CN106546841A - Aircraft electromagnetic environment Safety Margin code method - Google Patents
Aircraft electromagnetic environment Safety Margin code method Download PDFInfo
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- CN106546841A CN106546841A CN201610892279.8A CN201610892279A CN106546841A CN 106546841 A CN106546841 A CN 106546841A CN 201610892279 A CN201610892279 A CN 201610892279A CN 106546841 A CN106546841 A CN 106546841A
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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
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- 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
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- 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
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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
- G01R31/005—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
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- General Physics & Mathematics (AREA)
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- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
A kind of aircraft electromagnetic environment Safety Margin code method, comprising the high level surface current injection method suitable for aircraft exterior electromagnetic environment Safety Margin, step is as follows：(1) confirm by assessment system；(2) determine aircraft exterior electromagnetic ambient level；(3) set up device-dependent backflow framework；(4) Injection Current calibration, which includes low level scanning and irradiation with low level surface current injection of equal value；(5) high level surface current injection method airworthiness compliance test.The present invention is worked to aircraft electromagnetic environment Safety Margin and is acted on standardization by above-mentioned method, strong operability, and with good practical directiveness, can significantly improve carries out operating efficiency, the reduction expense of such assessment in engineering.
Description
【Technical field】
The present invention relates to be applied to the electromagnetic compatibility test of aircraft, aircraft electromagnetic environment Safety Margin is particularly related to
Code method.
【Background technology】
Before the aircraft development stage especially shapes, need with regard to aircraft to the external electromagnetic environment of actually used experience
Adaptability, and the margin of safety that aircraft possesses to this is estimated.It includes airborne equipment, system, each aspect of full machine really
Recognize and verify work, both needed a set of comprehensive elaboration program and carefully planned guidance, be also relied on corresponding complete skill
Document, data calculate analysis, the support of test measured result.
The requirement of electromagnetic environment margin of safety is specify only in airborne vehicle Airworthiness Certification file, Its Relevant Technology Standards typically,
Get off the plane in what electromagnetic environment condition and how to show, particularly as being (electric with per meter some volts in bad electromagnetic environment
Field intensity is measuring) under keep how function and performance, without providing exercisable checking code.Therefore press electromagnetic compatibility neck
The conventional way in domain, is exactly to require by definition directly to carry out aircraft the test of high field intensity radiation exposure HIRF.
But the energy-rich radiation level value that the test of aircraft electromagnetic environment margin of safety is related to is far beyond current industrial quarters
Actual tests ability level, i.e., be difficult to meet these regulations with conventional test methods, in the industry in the urgent need to seeking and working out one
A little more simple and feasible alternatives.
【The content of the invention】
It is an object of the invention to provide several aircraft electromagnetic environment Safety Margin code methods, existing to solve
Mode experimentation cost and the problem of research and development of products high cost.
To realize the object of the invention, the present invention proposes a kind of aircraft electromagnetic environment Safety Margin code method, comprising
Suitable for the high level surface current injection method of aircraft exterior electromagnetic environment Safety Margin, the method comprises the steps：
(1) confirm by assessment system；
(2) determine aircraft exterior electromagnetic ambient level；
(3) set up device-dependent backflow framework；
(4) Injection Current calibration, which includes low level scanning and irradiation with low level surface current injection of equal value；
(5) high level surface current injection method airworthiness compliance test.
According to above-mentioned principal character, wherein the consequence being likely to result in aircraft when there are EMC problems according to equipment and harm
Degree, the influence degree of mission that aircraft is carried out task, the functional characteristic of equipment, the inconsistency of hardware and relevant not true
Qualitative factor, sets up each equipment importance rate and correspondence margin of safety is required.
According to above-mentioned principal character, the number that directly can be given using user outside aircraft exterior electromagnetic ambient level EMEL is determined
According to or Certification requirement, the much more general regulations quoted in some related platform level electromagnetic compatible standards are also given specific
The concrete quantizating index of application scenarios.
According to above-mentioned principal character, determine,
I.e. by the various electromagnetic environments that may be met with during analysis of aircraft use, reference, class choose which than conventional engineering experience
The most harsh typical scene of middle electromagnetic environment, carries out in-site measurement statistics.
