CN106383273A - Plane electromagnetic environment safety margin evaluation procedure method - Google Patents
Plane electromagnetic environment safety margin evaluation procedure method Download PDFInfo
- Publication number
- CN106383273A CN106383273A CN201610891443.3A CN201610891443A CN106383273A CN 106383273 A CN106383273 A CN 106383273A CN 201610891443 A CN201610891443 A CN 201610891443A CN 106383273 A CN106383273 A CN 106383273A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- electromagnetic
- electromagnetic environment
- level
- safety margin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/001—Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/0807—Measuring electromagnetic field characteristics characterised by the application
- G01R29/0814—Field measurements related to measuring influence on or from apparatus, components or humans, e.g. in ESD, EMI, EMC, EMP testing, measuring radiation leakage; detecting presence of micro- or radiowave emitters; dosimetry; testing shielding; measurements related to lightning
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/0864—Measuring electromagnetic field characteristics characterised by constructional or functional features
- G01R29/0892—Details related to signal analysis or treatment; presenting results, e.g. displays; measuring specific signal features other than field strength, e.g. polarisation, field modes, phase, envelope, maximum value
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The invention discloses a plane electromagnetic environment safety margin evaluation procedure method which comprises a low level coupling method suitable for plane outside electromagnetic environment safety margin evaluation. The method comprises the steps of (1) confirming an evaluated system, (2) determining a plane outside electromagnetic environment level, (3) carrying out low level scanning on a plane to determine sensing current on a tested piece interaction cable in a plane or the transfer function in a mounting space electromagnetic field, (4) calculating the sensing current on the interaction cable corresponding to the plane outside electromagnetic environment level or the magnitude of the mounting space electromagnetic field with a mode of linear extrapolation, (5) carrying out cable current injection or irradiation with the result of the linear extrapolation and carrying out conformity assessment. Through the above method, the plane electromagnetic environment safety margin evaluation working is standardized, the operability is high, the practical guidance is good, and the working efficiency of the evaluation in the engineering can be improved significantly, and the cost can be reduced.
Description
【Technical field】
The present invention relates to being applied to the electromagnetic compatibility test of 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 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 typically specify only in airborne vehicle Airworthiness Certification file, Its Relevant Technology Standards,
Get off the plane in what electromagnetic environment condition and how to show, particularly as being (with every meter of some volts of electricity 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 it is simply that require by definition directly aircraft is carried out with 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, is 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.
【Content of the invention】
It is an object of the invention to provide several aircraft electromagnetic environment Safety Margin code methods, existing in order to solve
Mode experimentation cost and the problem of research and development of products high cost.
For realizing the object of the invention, the present invention proposes a kind of aircraft electromagnetic environment Safety Margin code method, comprises
It is applied to the low level coupled method of aircraft exterior electromagnetic environment Safety Margin, the method comprises the steps：
(1) confirm to be subject to assessment system；
(2) determine aircraft exterior electromagnetic ambient level；
(3) it is subject to induced-current or installation place external electromagnetic field on test specimen interconnecting cable in aircraft low level scanning determination machine
Transmission function；
(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 are carried out with this high level, and accordance assessment.
According to above-mentioned principal character, consequence and harm during EMC problem, aircraft being likely to result in wherein occurs according to equipment
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 corresponding margin of safety requires.
According to above-mentioned principal character, determine the number that can directly provide outside aircraft exterior electromagnetic ambient level EMEL using user
According to or Certification requirement, typically regulations quoted in some related platform level electromagnetic compatible standards more, be also given specific
The concrete quantizating index of application scenarios.
According to above-mentioned principal character, determine and can be determined using analysis measurement method outside aircraft exterior electromagnetic ambient level EMEL,
The various electromagnetic environments that may meet with during being used by analysis of aircraft, reference, class, than conventional engineering experience, choose it
Middle electromagnetic environment typical scene the harshest, carries out in-site measurement statistics.
According to above-mentioned principal character, determine and can be determined using simulation calculation outside aircraft exterior electromagnetic ambient level EMEL, that is,
Electromagnetic environment typical scene the harshest is carried out as true to nature as possible, model in detail.Every have tribute of can comparing to electromagnetic environment
The radiation source offered will consider, determine they transmission power, frequency range, signal waveform, antenna directivity, propagation away from
On the basis of participating in the experiment from, polarised direction etc., calculate each field source with electromagnetic wave lossless spatial range formula, communication equation number value
Contribution, and carry out vector superposed and synthesize total electromagnetic environment.
