CN106314822B - Aircraft electromagnetic environment Safety Margin code method - Google Patents
Aircraft electromagnetic environment Safety Margin code method Download PDFInfo
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- CN106314822B CN106314822B CN201610892277.9A CN201610892277A CN106314822B CN 106314822 B CN106314822 B CN 106314822B CN 201610892277 A CN201610892277 A CN 201610892277A CN 106314822 B CN106314822 B CN 106314822B
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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
- 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
- G01R29/0864—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
The invention discloses a kind of aircraft electromagnetic environment Safety Margin code methods, including the fuselage screen suitable for aircraft exterior electromagnetic environment Safety Margin is followed, steps are as follows：(1) confirm 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.The present invention by above-mentioned method, to the work of aircraft electromagnetic environment Safety Margin there is standardization effect, strong operability to have practical directiveness well, can significantly improve the working efficiency for carrying out such assessment in engineering, reduction expense.
Description
【Technical field】
The present invention relates to the electromagnetic compatibility tests applied to aircraft, particularly relate to aircraft electromagnetic environment Safety Margin
Code method.
【Background technology】
Before the aircraft development stage especially shapes, need with regard to aircraft to actually using the external electromagnetic environment met with
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 analysis, the support of experiment 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 verification regulation.Therefore it is led by electromagnetic compatibility
The way of domain routine is exactly to require directly to carry out the HIRF experiments of high field intensity radiation exposure to aircraft by definition.
But the energy-rich radiation level magnitude that the experiment of aircraft electromagnetic environment safety margin is related to is far beyond current industrial quarters
Actual tests ability level is difficult to meet these regulations with conventional test methods, there is an urgent need to seek and work out one in the industry
A little more simple and feasible alternatives.
【Invention content】
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 that a kind of aircraft electromagnetic environment Safety Margin code method includes suitable
Fuselage screen for aircraft exterior electromagnetic environment Safety Margin is followed, and this method comprises the following steps：
(1) confirm 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.
According to above-mentioned main feature, wherein when there are EMC problems according to equipment to aircraft may caused by consequence and harm
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 can be directly provided 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 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 with during analysis of aircraft use, 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, determines and simulation calculation determination can be used outside aircraft exterior electromagnetic ambient level EMEL, i.e.,
The typical scene progress most harsh to electromagnetic environment is as true to nature as possible, models in detail.It is every 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, it is true to determine that field measurement can be used in the fuselage screen efficiency presented in equipment installation position
It is fixed, to whether there is or not two kinds of situations of aircraft, outside machine different location, orientation antenna irradiated with safety equivalence level, to be closed in machine
The minimum signal level difference that (cockpit, equipment compartment etc.) receiving sensor receives at note position is to measure the fuselage screen effect ginseng in the place
Number.
According to above-mentioned main feature, it is true to determine that simulation calculation can be used in the fuselage screen efficiency presented in equipment installation position
It is fixed, electromagnetic-field simulation computation software package, such as EM3D, CST, FECO are such as used, to aircraft external and internal compositions size, material, especially
Be structure size, material in the cabin of installation concern equipment, carry out as true to nature as possible, detailed modeling, then select suitable time domain,
Frequency domain value algorithm is resolved.
According to above-mentioned main feature, it is true to determine that empirical analysis can be used in the fuselage screen efficiency presented in equipment installation position
It is fixed, i.e., estimated according to engineering experience, the shielding properties in astomous all-metal cabin is best, generally has the screen of 40dB or more to imitate；
There is the shielding properties in the metal cabin of perforation to take second place；The shielding properties in fenestrate, door metal or non-all-metal cabin is worst, generally
Only 10dB screen effects below, even enhance instead in resonant frequency, and general fuselage screen effect selection principle is：
0dB screens 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 screens 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；
Some corresponding shielding measure scenes of 12dB screens effect, as metal aeroplane band crossing cabin connector from rather than full-closed electronic set
Standby cabin, cockpit, without EMI choke grooves 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 screens 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 screens effect, as in good full-shield metal cabin.
According to above-mentioned main feature, determine in the level EMEL of each equipment installation position actual electromagnetic field to be that aircraft exterior is electric
Airframe shield effectiveness is subtracted outside magnetic environment level EMEL.