According to above-mentioned principal character, determine, i.e.,
The most harsh typical scene of electromagnetic environment is carried out it is as true to nature as possible, model in detail.It is every to have tribute of comparing to electromagnetic environment
The radiation source offered will consider, it is determined that they transmission power, frequency range, signal waveform, antenna directivity, propagation away from
On the basis of participating in the experiment from, polarised 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 principal character, include the step of Injection Current is calibrated configuration suitably by test specimen earthing mode and ground connection
Point position, first carries out low level irradiation, with the induced-current in cable caliper measurements apparatus interconnection cable, then airframe is closed
A suitable point injection low level current, is sized, induced-current and the measured value on the interconnecting cable for making monitor concern equipment
It is identical, the transfer function between irradiation field intensity 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 that standard is required, this should be directly injected into current value, finally keep flying
The Current injection points of machine, earthing mode and earth point position are constant, and the high current is injected to aircraft skin.
Compared with prior art, the present invention realizes aircraft electromagnetic environment Safety Margin by above-mentioned method,
This method strong operability, with good practical directiveness, can significantly improve carries out operating efficiency, the drop of such assessment in engineering
Low expense, the aircraft-level seaworthiness for contributing to the civil aircraft of China's implementation at the startup takes, the development of certification work.
【Description of the drawings】
Fig. 1 is the total schematic flow sheet of the present invention.
Fig. 2 is the schematic flow sheet for implementing the first embodiment of the present invention.
Fig. 3 is the schematic flow sheet for implementing the second embodiment of the present invention.
Fig. 4 is the schematic flow sheet for implementing the third embodiment of the present invention.
Fig. 5 is the schematic flow sheet for implementing the fourth embodiment of the present invention.
【Specific embodiment】
Refer to shown in Fig. 1, the present invention discloses a kind of aircraft electromagnetic environment Safety Margin code method, be based on outer
Some accommodations of the response of equal value of galvanomagnetic-effect of equal value and/or EUT functional performances that portion's electromagnetic environment EME stress is produced to EUT
Equivalent Test method, mainly comprises the steps：(1) confirm by assessment system；(2) determine aircraft exterior electromagnetic ambient level；
(3) transmission function of electromagnetic environment at external electromagnetic environment and internal focus is determined from suitable method；(4) according to transmission letter
Number determines focus actual electromagnetic field level；(5) determine each installation electromagnetical Design of Compatibility control level；(6) accordance assessment.
The present invention is worked to aircraft electromagnetic environment Safety Margin and is acted on standardization by above-mentioned method, strong operability, tool
There is practical directiveness well, can significantly improve carries out operating efficiency, the reduction expense of such assessment in engineering.As for above-mentioned side
The particular content of each step in method, the specific descriptions in four embodiments that can be below.
Margin of safety Margin refers to the difference of sensitive thresholding and actual interference level in environment, and conventional dB is represented.The electricity of aircraft
Magnetic environment margin of safety is the difference of the sensitive thresholding with environment actual interference level of airborne most sensitive equipment/system, excessively generally.
The concrete electromagnetic environment margin of safety of each airborne equipment/system is paid close attention in engineering more, they are general different, so aircraft
Electromagnetic environment margin of safety be really minimum of a value in the electromagnetic environment margin of safety 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-
Refer to the largest enveloping of the full machine external electromagnetic environment level that aircraft is likely to be at outside EMEL, substantially it is considered that locating on aircraft skin
Place is equal for same value.Aircraft exterior electromagnetic environment Safety Margin mainly includes following 6 steps：
1) confirm by assessment system；
2) determine aircraft exterior electromagnetic ambient level；
3) determine the fuselage screen efficiency presented in equipment installation site；
4) determine each equipment installation site actual electromagnetic field level；
5) determine each installation electromagnetical Design of Compatibility control level；
6) accordance assessment.
As shown in Figure 2, specific embodiment 1 is shown in the narration in detail of each step to estimation flow figure.