According to above-mentioned principal character, the method is suitable for frequency range and divides LLSCI, LLSC and LLSF tri- kinds, and LLSCI is applied to
10KHz～aircraft 1st resonant frequency, LLSC are applied to 500kHz～400MHz that cable plays main coupling, and LLSF is suitable for
In cabinet and all influential 100MHz～40GHz of cable, the method sets up electromagnetism on the airborne equipment of concern in the mode of surveying
Transmission function relation between effect and aircraft exterior electromagnetic environment, wherein LLSCI, LLSC are induced electricity on apparatus interconnection cable
Stream is connected with normalization aircraft exterior electromagnetic environment, and LLSF is equipment installation place field intensity and normalization aircraft exterior electromagnetism
Environment connects, then transmission function linear extrapolation must be assessed and equipment should be applied under the aircraft exterior electromagnetic environment of requirement accordingly
Plus interior of aircraft electromagnetic stress, thus carry out substitute indirect test checking.
Compared with prior art, the present invention by above-mentioned method it is achieved that aircraft electromagnetic environment Safety Margin,
This method strong operability, has practical directiveness well, can significantly improve operating efficiency, the fall carrying out such assessment in engineering
Low expense, the aircraft-level seaworthiness contributing to the civil aircraft of China's implementation at the startup takes, the development of certification work.
【Brief description】
Fig. 1 is the total schematic flow sheet of the present invention.
Fig. 2 is the schematic flow sheet implementing the first embodiment of the present invention.
Fig. 3 is the schematic flow sheet implementing the second embodiment of the present invention.
Fig. 4 is the schematic flow sheet implementing the third embodiment of the present invention.
Fig. 5 is the schematic flow sheet 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
Galvanomagnetic-effect of equal value and/or some accommodations of the response of equal value of EUT functional performance that portion's electromagnetic environment EME stress produces to EUT
Equivalent Test method, mainly comprises the steps：(1) confirm to be subject to 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 that each installation electromagnetical Design of Compatibility controls level；(6) accordance assessment.
The present invention, by above-mentioned method, has standardization effect, strong operability, tool to the work of aircraft electromagnetic environment Safety Margin
There is practical directiveness well, operating efficiency, the reduction expense that such assessment is carried out on engineering can be significantly improved.As for above-mentioned side
The particular content of each step in method, can specific descriptions in four embodiments below.
Margin of safety Margin refers to the difference of sensitive thresholding and actual interference level in environment, and conventional dB represents.The electricity of aircraft
Magnetic environment margin of safety is the difference with environment actual interference level for the sensitive thresholding of airborne most sensitive equipment/system, excessively generally.
The concrete electromagnetic environment margin of safety of each airborne equipment/system is more paid close attention on engineering, they are typically 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, substantially it is considered that locating on aircraft skin outside EMEL
Place equal for same value.Aircraft exterior electromagnetic environment Safety Margin mainly includes following 6 steps：
1) confirm to be subject to assessment system；
2) determine aircraft exterior electromagnetic ambient level；
3) determine the fuselage screen efficiency presenting in equipment installation site；
4) determine each equipment installation site actual electromagnetic field level；
5) determine that each installation electromagnetical Design of Compatibility controls 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)
Substitute HIRF irradiation with Bulk current injection method and carry out actual test, checking.The directly big electricity to fuselage skin injection
Stream, generates electromagnetic environment in machine needed for aircraft exterior electromagnetic environment Safety Margin, makes to be in the outer high level with machine by test specimen
Under irradiation field electromagnetic stress of equal value, thus producing same response.
