CN103869191B - Aircraft electromagnetic environment Safety Margin code method - Google Patents

Aircraft electromagnetic environment Safety Margin code method Download PDF

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Publication number
CN103869191B
CN103869191B CN201410098076.2A CN201410098076A CN103869191B CN 103869191 B CN103869191 B CN 103869191B CN 201410098076 A CN201410098076 A CN 201410098076A CN 103869191 B CN103869191 B CN 103869191B
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electromagnetic
level
equipment
aircraft
actual
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CN103869191A (en
Inventor
方愔
侯典国
胡超
王庆国
周伟
陶志杰
徐荟翎
马琼
徐琪皓
孙文静
吴藻菡
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China Aeronautical Radio Electronics Research Institute
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China Aeronautical Radio Electronics Research Institute
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Priority to CN201610892279.8A priority Critical patent/CN106546841B/en
Priority to CN201610891443.3A priority patent/CN106383273B/en
Priority to CN201410098076.2A priority patent/CN103869191B/en
Priority to CN201610892277.9A priority patent/CN106314822B/en
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/001—Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/0807—Measuring electromagnetic field characteristics characterised by the application
    • G01R29/0814—Field measurements related to measuring influence on or from apparatus, components or humans, e.g. in ESD, EMI, EMC, EMP testing, measuring radiation leakage; detecting presence of micro- or radiowave emitters; dosimetry; testing shielding; measurements related to lightning
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/0864—Measuring electromagnetic field characteristics characterised by constructional or functional features
    • G01R29/0892—Details related to signal analysis or treatment; presenting results, e.g. displays; measuring specific signal features other than field strength, e.g. polarisation, field modes, phase, envelope, maximum value
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/005—Testing of electric installations on transport means
    • G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels

Abstract

The present invention discloses a kind of aircraft electromagnetic environment Safety Margin code method, it is some flexible Equivalent Test methods of the response of equal value of the galvanomagnetic-effect of equal value and/or EUT functional performances that are produced based on external electromagnetic environment EME stress to EUT, mainly includes the following steps：（1）Confirm by assessment system；（2）Determine aircraft exterior electromagnetic ambient level；（3）Suitable method is selected to determine external electromagnetic environment and the transmission function of electromagnetic environment at internal focus；（4）Focus actual electromagnetic field level is determined according to transmission function；（5）Determine each installation electromagnetical Design of Compatibility control level；（6）Accordance is assessed.The present invention has the work of aircraft electromagnetic environment Safety Margin standardization effect, strong operability, has practical directiveness well, can significantly improve the work efficiency that such assessment is carried out in engineering, reduction expense by above-mentioned method.

Description

Aircraft electromagnetic environment Safety Margin code method
【Technical field】
The present invention relates to the electromagnetic compatibility test applied to aircraft, particularly relates to aircraft electromagnetic environment Safety Margin Code method.
【Background technology】
Before the aircraft development stage especially shapes, it is necessary to regard to aircraft to actually using the external electromagnetic environment met with Adaptability, and the margin of safety that aircraft possesses this are assessed.It includes airborne equipment, system, each aspect of full machine really Recognize and verify work, both needed a set of elaboration program comprehensively and carefully planned guidance, be also relied on corresponding complete skill Document, data calculate analysis, the support of experiment measured result.
It generally specify only the requirement of electromagnetic environment margin of safety in aircraft Airworthiness Certification file, Its Relevant Technology Standards, Get off the plane and how to show in what electromagnetic environment condition, particularly as being (with every meter of some volts of electricity in bad electromagnetic environment Field intensity is measured) under keep how function and performance, without providing exercisable verification code.Therefore led by electromagnetic compatibility The way of domain routine, is exactly to require directly to carry out aircraft high field intensity radiation exposure HIRF experiments by definition.
But the energy-rich radiation level value that the experiment of aircraft electromagnetic environment margin of safety is related to is far beyond current industrial quarters Actual tests ability level, i.e., be difficult to meet these regulations, there is an urgent need to seek and work out one in the industry with conventional test methods A little more simple and feasible alternatives.