2. aircraft exterior electromagnetic environment Safety Margin (high level surface current injection method)
HIRF irradiation is substituted with Bulk current injection method carries out actual test, checking.The big electricity that directly fuselage skin is injected
Stream, generates needed for aircraft exterior electromagnetic environment Safety Margin electromagnetic environment in machine, make by test specimen in the outer high level of machine
Under irradiation field electromagnetic stress of equal value, so as to produce same response.
It is that alternate test is assessed, one of advantage is that an overall test is just pacified while completing the EMC to all airborne equipments
Full nargin assessment.Its most effective usage frequency scope 10kHz～1st aircraft resonant frequencies (generally aircraft maximum dimension 150～
30 meters of corresponding electromagnetic wave half-wavelengths, 1～5MHz), 400MHz is can be extended to, then high-frequency makes bad stability.Assessment is main
Including following 5 steps：
1) confirm by assessment system；
2) determine aircraft exterior electromagnetic ambient level；
3) set up device-dependent backflow framework；
4) Injection Current calibration
A) low level scanning and irradiation；
B) low level surface current injection of equal value.
5) high level surface current injection method airworthiness compliance test.
Estimation flow figure is as shown in figure 3, in view of length is no longer illustrated in detail.
3. aircraft exterior electromagnetic environment Safety Margin (low level coupled method)
Category alternative, by tri- kinds of LLSCI, LLSC and LLSF of applicable frequency range point.LLSCI is applied to 10KHz～aircraft 1st
Resonant frequency, LLSC are applied to 500kHz～400MHz that cable plays main coupling, and LLSF is applied to cabinet and cable
Influential 100MHz～40GHz.Latter two method overlaps the reason for using in 100～400MHz frequency ranges is, major electromagnetic
Coupling mechanism is closely related with field source characteristic, field source/object construction material, field source and target distance, medium factors.Generally
On flivver, cable induction electric current plays main coupling, and on big aircraft, space electric field plays main coupling.So here frequency
In section, general both of which is used, in order to avoid omit harsher electromagnetic environment scene.Low level coupling sets up pass in the mode of surveying
Transmission function relation on the airborne equipment of note between galvanomagnetic-effect and aircraft exterior electromagnetic environment, i.e., LLSCI, LLSC are equipment
On interconnecting cable, induced-current is connected with normalization aircraft exterior electromagnetic environment, and LLSF is equipment installation place field intensity 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, so as to carry out substituting indirect test checking.Assessment mainly includes following 5
Individual step：
1) confirm by assessment system；
2) determine aircraft exterior electromagnetic ambient level；
3) aircraft low level scanning (Injection Current, irradiation) is asked in machine by induced-current or installation on test specimen interconnecting cable
The transmission function of place's external electromagnetic field；
4) linear extrapolation goes out induced-current or installation place sky on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level
Between electromagnetism field value；
5) cable current injection or irradiation, and accordance assessment are carried out with the high level.
Estimation flow figure as shown in Figure 4, in view of length is no longer illustrated in detail.
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
The largest enveloping of the full machine electromagnetic ambient level formed by on-board electrical electronic system, equipment energization work, which is abundant from compatible secure
Degree assessment mainly includes following 4 steps：
(1) confirm by assessment system；
(2) determine actual (or expected) electromagnetic ambient level of each equipment installation site；
(3) determine each equipment actual electromagnetic Design of Compatibility control level；
(4) accordance assessment
As shown in Figure 5, specific embodiment 4 is shown in the narration in detail of each step to estimation flow figure.
It is 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) confirm by assessment system
Consider all aircrafts of each mission phase, system, the various mode of operations of equipment, thus clear and definite interior of aircraft may
Most extreme electromagnetic environment.Consequence aircraft being likely to result in when there are EMC problems according to equipment simultaneously and the extent of injury, to flying
Machine carries out the influence degree of mission task, the functional characteristic of equipment, the inconsistency of hardware and relevant uncertain factor,
Set up each equipment importance rate and correspondence margin of safety is required, usual safe level is 12dB, and task level is 6dB, and regular grade is
0dB；.Preferably, ground or low latitude electromagnetic environment are harsher for general middle and high degree spatial domain electromagnetic environment, and near airports, warship shut down first
The electromagnetic environment of plate is harsher.
