be met in analysis of aircraft use process, the previous engineering experience of reference, analogy is chosen wherein The most harsh typical scene of electromagnetic environment carries out in-site measurement statistics.
According to above-mentioned main feature, aircraft exterior electromagnetic ambient level EMEL is determinedOutsidePair simulation calculation can be used to determine, i.e., The most harsh typical scene progress of electromagnetic environment is as true to nature as possible, models in detail.It is all to have the contribution that compare to electromagnetic environment Radiation source will consider, determine them transmission power, frequency range, signal waveform, antenna directivity, propagation distance, On the basis of polarization direction etc. is participated in the experiment, the tribute of each field source is calculated with the lossless spatial range formula of electromagnetic wave, communication equation number value It offers, and carries out vector superposed and synthesize total electromagnetic environment.
According to above-mentioned main feature, the step of Injection Current is calibrated includes configuration suitably by test specimen earthing mode and ground connection Point position, first carries out low level irradiation, closes with the induced current in cable caliper measurements apparatus interconnection cable, then to airframe Suitable point injection low level current, is sized, makes to monitor induced current and measured value on the interconnecting cable of concern equipment It is identical, the transfer function between irradiation field strength and Injection Current is thus obtained, is extrapolated using the linear relationship between low and high level Induced current on aircraft skin under the high level irradiation field of standard requirements, this should be directly injected into current value, finally keep flying The Current injection points of machine, earthing mode and grounding point position are constant, inject the high current to aircraft skin.
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 expection or actual electromagnetic ambient level；(5) each installation electromagnetical Design of Compatibility control level is determined；(6) it accords with The assessment of conjunction property.The present invention has standardization effect, behaviour by above-mentioned method, to the work of aircraft electromagnetic environment Safety Margin The property made is strong, has good practical directiveness, can significantly improve the working efficiency for carrying out such assessment in engineering, reduction expense. It, can be with the specific descriptions in four embodiments below as the particular content of step each in the above method.
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 level Electromagnetic EnvironmentLevel ─EMELOutsideRefer to the largest enveloping for the full machine external electromagnetic environment level that aircraft is likely to be at, substantially it is considered that on aircraft skin Equal everywhere is 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
Internal electromagnetic ambient level Electromagnetic Environment Level-EMELIt is interiorRefer to that aircraft the machine is complete Portion's onboard electrical electronic system, equipment are powered on the largest enveloping for being formed by full machine electromagnetic ambient level, from compatible peace Full nargin 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) aircraft exterior electromagnetic ambient level EMEL is determinedOutside
EMELOutsideIt is the benchmark for carrying out the assessment of external electromagnetic environment compatible secure nargin.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
Aircraft exterior electromagnetic ambient level EMELOutsideAirframe shield effectiveness FSE is subtracted, each equipment installation position is just obtained Set internal electromagnetic ambient level EMELIt is interior。
EMELIt is interior=EMELOutside- FSE
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 and " internal electromagnetic ambient level EMELIt is interior- 3dB " compares
Electromagnetic susceptibility level EMSL control >=expection and " internal actual electromagnetic ambient level EMEIn L+MIt is required that" compare
If
Electromagnetic interference level EMIL control≤inside electromagnetic ambient level EMELIt is interior- 3dB
Electromagnetic susceptibility level EMSL control >=inside electromagnetic ambient level EMELIt is interior+MIt is required that
At this moment safety margin M=electromagnetic susceptibility level EMSL control-inside electromagnetic ambient level EMELIt is interiorValue be 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 Internal electromagnetic ambient level EMEL is given in the assessment of levelIt is interiorIncrease some safety factors.
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 level EOuter lowElectromagnetic Field Irradiation aircraft；
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, measure wherein induced current IIrradiate cable low；
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 the induced current I of the interconnecting cable of concern equipmentInject cable lowWith 1)~2) IIrradiate cable lowIt is identical, record this Injection Current IInfuse low；
4) above step 1 is repeated)~3) to test full band scan measurement；
5) measurement data normalizes I to unit external irradiation fieldInfuse low/EOuter low；
6) by AVHRR NDVI data to desired aircraft exterior electromagnetic ambient level EMELOutsideCarry out linear extrapolation
IInfuse high=EMELOutside×IInfuse low/EOuter low
7) to airframe injection step 6) obtained high current IInfuse high, realize that high level irradiation is replaced in electric current injection Generation.Continue induced current on the interconnecting cable of monitoring concern equipment, if also keeping linear ratio relation, confirmed inside simultaneously The equivalence of electromagnetic ambient level.
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
Ihigh=EOuter high×Ilow/EOuter low
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) electromagnetic ambient level EMEL inside each equipment installation position is determinedIt is interior
EMELIt is interiorIt is the benchmark that aircraft is assessed from compatible secure nargin, 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 internal electromagnetic ambient level EMELIt is interior。
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 Testing limiting level is internal electromagnetic ambient level EMELIt is interior；Or with the test pole of conducted susceptibility CS, radiosensitivity RS in standard It rations the power supply and is worth based on putting down, increasedd or decreased several depending on installation region situation and neighbouring specific equipment according to previous practical experience Magnitude 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 and " internal electromagnetic ambient level EMELIt is interior- 3dB " compares
Electromagnetic susceptibility level EMSL control >=expection and " internal electromagnetic ambient level EMELIt is interior+ M " compares
If
Electromagnetic interference level EMIL control≤inside electromagnetic ambient level EMELIt is interior- 3dB
Electromagnetic susceptibility level EMSL control >=inside electromagnetic ambient level EMELIt is interior+MIt is required that
At this moment safety margin M=electromagnetic susceptibility level EMSL control-inside electromagnetic ambient level EMELIt is interiorValue be 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 Internal electromagnetic ambient level EMEL is given in the assessment of levelIt is interiorIncrease some safety factors.
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 (5)

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 high level surface current injection method of border Safety Margin, steps are as follows:
(1) confirmation is by assessment system；
(2) aircraft exterior electromagnetic ambient level EMEL is determinedOutside；
(3) device-dependent reflux framework is established；
(4) with low level EOuter lowElectromagnetic Field Irradiation aircraft；
(5) the induced current I of detection concern all interconnecting cables of equipmentIrradiate cable low；
(6) low level current is injected to airframe appropriate point, is sized, make the interconnecting cable for monitoring concern equipment Induced current IInject cable lowWith IIrradiate cable lowIt is identical, record injection low level current I at this timeInfuse low；
(7) step (4)~(6) are repeated to test full band scan measurement；
(8) measurement data normalizes I to unit external irradiation fieldInfuse low/EOuter low；
(9) by AVHRR NDVI data to desired aircraft exterior electromagnetic ambient level EMELOutsideLinear extrapolation is carried out, big electricity is calculated Flow IInfuse high:
IInfuse high=EMELOutside×IInfuse low/EOuter low；
(10) the high current I that airframe injection step (9) is obtainedInfuse high, continue to feel on the interconnecting cable of monitoring concern equipment Answer electric current IIrradiate cable lowIf also keeping linear ratio relation, it confirmed internal electromagnetic ambient level EMEL simultaneouslyIt is interiorEquivalence；
(11) 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；
(12) accordance is assessed: accordance assesses the external interface from equipment, radiation and conduction two including cabinet and interconnection line Aspect substitutes into following formula and obtains its conduction, radiation safety margin symbol respectively each device data obtained by abovementioned steps Close implementations:
If: electromagnetic interference level≤inside electromagnetic ambient level EMELIt is interior- 3dB
Electromagnetic susceptibility level >=inside electromagnetic ambient level EMELIt is interior+ safety margin requires MIt is required that
Then: practical safety margin MIt is practical=electromagnetic susceptibility level-inside electromagnetic ambient level EMELIt is interior
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 Portion electromagnetic ambient level EMELOutsideRelated platform level electromagnetic compatible is quoted in the requirement of the data or Certification that are provided using user Regulation in standard provides the specific quantizating index of specific application scene.
4. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that: aircraft exterior electricity Magnetic environment level EMELOutsideIt 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: aircraft exterior electricity Magnetic environment level EMELOutsideIt is determined using simulation calculation.
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