It is alternate test assessment, one of advantage is that an overall test just completes the EMC peace to all airborne equipments simultaneously
Full nargin assessment.Its most effective usage frequency scope 10kHz～1st aircraft resonant frequency (generally aircraft maximum dimension 150～
30 meters of corresponding electromagnetic wave half-wavelengths, 1～5MHz), can be extended to 400MHz, then high-frequency make bad stability.Assessment is main
Including following 5 steps：
1) confirm to be subject to 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)
Belong to alternative, divide LLSCI, LLSC and LLSF tri- kinds by applicable frequency range.LLSCI is applied to 10KHz～aircraft 1st
Resonant frequency, LLSC is applied to 500kHz～400MHz that cable plays main coupling, and LLSF is applied to cabinet and cable
Influential 100MHz～40GHz.In 100～400MHz frequency range the reason the overlapping use of latter two method it 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 omitting harsher electromagnetic environment scene.Low level coupling sets up pass in the mode of surveying
Transmission function relation between galvanomagnetic-effect and aircraft exterior electromagnetic environment on the airborne equipment of note, that is, LLSCI, LLSC are equipment
On interconnecting cable, induced-current and normalization aircraft exterior electromagnetic environment connect, 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, thus carry out substituting indirect test checking.Assessment is main to include following 5
Individual step：
1) confirm to be subject to 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 are carried out with this high level, and accordance assessment.
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 the whole machine of aircraft the machine in internal electromagnetic environment Electromagnetic Environment Level-EMEL
The largest enveloping of the full machine electromagnetic ambient level that on-board electrical electronic system, equipment energising work are formed, it is abundant from compatible secure
Degree assessment is main to include following 4 steps：
(1) confirm to be subject to assessment system；
(2) determine each equipment installation site actual (or expected) electromagnetic ambient level；
(3) determine that each equipment actual electromagnetic Design of Compatibility controls 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, with specific example, above-mentioned method is said respectively below
Bright.
Example 1. aircraft exterior electromagnetic environment Safety Margin (fuselage screen is followed)
1) confirm to be subject to 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
The most extreme electromagnetic environment.Consequence and extent of injury during EMC problem, aircraft being likely to result in occurs simultaneously, to winged according to equipment
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 corresponding margin of safety requires, usual safe level is 12dB, and task level is 6dB, and regular grade is
0dB；.Typically preferably, ground or low latitude electromagnetic environment are harsher for middle and high degree spatial domain electromagnetic environment, and first shut down by near airports, warship
The electromagnetic environment of plate is harsher.
2) determine outside aircraft exterior electromagnetic ambient level EMEL
It is by the benchmark of external electromagnetic environment compatible secure nargin assessment outside EMEL.May be used to lower several method to determine.
User requires：The data being directly given using user or the requirement of Certification, typically some correlations of quoting are put down more
Regulation in platform level electromagnetic compatible standard, also has the concrete quantizating index providing application-specific scene.
Analysis actual measurement：The various electromagnetic environments that analysis of aircraft may meet with during using, reference, class are than conventional engineering
Experience, chooses wherein electromagnetic environment typical scene the harshest, carries out in-site measurement statistics.
Simulation calculation：Electromagnetic environment typical scene the harshest is carried out as true to nature as possible, model in detail.Every to electricity
The radiation source that magnetic environment has contribution of can comparing will consider, in their transmission power of determination, frequency range, signal waveform, sky
On the basis of line directionality, propagation distance, polarised direction etc. are participated in the experiment, with electromagnetic wave lossless spatial range formula, 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 presenting 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 has or not aircraft here, in machine, sensor received signal level ratio in somewhere is
The fuselage screen effect that this point presents.Determined with following several method.
Field measurement：To having or not 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 at the concerned position with machine, (passenger cabin, equipment compartment etc.) reception sensor receives is for this ground of measurement
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 as true to nature as possible, detailed modeling, 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
Above screen effect；The shielding properties having the metal cabin of perforation is taken second place；Fenestrate, door metal or the shielding in non-all-metal cabin
Can be worst, typically the only screen of below 10dB is imitated, and even strengthens on the contrary in resonant frequency.General fuselage screen imitates selection principle：
The corresponding no any shielding measure scene of 0dB screen effect, such as non-conductive matrix material structural region, unshielded open zone
Domain, structure electrical bonding no support area etc.；
The corresponding little shielding measure scene of 6dB screen effect, the driving cabin of non-conductive matrix material fuselage of such as only a small amount of shielding,
Edge, landing gear compartment etc. before and after wing；
12dB screen effect some shielding measure scenes corresponding, such as the band crossing cabin joint of metal aeroplane from rather than full-closed electronic set
Standby cabin, driving cabin, no EMI choke groove 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 crossing cabin joint that not all electrical bonding is extremely passed through very well.