【The content of the invention】
It is existing to solve it is an object of the invention to provide a kind of aircraft electromagnetic environment Safety Margin code method The problem of mode experimentation cost and excessive research and development of products cost.
To achieve the above object, the present invention proposes a kind of aircraft electromagnetic environment Safety Margin code method, is suitable for Interior of aircraft electromagnetic environment is assessed from compatible secure nargin, and this method comprises the following steps：
(1) confirm by assessment system；
(2) actual (or expected) electromagnetic ambient level of each equipment installation site is determined；
(3) each equipment actual electromagnetic Design of Compatibility control level is determined；
(4) accordance is assessed.
According to above-mentioned main feature, wherein the step of confirming assessment system includes determining that all of each mission phase fly Machine, system, the various operating modes of equipment, with the possible most extreme electromagnetic environment of clear and definite interior of aircraft, while go out according to equipment During existing EMC problems to aircraft may caused by consequence and the extent of injury, the influence degree of the mission that carries out to aircraft task, equipment Functional characteristic, the inconsistency of hardware and related uncertain factor, establish each equipment importance rate and corresponding safety Margin requirement.
According to above-mentioned main feature, determine that the actual or expected electromagnetic ambient level of each equipment installation site passes through field measurement Obtain, the whole airborne electronic equipment/electrical equipments of the method order operate at full capacity and switch different working modes, investigate high-power, again The extreme working position such as the possible most strong transmitting of load equipment, most fast level change rate, most fast power consumption/load switching rate；f≥ During 100MHz, choosing the area equipment cabinets such as head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold space is nearby Ambient level sampled measurements point, with the scanning frequency spectrum of three axis Field probes+receiver measurement focus；During f≤400MHz, machine is chosen All connector end interconnecting cables of the area equipment such as head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold are ambient level Sampled measurements point, with the scanning frequency spectrum of current probe+receiver measurement focus；To scan the largest enveloping of frequency spectrum as expected electricity Magnetic environment level.
According to above-mentioned main feature, determine that the actual or expected electromagnetic ambient level of each equipment installation site is estimated by analyzing Determine, can be with conducted susceptibility CS, radiosensitivity in immediate system/device level EMC test standard GJB151A/152A The experiment limiting level of RS is expected electromagnetic environment electricity；Or the experiment pole with conducted susceptibility CS, radiosensitivity RS in standard Ration the power supply and be worth based on putting down, depending on installation region situation and neighbouring specific equipment, according to conventional practical experience, increased or decrease some Value is rationally adjusted.
According to above-mentioned main feature, determine that the actual or expected electromagnetic ambient level of each equipment installation site passes through analogies of experience Obtain, determined by the data with existing or appropriate correct of selecting similar airplane equipment scene.
According to above-mentioned main feature, determine that the actual or expected electromagnetic ambient level of each equipment installation site passes through simulation calculation Obtain, by using Large Electromagnetic simulation calculation software kit, such as EM3D, CST, FECO, to fuselage interior structure size, material Matter, size, trend, the material of laying interconnecting cable in cabin, installation site, size, the material of airborne equipment, equipment it is electrical The assessment such as energy object, environment, boundary condition carry out as true to nature as possible, detailed modeling, then select suitable time domain, frequency domain value Algorithm carries out resolving and obtains a result, and the transceiver with antenna can first be considered when calculating by simplifying, and by transmitter radiant power, receives Machine receiving sensitivity, dual-mode antenna directional diagram and spacing, transmitting-receiving frequency and bandwidth, calculating may deposit between transmitting-receiving fundamental wave, harmonic wave Interfere with each other influence；Transmitter is considered further that to miscellaneous equipment, according to transmitter transmission power, transmitting antenna directional diagram, hair Antenna is penetrated to equipment installation site, fuselage screen efficiency is paid close attention to, goes out to launch signal using communication distance equation calculation and concern is set Standby influence.
According to above-mentioned main feature, determine that each equipment actual electromagnetic Design of Compatibility control level is needed from electromagnetic susceptibility Consider in terms of level and electromagnetic interference level two, provided by the EMC test reports of equipment；For EMC approved apparatus up to standard, its Electromagnetic interference level is derived from the Electromagnetic Launching limit value for conducting and radiating in GJB151A, and electromagnetic susceptibility level is surveyed with equipment Subject to value.
According to above-mentioned main feature, accordance assesses the external interface of slave device, including cabinet and interconnection line radiation and The aspect of conduction two, respectively each device data obtained by abovementioned steps, substitutes into the following formula and obtains its conduction, radiation safety Nargin meets implementations：
If：Electromagnetic interference level≤reality (or expected) electromagnetic ambient level -3dB
Electromagnetic susceptibility level >=reality (or expected) electromagnetic ambient level+MIt is required that
At this moment, actual margin of safety MIt is actual=electromagnetic susceptibility level-actual electromagnetic ambient level
If actual margin of safety MIt is actualMore than margin of safety setting MIt is required that, then show that evaluated equipment/system meets to want Ask.
To realize the object of the invention, the present invention proposes another aircraft electromagnetic environment Safety Margin code method, fits For aircraft exterior electromagnetic environment Safety Margin, 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 site is determined；
(4) each equipment installation site 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, the influence degree of the mission that carries out to aircraft task, the functional characteristic of equipment, the inconsistency of hardware and related not true Qualitative factor, establishes each equipment importance rate and corresponding margin of safety requirement.
According to above-mentioned main feature, aircraft exterior electromagnetic ambient level EMEL is determinedOutsideThe number that can be directly provided using user 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, aircraft exterior electromagnetic ambient level EMEL is determinedOutsideAnalysis measurement method can be used to determine, i.e., By the various electromagnetic environments that may be met with during analysis of aircraft use, reference, class are chosen wherein than conventional engineering experience The most harsh typical scene of electromagnetic environment, carries out in-site measurement statistics.
According to above-mentioned main feature, aircraft exterior electromagnetic ambient level EMEL is determinedOutsidePair can be determined using simulation calculation, i.e., The most harsh typical scene progress of electromagnetic environment is as true to nature as possible, models in detail.It is every to have the contribution that compare to electromagnetic environment Radiation source will consider, determine they transmission power, frequency range, signal waveform, antenna directivity, propagation distance, On the basis of polarization direction etc. is participated in the experiment, the tribute of each field source is calculated with the lossless spatial range formula of electromagnetic wave, communication equation number value Offer, and carry out vector superposed and synthesize total electromagnetic environment.
According to above-mentioned main feature, the fuselage screen efficiency for determining to present in equipment installation site can use field measurement true Fixed, to whetheing there is two kinds of situations of aircraft, diverse location, the antenna in orientation are irradiated with safety equivalence level outside machine, to be closed in machine The received minimum signal level difference of (cockpit, equipment compartment etc.) receiving sensor at position is noted to measure the fuselage screen in place effect ginseng Number.
According to above-mentioned main feature, the fuselage screen efficiency for determining to present in equipment installation site can use simulation calculation true It is fixed, such as use electromagnetic-field simulation computation software package, such as EM3D, CST, FECO, to aircraft external and internal compositions size, material, especially Be cabin inner structure size, the material 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, the fuselage screen efficiency for determining to present in equipment installation site can use empirical analysis true It is fixed, i.e., estimated according to engineering experience, the shielding properties in astomous all-metal cabin is best, and the screen for generally having more than 40dB is imitated； The shielding properties for having the metal cabin of perforation is taken second place；The shielding properties in fenestrate, door metal or non-all-metal cabin is worst, generally The screen effect of only below 10dB, even strengthens on the contrary 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, each equipment installation site actual electromagnetic field level EMEL is determinedIt is interiorFor by aircraft exterior electricity Magnetic environment level EMELOutsideSubtract airframe shield effectiveness.
According to above-mentioned main feature, determine that each equipment actual electromagnetic Design of Compatibility control level is needed from electromagnetic susceptibility Consider in terms of level and electromagnetic interference level two, provided by the EMC test reports of equipment；For EMC approved apparatus up to standard, its Electromagnetic interference level is derived from the Electromagnetic Launching limit value for conducting and radiating in GJB151A, and electromagnetic susceptibility level is surveyed with equipment Subject to value.
According to above-mentioned main feature, accordance assesses the external interface of slave device, including cabinet and interconnection line radiation and The aspect of conduction two, respectively each device data obtained by abovementioned steps, substitutes into the following formula and obtains its conduction, radiation safety Nargin meets implementations：
Electromagnetic interference level EMILControl≤ it is expected electromagnetic ambient level EMELIt is interior- 3dB
Electromagnetic susceptibility level EMSLControl>=it is expected electromagnetic ambient level EMELIt is interior+M
If margin of safety M=electromagnetic susceptibility level EMSLControl- it is expected electromagnetic ambient level EMELIt is interiorMore than defined Value, then show that evaluated equipment/system is met the requirements.
To realize the object of the invention, the present invention proposes another aircraft electromagnetic environment Safety Margin code method, fits For aircraft exterior electromagnetic environment Safety Margin, this method comprises the following 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, it includes low level scanning and irradiation and is injected with low level surface current of equal value；
(5) high level surface current injection method airworthiness compliance is tested.
According to above-mentioned main feature, the step of Injection Current is calibrated, includes configuration suitably by test specimen earthing mode and ground connection Point position, first carries out low level irradiation, is closed with the sensing electric current in cable caliper measurements apparatus interconnection cable, then to airframe Suitable point injection low level current, is sized, and makes to monitor to sense electric current and the measured value on the interconnecting cable of concern equipment It is identical, the transfer function between irradiation field strength and Injection Current is thus obtained, is extrapolated using the linear relationship between low and high level Sense electric current on aircraft skin under the high level irradiation field of standard requirement, this should be directly injected into current value, finally keep flying The Current injection points of machine, earthing mode and earth point position are constant, and the high current is injected to aircraft skin.
To realize the object of the invention, the present invention proposes another aircraft electromagnetic environment Safety Margin code method, fits For aircraft exterior electromagnetic environment Safety Margin, this method comprises the following steps：
(1) confirm by assessment system；
(2) aircraft exterior electromagnetic ambient level is determined；
(3) aircraft low level is scanned in the machine of determining by sensing electric current or installation place external electromagnetic field on test specimen interconnecting cable Transmission function；
(4) linear extrapolation goes out on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level to sense electric current or installation place is empty Between electromagnetism field value；
(5) cable current injection or irradiation, and accordance assessment are carried out with the high level.
According to above-mentioned main feature, this method is applicable in frequency range and divides LLSCI, LLSC and LLSF tri- kinds, and LLSCI is suitable for 10KHz~aircraft 1st resonant frequencies, LLSC are suitable for 500kHz~400MHz that cable plays main coupling, and LLSF is applicable in In all influential 100MHz~40GHz of cabinet and cable, the method establishes electromagnetism on the airborne equipment of concern in a manner of surveying Transmission function 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 strength and normalization aircraft exterior electromagnetism Environment connects, then transmission function linear extrapolation must be assessed equipment should be applied under the aircraft exterior electromagnetic environment of requirement accordingly The interior of aircraft electromagnetic stress added, so as to carry out substituting indirect test verification.
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 work efficiency that such assessment is carried out 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.
【Brief 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.
【Embodiment】
Refering to Figure 1, the present invention discloses a kind of aircraft electromagnetic environment Safety Margin code method, it is based on outer Some accommodations of the response of equal value of galvanomagnetic-effect of equal value and/or EUT functional performances that portion's electromagnetic environment EME stress produces EUT 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 external electromagnetic environment and the transmission function of electromagnetic environment at internal focus；(4) according to transmission letter The definite focus actual electromagnetic field level of number；(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 work efficiency that such assessment is carried out in engineering, reduction expense can be significantly improved.As for above-mentioned side The particular content of each step in method, the specific descriptions in four embodiments that can be below.
Margin of safety Margin refers to the difference of actual interference level in sensitive thresholding and environment, commonly uses dB and represents.The electricity of aircraft Magnetic environment margin of safety is the difference of sensitive thresholding and environment the actual interference level of airborne most sensitive equipment/system, excessively generally. The specific electromagnetic environment margin of safety of each airborne equipment/system is more paid close attention in engineering, they are general different, so aircraft Electromagnetic environment margin of safety be really minimum value in the electromagnetic environment margin of safety of each airborne equipment/system.
1. interior of aircraft electromagnetic environment is assessed from compatible secure nargin
Refer to aircraft the machine whole machine in internal electromagnetic environment Electromagnetic Environment Level-EMEL The largest enveloping for the full machine electromagnetic ambient level that on-board electrical electronic system, equipment energization work are formed, it is abundant from compatible secure Degree assessment mainly includes following 4 steps：
(1) confirm by assessment system；
(2) actual (or expected) electromagnetic ambient level of each equipment installation site is determined；
(3) each equipment actual electromagnetic Design of Compatibility control level is determined；
(4) accordance is assessed
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 (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 locating on aircraft skin It is same value to locate equal.Aircraft exterior electromagnetic environment Safety Margin mainly includes 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 site is determined；
4) each equipment installation site actual electromagnetic field level is determined；
5) each installation electromagnetical Design of Compatibility control level is determined；
6) accordance is assessed.
As shown in Figure 3, specific embodiment 2 is shown in the narration in detail of each step to estimation flow figure.
3. 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 needed for aircraft exterior electromagnetic environment Safety Margin electromagnetic environment in machine, makes to be in by test specimen and high level outside machine Under the electromagnetic stress of irradiation field equivalence, so as to produce same response.
It is alternate test assessment, one of advantage is an overall test just while completes to pacify the EMC of all airborne equipments Full nargin assessment.Its most effective frequency of use scope 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 is as shown in figure 4, in view of length is no longer illustrated in detail.
4. 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 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 for the overlapping use of latter two method it is major electromagnetic in 100~400MHz frequency ranges Coupling mechanism and field source characteristic, field source/object construction material, field source and target spacing, medium factors are closely related.Usually Cable induced electricity stream 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 relation on the airborne equipment of note between galvanomagnetic-effect and aircraft exterior electromagnetic environment, i.e., LLSCI, LLSC are equipment Sense electric current on interconnecting cable to connect with normalization aircraft exterior electromagnetic environment, 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, so as to carry out substituting indirect test verification.Assessment mainly includes 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 sensing electric current or installation on test specimen interconnecting cable Locate the transmission function of external electromagnetic field；
4) linear extrapolation goes out on interconnecting cable corresponding with aircraft exterior electromagnetic ambient level to sense electric current or installation place is empty Between electromagnetism field value；
5) cable current injection or irradiation, and accordance assessment are carried out with the high level.
Estimation flow figure as shown in Figure 5, in view of length is no longer illustrated in detail.
For the understanding apparent to above-mentioned method, above-mentioned method is said respectively with specific example below It is bright.
1. interior of aircraft electromagnetic environment of example is assessed from compatible secure nargin
1) confirm by assessment system
Consider all aircrafts, system, the various operating modes of equipment of each mission phase, thus clear and definite interior of aircraft may Most extreme electromagnetic environment.When there are EMC problems according to equipment at the same time 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 margin of safety, usual safe level is 12dB, task level 6dB, and regular grade is 0dB；
2) actual (or expected) the electromagnetic ambient level EMEL of each equipment installation site is determinedIt is interior
EMELIt is interiorIt is the benchmark that aircraft is assessed from compatible secure nargin, can be used to lower several method and determine.
Field measurement：Whole airborne electronic equipment/electrical equipments is operated at full capacity and switch 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.During f >=100MHz, the area equipment cabinets such as head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold are chosen Neighbouring space is ambient level sampled measurements point, with the scanning frequency spectrum of three axis Field probes+receiver measurement focus；f≤ During 400MHz, it is mutual to choose all connector ends of area equipment such as head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold Even cable is ambient level sampled measurements point, with the scanning frequency spectrum of current probe+receiver measurement focus；To scan frequency spectrum Largest enveloping is expected electromagnetic ambient level EMELIt is interior。
Analysis estimation：System/device level electromagnetic compatible testing standard GJB151A/152A has fully taken into account airborne set The electromagnetic environment being likely encountered during standby installation experiment, directly takes the examination of conducted susceptibility CS, radiosensitivity RS in standard It is expected electromagnetic ambient level EMEL to test limiting levelIt is interior；Or the experiment pole with conducted susceptibility CS, radiosensitivity RS in standard Ration the power supply and be worth based on putting down, depending on installation region situation and neighbouring specific equipment, according to conventional practical experience, increased or decrease some Value is rationally adjusted.
Analogies of experience：Select the data with existing of similar airplane equipment scene, or appropriate amendment.
Simulation calculation：Use Large Electromagnetic simulation calculation software kit, 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, The assessment such as electrical property of equipment object, 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.The transceiver with antenna can first be considered when calculating by simplifying, by transmitter spoke Power, receiver receiving sensitivity, dual-mode antenna directional diagram and spacing, transmitting-receiving frequency and bandwidth are penetrated, calculates transmitting-receiving fundamental wave, harmonic wave Between that may be present interfere with each other influence；Transmitter is considered further that to miscellaneous equipment, according to transmitter transmission power, transmitting antenna Directional diagram, transmitting antenna go out to launch signal to equipment installation site, fuselage screen efficiency is paid close attention to using communication distance equation calculation Influence to paying close attention to equipment.
3) each equipment actual electromagnetic Design of Compatibility control level is determined
The EMC margins of safety of so-called aircraft are too general, and the equipment of different importance rates has the requirement of different margins of safety, The equipment of same hierarchically secure margin requirement also has different actual margins of safety.So the EMC margins of safety of aircraft are final To specifically it implement in each equipment.The electromagnetic Compatibility Design control level of every equipment is, it is necessary to electric from electromagnetic susceptibility Flat Electromagnetic Susceptibility Level-EMSLControlWith electromagnetic interference level Electromagnetic Interference Level─EMILControlConsider in terms of two.It can generally be provided by the EMC test reports of equipment.For EMC Approved apparatus up to standard, its EMILControlSuch as more conservative Electromagnetic Launching limit value that may be derived from conducting and radiating in GJB151A, and EMSLControl It should then be subject to equipment measured value.
4) accordance is assessed
The external interface of slave device-- cabinet and interconnection line are set about so as to radiate and conduct two aspects, respectively by above Each device data that a few section methods obtain, substitution the following formula obtains its conduction, radiation safety margin meets implementations.
If：Electromagnetic interference level≤reality (or expected) electromagnetic ambient level -3dB
Electromagnetic susceptibility level >=reality (or expected) electromagnetic ambient level+MIt is required that
At this moment, actual margin of safety MIt is actual=electromagnetic susceptibility level-actual electromagnetic ambient level
If actual margin of safety MIt is actualMore than margin of safety setting MIt is required that, then show that evaluated equipment/system meets to want Ask.Here not only consider to be assessed from the electromagnetic susceptibility level of safety margin definition, also add to Electromagnetic Launching level Assessment, to internal electromagnetic ambient level EMELIt is interiorIncrease some safety factors.
2. aircraft exterior electromagnetic environment Safety Margin of example (fuselage screen is followed)
1) confirm by assessment system
With example 1 1), general middle and high degree spatial domain electromagnetic environment is preferable, and ground or low latitude electromagnetic environment are harsher, and airport is attached Closely, the electromagnetic environment on warship shutdown deck is harsher.
2) aircraft exterior electromagnetic ambient level EMEL is determinedOutside
EMELOutsideIt is the benchmark for carrying out the assessment of external electromagnetic environment compatible secure nargin.Lower several method is can be used to determine.
User requires：The data directly provided using user or the requirement of Certification, it is flat generally to quote some correlations more Regulation in platform level electromagnetic compatible standard, also there is the specific quantizating index for providing application-specific scene.
Analysis actual measurement：The various electromagnetic environments that may be met with during analysis of aircraft use, reference, class are than conventional engineering Experience, chooses the wherein most harsh typical scene of electromagnetic environment, carries out in-site measurement statistics.
Simulation calculation：The typical scene progress most harsh to electromagnetic environment is as true to nature as possible, models in detail.It is every to electricity The radiation source that magnetic environment has the contribution that can compare will consider, determine they 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 site is determined
Integral body shield effectiveness seems excessively rough in engineering, and the fuselage that concerned equipment installed position shows Shield effectiveness more has practical value.So when definition whether there is aircraft here, somewhere sensor received signal level ratio is in machine The fuselage screen effect that the point is presented.Determined with following several method.
Field measurement：To whetheing there is two kinds of situations of aircraft, diverse location, the antenna in orientation are with safety equivalence level spoke outside machine According to the received minimum signal level difference of (cockpit, equipment compartment etc.) receiving sensor is the measurement ground at concerned position in machine The fuselage screen effect parameter of point.
Simulation calculation：Using electromagnetic-field simulation computation software package, such as EM3D, CST, FECO, to aircraft external and internal compositions ruler Cabin inner structure size, the material of very little, material, especially installation concern equipment, carry 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 is best, generally there is 40dB Screen effect above；The shielding properties for having the metal cabin of perforation is taken second place；Fenestrate, door metal or the shielding in non-all-metal cabin Can be worst, the screen effect of general only below 10dB, even strengthens on the contrary in resonant frequency.General fuselage screen imitates selection principle：
0dB screens effect 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 site actual electromagnetic field level is determined
Aircraft exterior electromagnetic ambient level EMELOutsideAirframe shield effectiveness FSE is subtracted, just obtains each equipment installation position Put actual electromagnetic field level EMELIt is interior。
EMELIt is interior=EMELOutside- FSE
5) each installation electromagnetical Design of Compatibility control level is determined
With 3) saving for example 1.
6) accordance is assessed
With 4) saving for example 1.
3. 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 actual installation state consistency or Carried out easy to test), low level irradiation is first carried out, with the sensing electric current in cable caliper measurements apparatus interconnection cable, then to flying Machine fuselage appropriate point injects low level current, is sized, make to monitor to sense on the interconnecting cable of concern equipment electric 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 Sense electric current on aircraft skin under the high level irradiation field of relation extrapolation standard requirement, this should be directly injected into current value.Most Keep the Current injection points, earthing mode and earth point position of aircraft constant afterwards, the high current is injected to aircraft skin.Inductive step It is rapid as follows：
1) with low level EOuter lowElectromagnetic Field Irradiation aircraft；
2) the sensing electric current of detection concern all interconnecting cables of equipment, is stuck in away from cable under test at cabinet 50mm with current clamp On, measurement wherein senses electric current IIrradiate cable low；
3) to airframe appropriate point (common injection/outflow point pair：Head-vertical fin end, head-left/right horizontal tail end, machine Head-left/right wingtip, wingtip-wingtip, keypoint part both sides etc.) injection low level current, it is sized, makes monitoring To the sensing electric current I of the interconnecting cable of concern equipmentInject cable lowWith 1)~2) IIrradiate cable lowIt is identical, record this Injection Current INote low；
4) above step 1 is repeated)~3) to experiment full band scan measurement；
5) measurement data normalizes I to unit external irradiation fieldNote low/EOuter low；
6) by AVHRR NDVI data to desired aircraft exterior electromagnetic field level EMELOutsideCarry out linear extrapolation
INote high=EMELOutside×INote low/EOuter low
7) to airframe injection step 6) obtained high current INote high, realize that high level irradiation is replaced in electric current injection Generation.Continue to sense electric current on the interconnecting cable of monitoring concern equipment, if also keeping linear ratio relation, confirm electromagnetism at the same time The equivalence of environment.