2) determine 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.May be used to lower several method to determine.
User requires：The requirement of the data or Certification that are directly given using user, general some correlations of many references are flat
Regulation in platform level electromagnetic compatible standard, also has the concrete quantizating index for providing application-specific scene.
Analysis actual measurement：The various electromagnetic environments that may be met with during analysis of aircraft use, reference, class are than conventional engineering
Experience, chooses the wherein most harsh typical scene of electromagnetic environment, carries out in-site measurement statistics.
Simulation calculation：The most harsh typical scene of electromagnetic environment is carried out it is as true to nature as possible, model in detail.It is every to electricity
The radiation source that magnetic environment has contribution of can comparing will consider, it is determined that they transmission power, frequency range, signal waveform, day
On the basis of line directionality, propagation distance, polarised direction etc. are participated in the experiment, with the lossless spatial range formula of electromagnetic wave, communication equation
The contribution of each field source of numerical computations, and carry out vector superposed and synthesize total electromagnetic environment.
3) determine fuselage screen efficiency FSE presented in equipment installation site
In engineering, integral body shield effectiveness seems excessively rough, and the fuselage that concerned equipment installed position presents
Shield effectiveness more has practical value.So when definition whether there is aircraft here, in machine, sensor received signal level ratio in somewhere is
The fuselage screen effect that the point is presented.Determined with following several method.
Field measurement：To whetheing there is two kinds of situations of aircraft, outside machine, the antenna in diverse location, orientation is with safety equivalence level spoke
According to the minimum signal level difference that (passenger cabin, equipment compartment etc.) reception sensor is received at concerned position with machine is as the measurement ground
The fuselage screen effect parameter of point.
Simulation calculation：Using electromagnetic-field simulation computation software package, such as EM3D, CST, FECO etc., to aircraft external and internal compositionses chi
Very little, material, especially installs cabin inner structure size, the material of concern equipment, carries out modeling as true to nature as possible, detailed, then select
Resolved with suitable time domain, frequency domain value algorithm.
Empirical analysis：Estimated according to engineering experience, the shielding properties in astomous all-metal cabin preferably, typically has 40dB
Screen effect above；The shielding properties for having the metal cabin of perforation is taken second place；The metal of fenestrate, door or the shielding in non-all-metal cabin
Can be worst, the screen effect of general only below 10dB even strengthens on the contrary in resonant frequency.General fuselage screen imitates selection principle：
0dB screens effect correspondence is 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 little shielding measure scene of 6dB screens effect correspondence, the driving cabin of the non-conductive matrix material fuselage of such as only a small amount of shielding,
Edge, landing gear compartment etc. before and after wing；
12dB screens effect correspondence some shielding measure scenes, such as the band crossing cabin joint of metal aeroplane from rather than full-closed electronic set
For cabin, driving cabin, without EMI choke grooves door and window/instrument board near zone, in these regions, such as hydraulic tube, cable bundle, metal are led
On the current－carrying conductors such as the wire casing not all very well crossing cabin joint extremely passed through by electrical bonding.
The medium shielding measure scene of 20dB screens effect correspondence, such as current－carrying conductor electrical bonding are good, bunch of cables presses close to metal structure
The above-mentioned zone of cabling；
The fine shielding measure scene of 32dB screens effect correspondence, such as in good full-shield metal cabin.
4) determine each equipment installation site actual electromagnetic field level
Airframe shield effectiveness FSE is deducted outside aircraft exterior electromagnetic ambient level EMEL, just obtain each equipment and install
In the level EMEL of position actual electromagnetic field.
In EMEL=outer-FSE of EMEL
5) determine each installation electromagnetical Design of Compatibility control level
The EMC margins of safety of so-called aircraft are too general, and the equipment of different importance rates has the requirement of different margins of safety,
The equipment of same hierarchically secure margin requirement also has different actual margins of safety.So the EMC margins of safety of aircraft are final
Specifically implemented on each equipment.The electromagnetic Compatibility Design control level of every equipment, needs from electromagnetic susceptibility electricity
Flat Electromagnetic Susceptibility Level-EMSL is controlled and electromagnetic interference level Electromagnetic
Interference Level-consider in terms of EMIL controls two.Typically can be provided by the EMC test reports of equipment.For
EMC approved apparatus up to standard, its EMIL control such as more conservative Electromagnetic Launching limit value for being retrieved from conduction and radiation in GJB151A, and
EMSL controls then should be defined by equipment measured value.