The corresponding medium shielding measure scene of 20dB screen effect, such as current－carrying conductor electrical bonding are good, bunch of cables presses close to metal structure
The above-mentioned zone of cabling；
The corresponding fine shielding measure scene of 32dB screen effect, such as in good full-shield metal cabin.
4) determine each equipment installation site actual electromagnetic field level
Deducting airframe shield effectiveness FSE 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 that each installation electromagnetical Design of Compatibility controls level
The EMC margin of safety of so-called aircraft is 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 margin of safety of aircraft is final
Specifically implemented on each equipment.The electromagnetic Compatibility Design of every equipment controls level, needs from electromagnetic susceptibility electricity
Flat Electromagnetic Susceptibility Level-EMSL controls and electromagnetic interference level Electromagnetic
Interference Level-EMIL controls two aspects to consider.Typically can be provided by the EMC test report of equipment.For
EMC approved apparatus up to standard, its EMIL controls such as the more conservative Electromagnetic Launching limit value being retrieved from and conducting in GJB151A and radiate, and
EMSL control then must be defined by equipment measured value.
6) accordance assessment
External interface from equipment --- cabinet and interconnection line are thus set about in terms of radiation and conduction two, respectively by above
Each device data that a few section methods obtain, substitution below equation obtains its conduction, radiation safety margin meets implementations.
Electromagnetic interference level EMIL control≤expection is compared with " -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL controls the >=expected and " interior+M of actual electromagnetic ambient level EMELRequire" compare
If
- 3dB in electromagnetic interference level EMIL control≤actual electromagnetic ambient level EMEL
+ M in electromagnetic susceptibility level EMSL control >=actual electromagnetic ambient level EMELRequire
At this moment margin of safety M=electromagnetic susceptibility level EMSL controls-expects the value in actual electromagnetic ambient level EMEL
Value M more than regulationRequire, then show that evaluated equipment/system meets and require.
Here not only consider to be estimated from the electromagnetic susceptibility level of safety margin definition, also add to Electromagnetic Launching
The assessment of level, increases some safety factors in internal electromagnetic ambient level EMEL.
Example 2. aircraft exterior electromagnetic environment Safety Margin (high level surface current injection method)
Experiment process is：Configuration be suitably subject to test specimen earthing mode and earth point position (with actual installation state consistency or
It is easy to test to carry out), first carry out low level irradiation, 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 making monitor concern equipment induced-current with
This 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 requires, this should be directly injected into current value.?
Keep Current injection points, earthing mode and the earth point position of aircraft constant afterwards, aircraft skin is injected with this high current.Inductive step
Suddenly as follows：
1) with the outer low Electromagnetic Field Irradiation aircraft of low level E；
2) detect the induced-current of all interconnecting cables of concern equipment, be stuck in cable under test at cabinet 50mm with 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, make monitoring
Induced-current I to the interconnecting cable of concern equipment injects cable low and 1)～2) I irradiation cable low identical, 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) AVHRR NDVI data is carried out linear extrapolation to outside the aircraft exterior electromagnetic field level EMEL requiring
Outside I note high=EMEL × the outer low of I note low/E
7) to airframe implantation step 6) high current I that obtains note high, realizes electric current and injects to high level irradiation
Substitute.Continuing induced-current on the interconnecting cable of monitoring concern equipment, if also keeping linear ratio relation, confirming electricity simultaneously
The equivalence of magnetic environment.
Example 3. aircraft exterior electromagnetic environment Safety Margin (low level coupled method)
Only taking low level current scanning method LLSC as a example illustrate.Experiment process is：Configuration is suitably grounded by test specimen
Mode and earth point position (with actual installation state consistency or be easy to test and 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
Induced-current in interconnecting cable under the high level irradiation field being required with the linear relationship extrapolation standard between low and high level, that is, sense
Injected value of current.Finally keep constant by the earthing mode of test specimen and earth point position, value electric current will be corresponded to through cable clamp
Sensing injection is transmitted in interconnecting cable.Induction step is as follows：
1) test specimen is subject to the outer low Electromagnetic Field Irradiation of default low level E；
2) detection current clamp is stuck on all interconnecting cables at cabinet 50mm, 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) AVHRR NDVI data is carried out linear extrapolation to the high level field intensity of code requirement
The outer low of the outer high × Ilow/E of Ihigh=E
By electric current clamp, implantation step 5 is sensed to tested interconnecting cable) the high level energy that obtains, realize electric current injection
Replacement to high level irradiation, completes to test.