According to above-mentioned main feature, determine that each equipment actual electromagnetic Design of Compatibility control level is needed from electromagnetic susceptibility
Level Electromagnetic Susceptibility Level-EMSL is controlled and electromagnetic interference level
Electromagnetic Interference Level-consider in terms of EMIL controls two, is generally tested by the EMC of equipment
Report provides；For EMC approved apparatus up to standard, electromagnetic interference level also may be derived from the electromagnetism for conducting and radiating in GJB151A
Emission Limits, and electromagnetic susceptibility level is subject to equipment measured value.
According to above-mentioned main feature, accordance assesses the external interface from equipment, including cabinet and interconnection line radiation and
Two aspect of conduction substitutes into following formula and obtains its conduction, radiation safety respectively each device data obtained by abovementioned steps
Nargin meets implementations：
Electromagnetic interference level EMIL controls are compared with " it is expected that or -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL control with " in expected or actual electromagnetic ambient level EMEL+safety margin requires
MIt is required that" compare
If
Electromagnetic interference level EMIL controls≤expection or actual electromagnetic ambient level EMELIt is interior- 3dB
Electromagnetic susceptibility level EMSL controls >=expection or actual electromagnetic ambient level EMELIt is interior+ safety margin requires MIt is required that
At this moment practical safety margin MIt is practical=electromagnetic susceptibility level EMSL is controlled-is expected actual electromagnetic ambient level EMEL
Interior value is more than defined value, then shows that evaluated equipment/system is met the requirements.
Compared with prior art, the present invention realizes aircraft electromagnetic environment Safety Margin by above-mentioned method,
This method strong operability has practical directiveness well, can significantly improve the working efficiency for carrying out such assessment in engineering, drop
Low expense contributes to the aircraft-level seaworthiness of the civil aircraft of China's implementation at the startup to take, the development of certification work.
【Description of the drawings】
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 implementation mode】
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-effects of equal value generated and/or EUT functional performances
Equivalent Test method, mainly includes the following steps：(1) confirm by assessment system；(2) aircraft exterior electromagnetic ambient level is determined；
(3) suitable method is selected to determine the transmission function of external electromagnetic environment and electromagnetic environment at internal focus；(4) according to transmission 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 practical directiveness well, 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, commonly uses dB and indicates.The electricity of aircraft
Magnetic environment safety margin is the difference of the sensitive thresholding and environment actual interference level of airborne most sensitive equipment/system, excessively generally.
The specific electromagnetic environment safety margin of each airborne equipment/system is more paid close attention in engineering, they are general different, so aircraft
Electromagnetic environment safety margin be really each airborne equipment/system electromagnetic environment safety margin in minimum value.
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 to be same magnitude.Aircraft exterior electromagnetic environment Safety Margin includes mainly following 6 steps：
1) confirm 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 specific embodiment 1 is shown in the narration in detail of each step.
2. aircraft exterior electromagnetic environment Safety Margin (high level surface current injection method)
HIRF irradiation, which is substituted, with Bulk current injection method carries out actual test, verification.Directly to the big electricity of fuselage skin injection
Stream generates electromagnetic environment in machine needed for aircraft exterior electromagnetic environment Safety Margin, makes to be in and high level outside machine by test specimen
Under the electromagnetic stress of irradiation field equivalence, to generate same response.
It is alternate test assessment, one of advantage 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 aircrafts resonant frequency (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) 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
Resonant 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 ranges 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 substitute indirect test verification.Assessment includes mainly following 5
A step：
1) confirm 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 are carried out with the high level and accordance is assessed.
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 includes mainly following 4 steps：
(1) confirm 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 specific embodiment 4 is shown in the narration in detail of each step.
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) confirm 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.When there are EMC problems according to equipment simultaneously to aircraft may caused by consequence 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 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 spatial domain 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.Lower several method is can be used to determine.
User requires：It is flat generally to quote some correlations more for the requirement of the data or Certification that are directly provided using user
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 with during analysis of aircraft use, 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 every to electricity
Magnetic environment has the radiation source for the contribution that can compare that will consider, determine them transmission power, frequency range, signal waveform, day
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
The contribution of each field source of numerical computations, and carry 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 concerned position in machine minimum signal level difference
The fuselage screen of point imitates parameter.