6) accordance assessment
From the external interface-- cabinet and interconnection line of equipment so as to radiating and setting about in terms of conducting two, respectively by above
Each device data that a few section methods are obtained, substitution below equation obtain its conduction, radiation safety margin and meet implementations.
Electromagnetic interference level EMIL controls≤be expected to compare with " -3dB in actual electromagnetic ambient level EMEL "
The electromagnetic susceptibility level EMSL controls >=expected and " interior+M of actual electromagnetic ambient level EMELRequire" compare
If
- 3dB in electromagnetic interference level EMIL control≤actual electromagnetic ambient levels EMEL
+ M in electromagnetic susceptibility level EMSL control >=actual electromagnetic ambient levels EMELRequire
At this moment margin of safety M=electromagnetic susceptibility level EMSL controls-is expected the value in actual electromagnetic ambient level EMEL
More than value M of regulationRequire, then show that evaluated equipment/system meets and require.
Here not only consider from the electromagnetic susceptibility level of safety margin definition to be estimated, also add to Electromagnetic Launching
The assessment of level, to increasing some safety factors in internal electromagnetic ambient level EMEL.
2. aircraft exterior electromagnetic environment Safety Margin of example (high level surface current injection method)
Experiment process is：Configuration suitably receive test specimen earthing mode and earth point position (with actual installation state consistency or
It is easy to test to carry out), 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, on the interconnecting cable for making monitor concern equipment induced-current with
The measured value is identical, thus obtains the transfer function between irradiation field intensity and Injection Current.Using linear between low and high level
Induced-current on aircraft skin under the high level irradiation field that relation extrapolation standard is required, this should be directly injected into current value.Most
Keep Current injection points, earthing mode and the earth point position of aircraft constant afterwards, the high current is injected to aircraft skin.Inductive step
It is rapid as follows：
1) with the outer low Electromagnetic Field Irradiation aircrafts of low level E；
2) induced-current of all interconnecting cables of concern equipment is detected, the cable under test at cabinet 50mm is stuck in current clamp
On, measure wherein induced-current I irradiation cable low；
3) to airframe appropriate point, (conventional injection/outflow point is right：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 monitoring
Induced-current I injection cable low to the interconnecting cable of concern equipment are identical with 1)～I irradiation cable low 2), record this injection electric
Stream I note low；
4) repeat above step 1)～3) to test full band scan measurement；
5) measurement data low outer to unit external irradiation field normalization I note low/E；
6) by AVHRR NDVI data to carrying out linear extrapolation outside the aircraft exterior electromagnetic field level EMEL that requires
Outside I note high=EMEL × the outer low of I note low/E
7) the high current I note high for 6) obtaining to airframe implantation step, realizes that electric current is injected to high level irradiation
Substitute.Continue induced-current on the interconnecting cable of monitoring concern equipment, if also keeping linear ratio relation, confirm electricity simultaneously
The equivalence of magnetic environment.
3. aircraft exterior electromagnetic environment Safety Margin (low level coupled method) of example
Only illustrate by taking low level current scanning method LLSC as an example.Experiment process is：Configuration is suitable to be grounded by test specimen
Mode and earth point position (with actual installation state consistency or be easy to test to carry out), first carry out low level irradiation, use strain relief clamp
Induced-current in pincers measurement interconnecting cable, obtains the transfer function between induced-current on irradiation field intensity and interconnecting cable.Profit
With induced-current in interconnecting cable under the high level irradiation field of the linear relationship extrapolation standard requirement between low and high level, that is, sense
Injected value of current.Finally keep receiving the earthing mode of test specimen and earth point position constant, Jing cables clamp will correspondence value electric current
Sensing injection is transmitted in interconnecting cable.Induction step is as follows：
1) test specimen is received with the outer low Electromagnetic Field Irradiations of default low level E；
2) detection current clamp is stuck at cabinet 50mm on all interconnecting cables, measures wherein induced-current Ilow；
3) repeat above step 1)～2) to test full band scan measurement；
4) measurement data low outer to unit external irradiation field normalization Ilow/E；
5) by AVHRR NDVI data the high level field intensity of code requirement is carried out the outer high of linear extrapolation Ihigh=E ×
The outer low of Ilow/E
The high level energy that 5) implantation step obtains is sensed by electric current clamp to tested interconnecting cable, realizes that electric current injects
Replacement to high level irradiation, completes test.