Example 4. interior of aircraft electromagnetic environment is assessed from compatible secure nargin
1) confirm to be subject to 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
The most extreme electromagnetic environment.Consequence and extent of injury during EMC problem, aircraft being likely to result in occurs simultaneously, to winged according to equipment
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 corresponding margin of safety requires, usual safe level is 12dB, and task level is 6dB, and regular grade is
0dB；
2) determine in each equipment installation site actual (or expected) electromagnetic ambient level EMEL
It is the benchmark that aircraft is assessed from compatible secure nargin in EMEL, may be used to lower several method and determine.
Field measurement：Whole airborne electronic equipment/electrical equipments are made to operate at full capacity and switch different working modes, main investigation
High-power, heavy load equipment possible transmitting, the limit work such as the fastest level rate of change, the fastest power consumption/load switching rate the most by force
Make state.During frequency f >=100MHz, choose head/area equipment such as each equipment compartment of fuselage/tail, driving cabin, main cabin, cargo hold
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, choose head/all connector ends of area equipment such as each equipment compartment of fuselage/tail, driving cabin, main cabin, cargo hold
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 be 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 in standard, the examination of radiosensitivity RS
Testing limiting level is in expected electromagnetic ambient level EMEL；Or the test with 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 suitable correction.
Simulation calculation：Using Large Electromagnetic simulation calculation software kit, such as EM3D, CST, FECO etc., ties to fuselage interior
Structure size, material, lay the size of interconnecting cable, trend, material in cabin, the installation site of airborne equipment, size, material,
The evaluation objects such as the electrical property of equipment, environment, boundary condition carry out as true to nature as possible, detailed modeling.When selecting suitable again
Domain, frequency domain value algorithm carry out resolving and obtain a result.Simplify and can first consider the transceiver with antenna, by emitter spoke when calculating
Penetrate power, receiver receiving sensitivity, dual-mode antenna directional diagram and spacing, transmitting-receiving frequency and bandwidth, calculate transmitting-receiving fundamental wave, harmonic wave
Between that may be present interfere impact；Consider further that emitter to miscellaneous equipment, according to emitter transmission power, transmitting antenna
Directional diagram, transmitting antenna, to paying close attention to equipment installation site, fuselage screen efficiency, calculate transmission signal using communication distance equation
Impact to concern equipment.
3) determine that each equipment actual electromagnetic Design of Compatibility controls level
The EMC margin of safety of so-called aircraft is 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 margin of safety of aircraft is final
Specifically implemented on each equipment.The electromagnetic Compatibility Design of every equipment controls level, needs from electromagnetic susceptibility electricity
Flat Electromagnetic Susceptibility Level-EMSL controls and electromagnetic interference level Electromagnetic
Interference Level-EMIL controls two aspects to consider.Typically can be provided by the EMC test report of equipment.For
EMC approved apparatus up to standard, its EMIL controls such as the more conservative Electromagnetic Launching limit value being retrieved from and conducting in GJB151A and radiate, and
EMSL control then must be defined by equipment measured value.
4) accordance assessment
External interface from equipment --- cabinet and interconnection line are thus set about in terms of radiation and conduction two, respectively by above
Each device data that a few section methods obtain, substitution below equation obtains its conduction, radiation safety margin meets implementations.
Electromagnetic interference level EMIL control≤expection is compared with " -3dB in actual electromagnetic ambient level EMEL "
Electromagnetic susceptibility level EMSL control >=expection is compared with "+M in actual electromagnetic ambient level EMEL "
If
- 3dB in electromagnetic interference level EMIL control≤actual electromagnetic ambient level EMEL
+ M in electromagnetic susceptibility level EMSL control >=actual electromagnetic ambient level EMELRequire
At this moment margin of safety M=electromagnetic susceptibility level EMSL controls-expects the value in actual electromagnetic ambient level EMEL
Value M more than regulationRequire, then show that evaluated equipment/system meets and require.
Here not only consider to be estimated from the electromagnetic susceptibility level of safety margin definition, also add to Electromagnetic Launching
The assessment of level, increases 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 change or replace the guarantor that all should belong to appended claims of the invention
Shield scope.