Simulation calculation：Using electromagnetic-field simulation computation software package, such as EM3D, CST, FECO, 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：Estimated according to engineering experience, 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 effects below even enhance instead in resonant frequency.General fuselage screen imitates selection principle：
0dB screens 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 screens 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；
Some corresponding shielding measure scenes of 12dB screens effect, as metal aeroplane band crossing cabin connector from rather than full-closed electronic set
Standby cabin, cockpit, without EMI choke grooves 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 screens 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 screens 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
Position is expected or actual electromagnetic field level EMEL in.
In EMEL=outer-FSE of EMEL
5) each installation electromagnetical Design of Compatibility control level is determined
The EMC safety margins of so-called aircraft are 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 margins of aircraft are 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 is controlled and electromagnetic interference level Electromagnetic
Interference Level-consider in terms of EMIL controls two.It can generally be provided by the EMC test reports of equipment.For
EMC approved apparatus up to standard, the EMIL controls such as more conservative Electromagnetic Launching limit values that may be derived from conducting and radiating in GJB151A, and
EMSL controls 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 controls are compared with " it is expected that or -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL is controlled and " it is expected that or+M in actual electromagnetic ambient level EMELIt is required that" compare
If
Electromagnetic interference level EMIL controls≤expection or the interior -3dB of actual electromagnetic ambient level EMEL
In electromagnetic susceptibility level EMSL controls >=expection or actual electromagnetic ambient level EMEL+safety margin requires MIt is required that
At this moment practical safety margin M=electromagnetic susceptibility level EMSL is controlled-is expected in actual electromagnetic ambient level EMEL
Value be more than defined safety margin require 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 is：Configuration suitably by test specimen earthing mode and earth point position (with practical installation state consistency or
Carried out convenient for experiment), 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 the aircraft skin that relationship is extrapolated under the high level irradiation field that standard requires, this should be directly injected into current value.Most
It keeps the Current injection points, earthing mode and earth 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 aircrafts 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, measure wherein induced current I irradiation cables 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 monitoring
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 notes low；
4) above step 1 is repeated)~3) experiment full band scan is measured；
5) measurement data is to low outside unit external irradiation field normalization I notes low/E；
6) AVHRR NDVI data are subjected to linear extrapolation outside to desired aircraft exterior electromagnetic field level EMEL
I notes outside high=EMEL × outer the low of I notes low/E
7) to airframe injection step 6) obtained high current I note high, realizes what electric current injection irradiated high level
It substitutes.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 illustrated by taking low level current scanning method LLSC as an example.Experiment process is：Configuration is suitably grounded by test specimen
Mode and earth point position (being carried out with practical installation state consistency or convenient for experiment), first carry out low level irradiation, use strain relief clamp
Pincers measure the induced current in interconnecting cable, obtain the transfer function between induced current on irradiation field strength 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, incude
Injected value of current.Finally keep constant by the earthing mode of test specimen and earth 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 Irradiations outside default low level E by test specimen；
2) detection current clamp is stuck in away from cabinet 50mm on had interconnecting cable, measurement wherein induced current Ilow；
3) above step 1 is repeated)~2) experiment full band scan is measured；
4) measurement data is to low outside unit external irradiation field normalization Ilow/E；
5) AVHRR NDVI data are subjected to linear extrapolation to the high level field strength of code requirement
The outer low of the outer high × Ilow/E of Ihigh=E
Electric current clamp are passed through to tested interconnecting cable and incude injection step 5) obtained high level energy, realize electric current injection
To the replacement of high level irradiation, experiment is completed.
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, the various operating modes of system, equipment, thus clear interior of aircraft may
Most extreme electromagnetic environment.When there are EMC problems according to equipment simultaneously to aircraft may caused by consequence 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 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：So that whole airborne electronic equipment/electrical equipments is operated at full capacity and switches different working modes, it is 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, and the scanning frequency spectrum of focus is measured with three axis Field probes+receiver；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, and the scanning frequency spectrum of focus is measured with current probe+receiver；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 that standby installation experiment is likely encountered in the process, directly takes the examination of conducted susceptibility CS, radiosensitivity RS in standard
It is in expected electromagnetic ambient level EMEL to test limiting level；Or with the experiment 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 rationally adjusted.
Analogies of experience：Select the data with existing of similar airplane equipment scene, or appropriate amendment.
Simulation calculation：Using Large Electromagnetic simulation calculation software package, such as EM3D, CST, FECO, 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 by simplifying the when of calculating, 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 miscellaneous 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
To paying close attention to the influence of equipment.
3) each equipment actual electromagnetic Design of Compatibility control level is determined
The EMC safety margins of so-called aircraft are 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 margins of aircraft are 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 is controlled and electromagnetic interference level Electromagnetic
Interference Level-consider in terms of EMIL controls two.It can generally be provided by the EMC test reports of equipment.For
EMC approved apparatus up to standard, the EMIL controls such as more conservative Electromagnetic Launching limit values that may be derived from conducting and radiating in GJB151A, and
EMSL controls 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 controls≤expection is compared with " -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL controls >=expection is compared with "+M in actual electromagnetic ambient level EMEL "
If
- 3dB in electromagnetic interference level EMIL controls≤actual electromagnetic ambient level EMEL
+ M in electromagnetic susceptibility level EMSL controls >=actual electromagnetic ambient level EMELIt is required that
At this moment safety margin M=electromagnetic susceptibilities level EMSL controls-is expected the value in actual electromagnetic ambient level EMEL
More 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 should all belong to the guarantor of appended claims of the invention
Protect range.
Claims (9)
1. a kind of aircraft electromagnetic environment Safety Margin code method, it is characterised in that comprising suitable for aircraft exterior electromagnetism ring
The fuselage screen of border Safety Margin is followed, and steps are as follows：
(1) confirm 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 expection or actual electromagnetic ambient level are determined, it is contemplated that or actual electromagnetic ambient level is that will fly
Machine external electromagnetic environment level subtracts airframe shield effectiveness
(5) 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；
(6) accordance is assessed:Accordance assesses the external interface from equipment, includes two sides of radiation and conduction of 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 more 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
When existing EMC problems to aircraft may caused by consequence and the extent of injury, carry out the influence degree of mission task, equipment to aircraft
Functional characteristic, the inconsistency of hardware and related uncertain factor 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：It determines outside aircraft
The requirement for the 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：It determines outside aircraft
Portion's electromagnetic ambient level is determined using analysis measurement method, passes through the various electromagnetism rings that may be met with during analysis of aircraft use
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：It determines 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：It determines in equipment
The fuselage screen efficiency that installation site is presented is using field measurement determination, to whether there is or not two kinds of situations of aircraft, outside machine different location,
The antenna in orientation is irradiated with safety equivalence level, poor with receiving sensor receives at concerned position in machine minimum signal level
Fuselage screen to measure the concerned position imitates parameter.
7. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that：It determines in equipment
The fuselage screen efficiency that installation site is presented is determined using simulation calculation.
8. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that：It determines in equipment
The fuselage screen efficiency that installation site is presented is determined using empirical analysis.
9. aircraft electromagnetic environment Safety Margin code method as described in claim 1, it is characterised in that：EMC is reached
Qualified equipment is marked, electromagnetic interference level is derived from the Electromagnetic Launching limit value for conducting and radiating in GJB151A, otherwise by equipment
EMC test reports provide electromagnetic interference level, and electromagnetic susceptibility level is subject to equipment measured value.
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| 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 |
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| CN109655671B (en) * | 2018-11-21 | 2021-07-20 | 上海无线电设备研究所 | High-intensity radiation field effect test system and test method for low-level sweep current |
| 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 |
| 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 |
| CN110441618B (en) * | 2019-09-04 | 2022-03-29 | 上海无线电设备研究所 | System and method for collecting and processing HIRF (high-altitude RF) environmental data of flight route |
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| CN111398725B (en) * | 2020-04-29 | 2022-03-25 | 中国人民解放军军事科学院国防工程研究院工程防护研究所 | Equipment electromagnetic damage characterization method suitable for system electromagnetic vulnerability assessment |
| CN111812424B (en) * | 2020-05-08 | 2022-11-01 | 中国人民解放军63892部队 | Comprehensive capability assessment method under equipment whole-system threat electromagnetic environment |
| CN112114218B (en) * | 2020-09-22 | 2024-02-23 | 上海无线电设备研究所 | High-level test system for HIRF test and verification method |
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| CN103869191B (en) | 2018-04-17 |
| CN106383273B (en) | 2019-05-24 |
| CN103869191A (en) | 2014-06-18 |
| CN106314822A (en) | 2017-01-11 |
| CN106546841B (en) | 2019-12-03 |
| CN106383273A (en) | 2017-02-08 |
| CN106546841A (en) | 2017-03-29 |
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