4. 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 actual installation state consistency or easy to test), first carry out low level irradiation, use strain relief clamp Sensing electric current in pincers measurement interconnecting cable, obtains sensing the transfer function between electric current on irradiation field strength and interconnecting cable.Profit With electric current is sensed in interconnecting cable under the high level irradiation field of the linear relationship extrapolation standard requirement between low and high level, that is, sense Injected value of current.Finally keep constant by the earthing mode of test specimen and earth point position, will corresponding value electric current through cable clamp Sensing injection is transmitted in interconnecting cable.Induction step is as follows：
1) with default low level EOuter lowElectromagnetic Field Irradiation is by test specimen；
2) detection current clamp is stuck in away from having at cabinet 50mm on interconnecting cable, measurement wherein senses electric current Ilow；
3) above step 1 is repeated)~2) to experiment full band scan measurement；
4) measurement data normalizes I to unit external irradiation fieldlow/EOuter low；
5) AVHRR NDVI data are subjected to linear extrapolation to the high level field strength of code requirement
Ihigh=EOuter high×Ilow/EOuter low
Electric current clamp are passed through to tested interconnecting cable and sense injection step 5) obtained high level energy, realize that electric current injects To the replacement of high level irradiation, experiment is completed.
It is understood that for those of ordinary skills, can be with technique according to the invention scheme and its hair 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 scope.

Claims (4)

  1. A kind of 1. aircraft electromagnetic environment Safety Margin code method, comprising suitable for the certainly compatible peace of interior of aircraft electromagnetic environment The method of full nargin assessment, step are as follows：
    (1) confirm by assessment system；
    (2) each equipment installation site actual electromagnetic ambient level EMEL is determined by field measurementIt is interior；
    (3) each equipment actual electromagnetic Design of Compatibility control is determined in terms of electromagnetic susceptibility level and electromagnetic interference level two Level,
    (4) accordance is assessed；
    Wherein, the field measurement is, makes whole airborne electronic equipment/electrical equipments operate at full capacity and switches different working modes, Investigate comprising high-power, the possible most strong transmitting of heavy load equipment, most fast level change rate, most fast power consumption/load switching rate Extreme working position；During frequency f >=100MHz, head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold area are chosen Nearby space is ambient level sampled measurements point to domain equipment cabinets, is surveyed with three axis Field probes and receiver measuring environment level sampling Measure the scanning frequency spectrum of point；During frequency f≤400MHz, head/each equipment compartment of fuselage/tail, cockpit, main cabin, cargo hold area are chosen Equipment all connector end interconnecting cables in domain are ambient level sampled measurements point, with current probe and receiver measuring environment level The scanning frequency spectrum of sampled measurements point；To scan the largest enveloping of frequency spectrum as actual or expected electromagnetic ambient level；
    The external interface of the accordance assessment slave device, includes radiation and the aspect of conduction two of cabinet and interconnecting cable, respectively Each device data obtained by abovementioned steps, substitution the following formula obtains its conduction, radiation safety margin meets implementations：
    If：Electromagnetic interference level≤actual electromagnetic ambient level -3dB
    Electromagnetic susceptibility level >=actual electromagnetic ambient level+MIt is required that
    At this moment, actual margin of safety MIt is actual=electromagnetic susceptibility level-actual electromagnetic ambient level
    If actual margin of safety MIt is actualMore than margin of safety setting MIt is required that, then show that evaluated equipment/system is met the requirements.
  2. 2. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1, it is characterised in that：Confirm assessment system The step of system, includes determining the various operating modes of the system and equipment on all aircrafts and aircraft of each mission phase, with When specifying the possible most extreme electromagnetic environment of interior of aircraft, while EMC problems occur according to equipment to aircraft may caused by after Fruit and the extent of injury, the influence degree of the mission that carries out to aircraft task, the functional characteristic of equipment, the inconsistency of hardware and have The uncertain factor of pass, establishes each equipment importance rate and corresponding margin of safety requirement.
  3. 3. aircraft electromagnetic environment Safety Margin code method as claimed in claim 1, it is characterised in that：The electromagnetism is quick Sensitivity level and electromagnetic interference level are provided by the EMC laboratory reports of equipment.
  4. 4. aircraft electromagnetic environment Safety Margin code method as claimed in claim 3, it is characterised in that：Reached for EMC Qualified equipment is marked, the electromagnetic interference level of the equipment is derived from the Electromagnetic Launching limit value for conducting and radiating in GJB151A, the equipment Electromagnetic susceptibility level pass through survey obtain.
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