Claims (6)
1. a kind of aircraft electromagnetic environment Safety Margin code method is it is characterised in that comprise to be applied to aircraft exterior electromagnetism ring
The low level coupled method of border Safety Margin, step is as follows：
(1) confirm to be subject to assessment system；
(2) determine aircraft exterior electromagnetic ambient level；
(3) passed by induced-current on test specimen interconnecting cable or installation place external electromagnetic field in aircraft low level scanning determination machine
Delivery function；
(4) calculated in the way of linear extrapolation on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level induced-current or
Installation place spatial electromagnetic field value；
(5) cable current injection or irradiation are carried out with the result of this linear extrapolation, and accordance assessment.
2. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1 it is characterised in that：Gone out according to equipment
Consequence during existing EMC problem, aircraft being likely to result in 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 corresponding safety
Margin requirement.
3. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1 it is characterised in that：Determine outside aircraft
Data or the requirement of Certification that portion's electromagnetic ambient level is given using user, quote some related platform level electromagnetic compatible marks
Regulation in standard, also has the concrete quantizating index 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, the various electromagnetism rings that may meet with during being used by analysis of aircraft
Border, reference, class, than conventional engineering experience, are chosen wherein electromagnetic environment typical scene the harshest, are carried out in-site measurement statistics.
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 adopts simulation calculation to determine.
6. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1 it is characterised in that：This low level coupling
Legal applicable frequency range divides LLSCI, LLSC and LLSF tri- kinds, and LLSCI is applied to resonant frequency of 10KHz～aircraft, and LLSC fits
Play the 500kHz～400MHz of main coupling for cable, LLSF be applied to cabinet and all influential 100MHz of cable～
40GHz, the method sets up the biography between galvanomagnetic-effect and aircraft exterior electromagnetic environment on the airborne equipment of concern in the mode of surveying
Delivery function relation, wherein LLSCI, LLSC are contacted induced-current on apparatus interconnection cable with normalization aircraft exterior electromagnetic environment
Get up, and LLSF connects equipment installation place field intensity and normalization aircraft exterior electromagnetic environment, then transmission function line accordingly
Property extrapolate and must assess the interior of aircraft electromagnetic stress that equipment should be applied under the aircraft exterior electromagnetic environment of requirement, thus carrying out
Substitute indirect test checking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610891443.3A CN106383273B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410098076.2A CN103869191B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
| CN201610891443.3A CN106383273B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410098076.2A Division CN103869191B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106383273A true CN106383273A (en) | 2017-02-08 |
| CN106383273B CN106383273B (en) | 2019-05-24 |
Family
ID=50907938
Family Applications (4)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610892279.8A Active CN106546841B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
| CN201610892277.9A Active CN106314822B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
| CN201610891443.3A Active CN106383273B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
| CN201410098076.2A Active CN103869191B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
Family Applications Before (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610892279.8A Active CN106546841B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
| CN201610892277.9A Active CN106314822B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410098076.2A Active CN103869191B (en) | 2014-03-17 | 2014-03-17 | Aircraft electromagnetic environment Safety Margin code method |
Country Status (1)
| Country | Link |
|---|---|
| CN (4) | CN106546841B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109508889A (en) * | 2018-11-20 | 2019-03-22 | 中国舰船研究设计中心 | It is a kind of that performance stage division is compatible with based on the ship platform of analytic hierarchy process (AHP) frequency installation electromagnetical |