4. interior of aircraft electromagnetic environment of example is assessed from compatible secure nargin
1) confirm by assessment system
Consider all aircrafts of each mission phase, system, the various mode of operations of equipment, thus clear and definite interior of aircraft may
Most extreme electromagnetic environment.Consequence aircraft being likely to result in when there are EMC problems according to equipment simultaneously and the extent of injury, to flying
Machine carries out the influence degree of mission task, the functional characteristic of equipment, the inconsistency of hardware and relevant uncertain factor,
Set up each equipment importance rate and correspondence margin of safety is required, usual safe level is 12dB, and task level is 6dB, and regular grade is
0dB；
2) determine in actual (or expected) the electromagnetic ambient level EMEL of each equipment installation site to be that aircraft is certainly compatible in EMEL
The benchmark of Safety Margin, may be used to lower several method and determines.
Field measurement：Whole airborne electronic equipment/electrical equipments are made to operate at full capacity and switch different working modes, it is main to investigate
The limit works such as the possible most strong transmitting of high-power, heavy load equipment, most fast level rate of change, most fast power consumption/load switching rate
Make state.During frequency f >=100MHz, the area equipments such as the head/each equipment compartment of fuselage/tail, driving cabin, main cabin, cargo hold are chosen
Nearby space is ambient level sampled measurements point to cabinet, measures the scanning frequency spectrum of focus with three axle Field probes+receiver；Frequency
During f≤400MHz, all connector ends of area equipment such as the head/each equipment compartment of fuselage/tail, driving cabin, main cabin, cargo hold are chosen
Interconnecting cable is ambient level sampled measurements point, measures the scanning frequency spectrum of focus with current probe+receiver；To scan frequency spectrum
Largest enveloping in expected electromagnetic ambient level EMEL.
Analysis is estimated：System/device level electromagnetic compatible testing standard GJB151A/152A has fully taken into account airborne setting
The electromagnetic environment being likely encountered during standby installation test, directly takes conducted susceptibility CS, the examination of radiosensitivity RS in standard
Limiting level is tested 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 concrete equipment, according to conventional practical experience, if increaseing or decreasing
Dry measure value carries out Reasonable adjustment.
Analogies of experience：From the data with existing of similar airplane equipment scene, or appropriate amendment.
Simulation calculation：Using Large Electromagnetic simulation calculation software kit, such as EM3D, CST, FECO etc., fuselage interior is tied
Structure size, material, lay the size of interconnecting cable, trend, material in cabin, the installation site of airborne equipment, size, material,
The assessment object such as electrical property of equipment, environment, boundary condition carry out modeling as true to nature as possible, detailed.When selecting suitable again
Domain, frequency domain value algorithm carry out resolving and obtain a result.Simplify and the transceiver with antenna can be first considered when calculating, by emitter 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 is calculated
Between that may be present interfere impact；Emitter is considered further that to miscellaneous equipment, according to emitter transmission power, transmitting antenna
Directional diagram, transmitting antenna calculate transmission signal using communication distance equation to equipment installation site, fuselage screen efficiency is paid close attention to
Impact to paying close attention to equipment.
3) determine each equipment actual electromagnetic Design of Compatibility control level
The EMC margins of safety of so-called aircraft are too general, and the equipment of different importance rates has the requirement of different margins of safety,
The equipment of same hierarchically secure margin requirement also has different actual margins of safety.So the EMC margins of safety of aircraft are final
Specifically implemented on each equipment.The electromagnetic Compatibility Design control level of every equipment, needs from electromagnetic susceptibility electricity
Flat Electromagnetic Susceptibility Level-EMSL is controlled and electromagnetic interference level Electromagnetic
Interference Level-consider in terms of EMIL controls two.Typically can be provided by the EMC test reports of equipment.For
EMC approved apparatus up to standard, its EMIL control such as more conservative Electromagnetic Launching limit value for being retrieved from conduction and radiation in GJB151A, and
EMSL controls then should be defined by equipment measured value.
4) accordance assessment
From the external interface-- cabinet and interconnection line of equipment so as to radiating and setting about in terms of conducting two, respectively by above
Each device data that a few section methods are obtained, substitution below equation obtain its conduction, radiation safety margin and meet implementations.
Electromagnetic interference level EMIL controls≤be expected to compare with " -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL controls >=be expected to compare with "+M in actual electromagnetic ambient level EMEL "
If
- 3dB in electromagnetic interference level EMIL control≤actual electromagnetic ambient levels EMEL
+ M in electromagnetic susceptibility level EMSL control >=actual electromagnetic ambient levels EMELRequire
At this moment margin of safety M=electromagnetic susceptibility level EMSL controls-is expected the value in actual electromagnetic ambient level EMEL
More than value M of regulationRequire, then show that evaluated equipment/system meets and require.
Here not only consider from the electromagnetic susceptibility level of safety margin definition to be estimated, also add to Electromagnetic Launching
The assessment of level, to increasing some safety factors in internal electromagnetic ambient level EMEL.
It is understood that for those of ordinary skills, with technology according to the present invention scheme and its can send out
Bright design in addition equivalent or change, and all these changes or replace the guarantor that should all belong to appended claims of the invention
Shield scope.
Claims (6)
1. a kind of aircraft electromagnetic environment Safety Margin code method, it is characterised in that comprising suitable for aircraft exterior electromagnetism ring
The high level surface current injection method of border Safety Margin, step are as follows：
(1) confirm by assessment system；
(2) determine aircraft exterior electromagnetic ambient level；
(3) set up device-dependent backflow framework；
(4) Injection Current calibration, which includes low level scanning and irradiation with low level surface current injection of equal value；
(5) high level surface current injection method airworthiness compliance test.
2. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1, it is characterised in that：Gone out according to equipment
Consequence aircraft being likely to result in during existing EMC problems and the extent of injury, the influence degree of mission that aircraft is carried out task, equipment
Functional characteristic, the inconsistency of hardware and relevant uncertain factor, set up each equipment importance rate and correspondence safety
Margin requirement.
3. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1, it is characterised in that：Determine outside aircraft
The requirement of data or Certification that portion's electromagnetic ambient level is given using user, quotes some related platform level electromagnetic compatible marks
Regulation in standard, also has the concrete quantizating index for providing application-specific scene.
4. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1, it is characterised in that：Determine outside aircraft
Portion's electromagnetic ambient level is determined using analysis measurement method, by the various electromagnetism rings that may be met with during analysis of aircraft use
Border, reference, class are chosen the wherein most harsh typical scene of electromagnetic environment, carry out in-site measurement statistics than conventional engineering experience.
5. aircraft electromagnetic environment Safety Margin code method as claimed 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 claimed in claim 1, it is characterised in that：Injection Current is fixed
Target step includes that configuration, suitably by test specimen earthing mode and earth point position, first carries out low level irradiation, uses electric current clamp
Induced-current in measuring apparatus interconnecting cable, then low level current is injected to airframe appropriate point, it is sized, makes prison
Measure induced-current on the interconnecting cable of concern equipment identical with the measured value, thus obtain between irradiation field intensity and Injection Current
Transfer function, using between low and high level linear relationship extrapolation standard require high level irradiation field under aircraft skin on
Induced-current, this should be directly injected into current value, finally keep Current injection points, earthing mode and the earth point position of aircraft not
Become, this is injected to aircraft skin and should be directly injected into current value.
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| CN106383273A (en) | 2017-02-08 |
| CN106546841B (en) | 2019-12-03 |
| CN106314822B (en) | 2018-08-10 |
| CN103869191B (en) | 2018-04-17 |
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| CN103869191A (en) | 2014-06-18 |
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