| CN109655670A (en) * | 2018-11-21 | 2019-04-19 | 上海无线电设备研究所 | The high high radiation field effect test system and test method that low level directly drives |
| CN112114218A (en) * | 2020-09-22 | 2020-12-22 | 上海无线电设备研究所 | High-level test system for HIRF test and verification method |
| CN116879664A (en) * | 2023-09-06 | 2023-10-13 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105197253B (en) * | 2015-08-14 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing Material Stiffened Panel margin of safety computational methods |
| CN105676020A (en) * | 2015-12-31 | 2016-06-15 | 陕西海泰电子有限责任公司 | System-level radiation safety margin test system and method |
| CN107918703B (en) * | 2017-11-10 | 2021-04-20 | 天津航天机电设备研究所 | Design method for wide-band radio frequency receiving satellite unintentional radiation emission limit value |
| CN108196132B (en) * | 2017-11-21 | 2020-03-17 | 中国船舶重工集团公司第七一0研究所 | Method for evaluating electromagnetic compatibility in system |
| CN108646110B (en) * | 2018-05-10 | 2020-08-18 | 中国人民解放军陆军工程大学 | Method for testing and evaluating safety margin of strong-field electromagnetic radiation of actual electric explosion device |
| 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 |
| 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 |
| CN110991110B (en) * | 2019-11-27 | 2021-12-07 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment |
| 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 |
| CN113076675B (en) * | 2021-04-12 | 2022-11-08 | 中国电子科技集团公司第三十三研究所 | Electromagnetic environment effect simulation design method for air cushion landing boat |
| CN113704884B (en) * | 2021-08-08 | 2024-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Electromagnetic environment effect simulation method for aircraft design |
| CN116973672B (en) * | 2023-09-25 | 2023-12-29 | 合肥航太电物理技术有限公司 | Low-level scanning current testing device and testing method thereof |
| CN117572853B (en) * | 2024-01-17 | 2024-03-15 | 中国人民解放军陆军装甲兵学院 | Magnetic field controller performance test analysis management system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101436221A (en) * | 2008-12-02 | 2009-05-20 | 北京航空航天大学 | Airplane complete machine electromagnetic compatible digitalization model system |
| CN101710160A (en) * | 2009-12-25 | 2010-05-19 | 中国舰船研究设计中心 | Method for measuring electromagnetic compatibility margin of electronic and electric equipment |
| CN102156234A (en) * | 2011-03-28 | 2011-08-17 | 中国舰船研究设计中心 | Method for measuring electromagnetic safety margin of electric initiating explosive device in radar scanning environment |
| CN102981064A (en) * | 2012-10-09 | 2013-03-20 | 中国人民解放军63892部队 | Aircraft external radio frequency electromagnetic environment prediction method and prediction system |
| CN103308801A (en) * | 2013-06-04 | 2013-09-18 | 上海无线电设备研究所 | Ground test method for full-aircraft electromagnetic compatibility of commercial aircraft |
| CN103455680A (en) * | 2013-07-01 | 2013-12-18 | 陕西海泰电子有限责任公司 | Prediction analysis system and analysis method for EMC (Electro Magnetic Compatibility) in system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0516265A1 (en) * | 1991-05-09 | 1992-12-02 | Siemens Plessey Electronic Systems Limited | Improvements in or relating to aircraft landing systems |
| US5490090A (en) * | 1994-06-14 | 1996-02-06 | The United States Of America As Represented By The Secretary Of The Army | Two tone test method for determining frequency domain transfer |
| US6037782A (en) * | 1998-02-20 | 2000-03-14 | Hewlett-Packard Company | Automatic adjustment of cables which aids in set-up of equipment under test for electromagnetic compatibility measurements |
| CN103616595B (en) * | 2013-11-29 | 2015-12-02 | 中国航空无线电电子研究所 | Return flow line method to set up in a kind of aircraft surfaces pulse current injectingt test |
-
2014
- 2014-03-17 CN CN201610892279.8A patent/CN106546841B/en active Active
- 2014-03-17 CN CN201610892277.9A patent/CN106314822B/en active Active
- 2014-03-17 CN CN201610891443.3A patent/CN106383273B/en active Active
- 2014-03-17 CN CN201410098076.2A patent/CN103869191B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101436221A (en) * | 2008-12-02 | 2009-05-20 | 北京航空航天大学 | Airplane complete machine electromagnetic compatible digitalization model system |
| CN101710160A (en) * | 2009-12-25 | 2010-05-19 | 中国舰船研究设计中心 | Method for measuring electromagnetic compatibility margin of electronic and electric equipment |
| CN102156234A (en) * | 2011-03-28 | 2011-08-17 | 中国舰船研究设计中心 | Method for measuring electromagnetic safety margin of electric initiating explosive device in radar scanning environment |
| CN102981064A (en) * | 2012-10-09 | 2013-03-20 | 中国人民解放军63892部队 | Aircraft external radio frequency electromagnetic environment prediction method and prediction system |
| CN103308801A (en) * | 2013-06-04 | 2013-09-18 | 上海无线电设备研究所 | Ground test method for full-aircraft electromagnetic compatibility of commercial aircraft |
| CN103455680A (en) * | 2013-07-01 | 2013-12-18 | 陕西海泰电子有限责任公司 | Prediction analysis system and analysis method for EMC (Electro Magnetic Compatibility) in system |
Non-Patent Citations (4)
| Title |
|---|
| 宋文武 等: "EMC安全裕度评估方法探讨", 《舰船电子工程》 * |
| 张学宇 等: "飞行器外部电磁环境分析与辐射安全裕度试验方法研究", 《遥测遥控》 * |
| 胡平道: "低电平耦合技术在飞机级试验中的应用", 《微波学报》 * |
| 阎芳: "《运输类飞机适航要求解读：第5卷 设备》", 30 September 2013 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109508889A (en) * | 2018-11-20 | 2019-03-22 | 中国舰船研究设计中心 | It is a kind of that performance stage division is compatible with based on the ship platform of analytic hierarchy process (AHP) frequency installation electromagnetical |
| CN109655670A (en) * | 2018-11-21 | 2019-04-19 | 上海无线电设备研究所 | The high high radiation field effect test system and test method that low level directly drives |
| 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 |
| CN112114218A (en) * | 2020-09-22 | 2020-12-22 | 上海无线电设备研究所 | High-level test system for HIRF test and verification method |
| 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 |
| CN116879664A (en) * | 2023-09-06 | 2023-10-13 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
| CN116879664B (en) * | 2023-09-06 | 2023-11-24 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106383273B (en) | 2019-05-24 |
| CN103869191B (en) | 2018-04-17 |
| CN106314822A (en) | 2017-01-11 |
| CN106546841B (en) | 2019-12-03 |
| CN103869191A (en) | 2014-06-18 |
| CN106314822B (en) | 2018-08-10 |
| CN106546841A (en) | 2017-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106383273B (en) | Aircraft electromagnetic environment Safety Margin code method | |
| CN103308801A (en) | Ground test method for full-aircraft electromagnetic compatibility of commercial aircraft | |
| CN109655670B (en) | Low-level direct-drive high-intensity radiation field effect test system and test method | |
| CN103033708B (en) | Plane whole-machine high-strength illumination testing method | |
| CN109412715B (en) | System and method for testing electromagnetic interference of quantization index of airborne communication radio frequency receiving equipment | |
| CN109655671B (en) | High-intensity radiation field effect test system and test method for low-level sweep current | |
| RU2697810C9 (en) | Method for evaluating electromagnetic compatibility of on-board radioelectronic equipment | |
| CN112578192A (en) | Time domain pulse shielding effectiveness testing device and method for small shielding body | |
| RU2497282C9 (en) | Method of evaluating electromagnetic compatibility of aircraft on-board equipment in frequency range from 10 khz to 400 mhz | |
| CN207516465U (en) | A kind of simulating, verifying test device of shielded cable | |
| CN105808800A (en) | Leakage radiation simulation and prediction method for electronic equipment cabinet | |
| CN109709403A (en) | A kind of data processing method of aircraft low level scanning field test | |
| Gutierrez et al. | Influence of geometric simplifications on high-intensity radiated field simulations | |
| Perez et al. | Lightning low level vs high level direct current injection tests on a full scale aircraft cockpit | |
| Prather et al. | CW measurements of electromagnetic shields | |
| Bastard et al. | Ways of improvement for HIRF transfer function assessment on rotorcraft | |
| Pous et al. | Time domain double-loaded electromagnetic field probe applied to unmanned air vehicles | |
| Bull et al. | Testing civil aircraft and equipment to the new external RF environmental conditions | |
| Bolsover et al. | Airframe current injection as part of aircraft clearance | |
| CN203720346U (en) | Test system of distance test equipment | |
| Akram et al. | Simulation of Aircraft Electromagnetic Environment to Compute EMC Test Conditions | |
| De Leo et al. | Numerical and experimental methods for the investigation of EMI into spacecraft modules caused by UWB signals | |
| Prather et al. | Swept CW testing of shielded systems | |
| Pous et al. | Characterization of Time Domain EM Field Double-loaded Curved Loop Probe | |
| Rierson | Determining an Aircraft's Attenuation Characteristics of HIRF Testing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |