CN109657277A - A kind of composite material Extraction of electromagnetic parameters method under cabin structure - Google Patents
A kind of composite material Extraction of electromagnetic parameters method under cabin structure Download PDFInfo
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- CN109657277A CN109657277A CN201811391862.6A CN201811391862A CN109657277A CN 109657277 A CN109657277 A CN 109657277A CN 201811391862 A CN201811391862 A CN 201811391862A CN 109657277 A CN109657277 A CN 109657277A
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Abstract
A kind of composite material Extraction of electromagnetic parameters method under cabin structure includes: S1, the homogenization computation model for establishing composite material；S2, shield effectiveness of the composite material under cabin structure and phase change coefficient are tested；The Extraction of electromagnetic parameters of S3, composite material under cabin structure；It specifically includes: the initial value and equivalent conductivity initial value of composite material equivalent relative dielectric constant S31, being obtained by fitting；S32, the shield effectiveness that each frequency point of the composite material under cabin structure is obtained by simulation calculation；S33, when the shield effectiveness of whole frequency points is all satisfied required precision, it determines relative dielectric constant initial value and conductivity initial value is the composite material electromagnetic parameter under cabin structure, simulation calculation is otherwise re-started until meeting required precision with fixed step size amendment electromagnetic parameter.Analog composite material compartment environment of the present invention, Extraction of electromagnetic parameters precision is high, provides effective basis for the emulation electrical parameter input of aerospace vehicle composite material electromagnetic protection design.
Description
Technical field
The present invention relates to a kind of Extraction of electromagnetic parameters method, in particular to it is a kind of under cabin structure to composite material into
The method of row Extraction of electromagnetic parameters belongs to the technical field of electromagnetic protection and electromagnetic environmental effects.
Background technique
Currently, advantage of the advanced composite material with many uniquenesses such as high-intensitive, corrosion-resistant, light weight gradually substitutes metal
Material is widely used in the industrial circles such as aerospace.Composite material has the microcosmic several of complexity compared with metal material
What configuration has larger difference in dielectric constant, conductivity, this will cause aerospace vehicle couple electromagnetic energy path and screen
Cover the difference of efficiency.Since the electric conductivity of carbon fibre composite is far below metal material, aerospace vehicle can be made to electricity
The shield effectiveness much lower of magnetic environment.By carrying out the Study on Extraction Method of composite material electromagnetic parameter, aviation boat can be used as
The electromagnetic parameter of its device composite material inputs, and establishes important foundation for the design of aerospace vehicle electromagnetic protection.
In the prior art, for the research of composite material Extraction of electromagnetic parameters method, there is computation model set forth below, imitate
Very and test method.
Chinese invention patent application CN101655525A provides a kind of based on support vector machines (SVM, Support
Vector Machine) electromagnetic parameters of artificial electromagnetic material parameter extracting method, this method can test left-handed material and have week
The artificial electromagnetic material of phase property structure, and test result precision is high, test sample production is simple.The invention is to utilize calculating electromagnetism
Numerical computation method FEM and FDTD calculates transmission and the reflection coefficient of measured material, using corresponding calculated result as training
Sequence is trained support vector machines.When support vector machines is after training up, input transmission and reflection can be passed through
The effective dielectric constant and equivalent permeability of measured material is calculated in the measured value of coefficient.
Chinese invention patent application CN104931818A proposes a kind of extraction of asymmetric electromagnetic parameters of artificial electromagnetic material parameter
Method, the asymmetry to solve the problems, such as due to structure lead to not extract material electromagnetic parameter, first individually emulation the
The scattering parameter S ' of layer of material；The electromagnetic parameter of the first layer material is calculated using S ' and symmetrical structure algorithm；It emulates asymmetric
The externals stray parameter S of artificial electromagnetic material；The electromagnetic parameter of the second layer is obtained based on the electromagnetic parameter of S and first layer；Utilize S
Correct the electromagnetic parameter of first layer again with second layer electromagnetic parameter；Above-mentioned steps are recycled, until the electricity in revised two layers
Magnetic parameter no longer significant change in entire frequency range, using this as final electromagnetic parameter.
Composite material extracting method has many conventional test methodologies, such as Resonant-cavity Method and network parameter method.Chinese invention is special
Benefit application CN106053956A provides a kind of material dielectric constant test macro and the test method based on the test macro, wraps
Include coaxial resonant cavity and control system.Coaxial resonant cavity includes cavity and the probe for stretching out cavity；Control system is same for providing
The microwave input signal of axis resonant cavity, probe form electromagnetic field outside cavity, sample to be tested by the interference to the electromagnetic field from
And change the microwave output signal of the coaxial resonant cavity；Control system is by exporting letter to the microwave before and after placement sample to be tested
Number carry out analytical calculation obtain the dielectric constant of sample to be tested.The material dielectric constant test macro data processing is simple, test
It is high-efficient；And the probe by stretching out cavity is scanned formula detection to sample to be tested, and test speed is fast.
The document disclosed in the 55th the 1178-1186 pages of phase in 2013 " IEEE Transactions on EMC " periodical
《Effective Permittivity of Shielding Effectiveness Materials for Microwave
Frequencies ", wherein Preault etc. proposes the research of the effective electromagnetic parameter homogenization method based on dopant problem, draws
Enter to describe the characteristic length of fibre structure, calculates the equivalent electromagnetism ginseng of fiber composite material in square arrangement on section
Number.
But composite material Extraction of electromagnetic parameters side under these existing technical solutions and cabin structure proposed by the present invention
There are apparent difference, computation model, test method and approximating methods of foundation etc. to be all different for method.
Based on above-mentioned, the present invention proposes a kind of composite material Extraction of electromagnetic parameters method under cabin structure, simulates compound
Material compartment environment solves disadvantage existing in the prior art and limitation, sets for aerospace vehicle composite material electromagnetic protection
Meter emulation electrical parameter input provides a kind of novel effective scheme.
Summary of the invention
The object of the present invention is to provide composite material Extraction of electromagnetic parameters method, analog composite materials under a kind of cabin structure
Compartment environment, Extraction of electromagnetic parameters precision is high, for the emulation electrical parameter input of aerospace vehicle composite material electromagnetic protection design
Effectively basis is provided.
To achieve the above object, the present invention provides a kind of composite material Extraction of electromagnetic parameters method under cabin structure, includes
Following steps:
S1, the homogenization computation model for establishing composite material；
S2, shield effectiveness of the composite material under cabin structure and phase change coefficient are tested；
The Extraction of electromagnetic parameters of S3, composite material under cabin structure；Include:
S31, the initial value and equivalent conductivity initial value of composite material equivalent relative dielectric constant are obtained by fitting；
S32, the shield effectiveness that each frequency point of the composite material under cabin structure is obtained by simulation calculation；
S33, when the shield effectiveness of whole frequency points is all satisfied required precision, determine relative dielectric constant initial value and conductance
Rate initial value is the electromagnetic parameter of the composite material under cabin structure, is otherwise re-started with fixed step size amendment electromagnetic parameter imitative
It is true to calculate until meeting required precision.
In the S1, by the way that composite material is equivalent to homogeneous material, the shield effectiveness SE of composite material is establishedcal's
Computation model, and establish phase change coefficient βcalWith composite material equivalent relative dielectric constant εer, equivalent conductivity σeBetween meter
Calculate model.
In the S2, building composite material cabin structure is positive cube unit, and wherein two opposite side surfaces are set as gold
Belong to material, remaining four side is set as the unknown composite material of electromagnetic parameter, analog composite material compartment environment.
In the S2, receiving antenna is set in the center of composite material cabin structure, is tied in composite material cabin
The external setting transmitting antenna of structure simultaneously irradiates the cabin structure；Under transmitting antenna excitation irradiation, by comparison, whether there is or not composite woods
The electric field strength measured by receiving antenna and phase when material cabin structure, obtain test of the composite material under cabin structure
Shield effectiveness and test phase change coefficient.
Specifically, test shield effectiveness SE of the composite material under cabin structuretestWith test phase change coefficient βtestCalculating
Formula are as follows:
Wherein, EtFor there are the electricity that when composite material cabin structure, the receiving antenna of cabin structure center is detected
Field field strength, EcaliFor there is no when composite material cabin structure, the electric field strength that receiving antenna detects is calibrated as electric field
Value,Phase difference when measuring for electric field strength twice, l are the thickness of composite material.
In the S31, specifically: using the test shield effectiveness SE of composite material cabin structure obtained in S2test
With test phase change coefficient βtest, with composite material shield effectiveness SE obtained in S1calWith phase change coefficient βcalComputation model into
Row fitting, obtains the initial value ε of composite material equivalent relative dielectric constanter0And its it is fitted upper and lower limits and composite material
The initial value σ of equivalent conductivitye0And its fitting upper and lower limits.
Wherein, fitting condition are as follows:
In the S32, specifically: establish the simulation model with identical composite material cabin structure in S2；Using multiple
Condensation material equivalent relative dielectric constant initial value εer0With equivalent conductivity initial value σe0Define the attribute of composite material；Using with
Identical transmitting antenna carries out excitation irradiation in S2, and the excitation amplitude and frequency point of transmitting antenna is arranged, and Composite Cabin is arranged
The center of cell structure solves electric field；The field intensity value of the center of composite material cabin structure when frequency point is set is obtained,
And the calibration field intensity value of the center in no composite material cabin structure, composite material is obtained by comparison and is tied in cabin
The shield effectiveness of each frequency point under structure.
In the S33, specifically: the composite material obtained in S32 by simulation calculation is each under cabin structure
Test shield effectiveness of the composite material obtained in the shield effectiveness and S2 of frequency point by measuring and calculation under cabin structure carries out
The case where comparative evaluation, frequency point is unsatisfactory for required precision if it exists, corrects relative dielectric constant initial value or conductivity initial value,
And simulation calculation is re-started, until meeting required precision；Finally determine the relative permittivity value and electricity for meeting required precision
Conductivity value is the electromagnetic parameter of the composite material under cabin structure.
In conclusion composite material Extraction of electromagnetic parameters method under cabin structure provided by the invention, analog composite material
Compartment environment effectively solves the problems, such as that the non-homogeneous feature bring Extraction of electromagnetic parameters of composite material is difficult, and Extraction of electromagnetic parameters
Precision is high, provides effective basis for the emulation electrical parameter input of aerospace vehicle composite material electromagnetic protection design.
Detailed description of the invention
Fig. 1 is the flow chart of composite material Extraction of electromagnetic parameters method under the cabin structure in the present invention；
Fig. 2 is the cabin structure of the composite material in the present invention and its structural schematic diagram of geometric parameter；
Fig. 3 is that the shield effectiveness and test that the composite material in the present invention is obtained under cabin structure by emulation obtain
The contrast schematic diagram of shield effectiveness.
Specific embodiment
Below in conjunction with FIG. 1 to FIG. 3, by preferred embodiment to technology contents of the invention, construction feature, reached purpose
And effect is described in detail.
As shown in Figure 1, including following step for composite material Extraction of electromagnetic parameters method under cabin structure provided by the invention
It is rapid:
S1, the homogenization computation model for establishing composite material；
S2, shield effectiveness of the composite material under cabin structure and phase change coefficient are tested；
The Extraction of electromagnetic parameters of S3, composite material under cabin structure；Include:
S31, the initial value and equivalent conductivity initial value of composite material equivalent relative dielectric constant are obtained by fitting；
S32, the shield effectiveness that each frequency point of the composite material under cabin structure is obtained by simulation calculation；
S33, when the shield effectiveness of whole frequency points is all satisfied required precision, determine relative dielectric constant initial value and conductance
Rate initial value is the electromagnetic parameter of the composite material under cabin structure, is otherwise re-started with fixed step size amendment electromagnetic parameter imitative
It is true to calculate until meeting required precision.
In the S1, by the way that composite material is equivalent to homogeneous material, the shield effectiveness SE of composite material is establishedcal's
Computation model, and establish phase change coefficient βcalWith composite material equivalent relative dielectric constant εer, equivalent conductivity σeBetween meter
Calculate model.
In the S1, comprising the following steps:
S11, composite material is equivalent to homogeneous material, equivalent relative dielectric constant is set as εer, equivalent conductivity sets
For σe, then the complex dielectric permittivity ε of composite materialeIt indicates are as follows:
Wherein, ε0For permittivity of vacuum；ω is incident angular frequency；
S12, according to transmission line theory, at the thickness l of homogeneous material, the reflection R of homogeneous material surfacelAnd transmission
Coefficient TlIt is respectively as follows:
Wherein, η0For vacuum wave impedance, andηeFor the wave impedance of homogeneous material, and
μ0For space permeability；
S13, in incidence wave side (i.e. at the thickness of homogeneous material 0), the reflection R of homogeneous material surface0With it is saturating
Penetrate coefficient T0It is respectively as follows:
The shield effectiveness SE of S14, composite materialcalComputation model are as follows:
SEcal=-20lg (| Tl×T0|)；
It is obtained according to the nonhomogeneous Helmholtz equation in conducting medium, phase change coefficient βcalIt is equivalent opposite with composite material
Permittivity εer, equivalent conductivity σeBetween computation model are as follows:
In the S2, composite material cabin structure as shown in Figure 2 is constructed.The composite material cabin structure is positive cube
Unit, the left and right sides are metal material, remaining is the unknown composite material of electromagnetic parameter, analog composite material cabin ring on four sides
Border.In a preferred embodiment of the invention, the length, width and height of the composite material cabin structure are having a size of 1m × 1m × 1m, composite material
With a thickness of l=2.5mm.
In the S2, receiving antenna is set in the center of composite material cabin structure, is tied in composite material cabin
The external setting transmitting antenna of structure simultaneously irradiates cabin structure；Under transmitting antenna excitation irradiation, by comparison, whether there is or not composite materials
The electric field strength measured by receiving antenna and phase when cabin structure, obtain test panel of the composite material under cabin structure
Cover efficiency and test phase change coefficient.
Specifically, test shield effectiveness SE of the composite material under cabin structuretestWith test phase change coefficient βtestCalculating
Formula are as follows:
Wherein, EtFor there are the electricity that when composite material cabin structure, the receiving antenna of cabin structure center is detected
Field field strength, EcaliFor there is no when composite material cabin structure, the electric field strength that receiving antenna detects is calibrated as electric field
Value,Phase difference when measuring for electric field strength twice, l are the thickness of composite material.
In a preferred embodiment of the invention, transmitting antenna is arranged at the 10m apart from cabin structure center, and sends out
Center and the cabin structure center for penetrating antenna are contour and on the same straight line, and Electromagnetic Wave Propagation direction is tied perpendicular to cabin
Composite material plane on structure.The center of cabin structure is arranged in receiving antenna, detects electric field strength and phase.
Wherein, in the frequency range of 100MHz~1GHz, using carrying out excitation irradiation as transmitting antenna to all antennas,
Sweep interval is 10MHz.Calibration test is carried out first, and electric field is measured by receiving antenna in no composite material cabin structure
Strong Ecali；Then, it keeps the power of transmitting antenna excitation constant, when there are composite material cabin structure, is surveyed by receiving antenna
Measure electric field strength Et, and the test shield effectiveness SE of composite material cabin structure is calculatedtestWith test phase change coefficient βtest。
Wherein, in the frequency range of 1GHz~6GHz, excitation photograph is carried out as transmitting antenna using double-ridged horn antenna
It penetrates, sweep interval 50MHz.Calibration test is carried out first, and electric field is measured by receiving antenna in no composite material cabin structure
Field strength Ecali；Then, keep the power of transmitting antenna excitation constant, when there are composite material cabin structure, by receiving antenna
Measure electric field strength Et, and the test shield effectiveness SE of composite material cabin structure is calculatedtestWith test phase change coefficient
βtest。
It should be pointed out that the size of composite material, thickness, transmitting antenna distance apart from cabin structure center away from
From day line options and sweep interval in different frequency range etc. are not limited in parameter area described above.
In the S31, specifically: using the test shield effectiveness SE of composite material cabin structure obtained in S2test
With test phase change coefficient βtest, with composite material shield effectiveness SE obtained in S1calWith phase change coefficient βcalComputation model into
Row fitting, obtains the initial value ε of composite material equivalent relative dielectric constanter0And its it is fitted upper and lower limits and composite material
The initial value σ of equivalent conductivitye0And its fitting upper and lower limits.
Wherein, institute's fitting condition are as follows:
In a preferred embodiment of the invention, the composite material under cabin structure is (multiple using carbon fibre reinforced composite
Condensation material is generally made of two or more materials, is made of in the present embodiment carbon fiber and synthetic resin), wherein the carbon fiber used
The relative dielectric constant of dimension is about 1, and conductivity is about 500；The relative dielectric constant of resin matrix is about 5, and conductivity is
0.Therefore it obtains, the fitting upper and lower limits of composite material equivalent relative dielectric constant are (1,5), composite material equivalent conductivity
Fitting upper and lower limits be (0,500), the two fitting initial value be respectively εer0=1.18, σe0=104.20.
In the S32, specifically: establish the simulation model of composite material cabin structure as shown in Figure 2, the composite wood
Expect to be consistent in the parameter and S2 of cabin structure；Using composite material equivalent relative dielectric constant initial value εer0With equivalent electricity
Conductance initial value σe0Define the attribute of composite material；Excitation irradiation, setting transmitting are carried out using with transmitting antenna identical in S2
The excitation amplitude and frequency point of antenna, and the center that composite material cabin structure is arranged solves electric field；Obtain setting frequency point
The field intensity value of the center of composite material cabin structure；
When emulating calibration, in addition to being not provided with composite material cabin structure, remaining all parameter includes material properties, transmitting
Antenna, frequency point etc. with it is above identical, to obtain the calibration field intensity value of the center in no composite material cabin structure；
The field intensity value and calibration field intensity value are compared into the shield effectiveness to determine each frequency point of the composite material under cabin structure.
In a preferred embodiment of the invention, the simulation model of composite material cabin structure as shown in Figure 2 is established, it is related
Parameter as also shown in Figure 2, i.e. the length, width and height of the composite material cabin structure having a size of 1m × 1m × 1m, composite material with a thickness of
L=2.5mm.With relative dielectric constant εer0=1.18, conductivityσe0=104.20 define the attribute of composite material.
Using all antennas as transmitting antenna, are arranged at the 10m apart from cabin structure center, Electromagnetic Wave Propagation
Direction is perpendicular to the composite material plane on cabin structure.Being arranged to the port excitation amplitude of all antennas is 1, is respectively set three
Solve frequency point 200MHz, 400MHz and 600MHz；And the center (0,0,0) that composite material cabin structure is arranged solves electricity
?.It submits FEKO to calculate the project file of foundation, obtains the field of the center of the composite material cabin structure of setting frequency point
Intensity values.Another project file is established, in addition to being not provided with composite material cabin structure, remaining all parameter includes material properties, hair
Penetrate antenna, frequency point etc. with it is above identical, obtain the calibration field intensity value of the center in no composite material cabin structure；It will
The field intensity value and calibration field intensity value compares the shield effectiveness to determine each frequency point of the composite material under cabin structure.
Or it is arranged at the 10m apart from cabin structure center using double-ridged horn antenna as transmitting antenna, electricity
Electromagnetic wave propagation direction is perpendicular to the composite material plane on cabin structure.The port excitation amplitude that double-ridged horn antenna is arranged is 1,
Six solution frequency points 1GHz, 1.5GHz, 2.5GHz, 3GHz, 4GHz, 5GHz are respectively set；And composite material cabin structure is set
Center (0,0,0) solve electric field.Subsequent operation with it is above-mentioned identical to the simulation process of all antennas, to be calculated multiple
The shield effectiveness of each frequency point of the condensation material under cabin structure.
In the S33, specifically: the composite material obtained in S32 by simulation calculation is each under cabin structure
Test shield effectiveness of the composite material obtained in the shield effectiveness and S2 of frequency point by measuring and calculation under cabin structure carries out
The case where comparative evaluation, frequency point is unsatisfactory for required precision if it exists, need to a fixed step size correct relative dielectric constant initial value or
Conductivity initial value, and simulation calculation is re-started, until meeting required precision；Finally determine opposite Jie for meeting required precision
Permittivity values and conductivity value are the electromagnetic parameter of the composite material under cabin structure.
In a preferred embodiment of the invention, it is desirable that the composite material obtained in S32 by simulation calculation is in cabin structure
Under each frequency point shield effectiveness and S2 in the test shielding effect of the composite material that is obtained by measuring and calculation under cabin structure
The difference of energy is within 6dB.It is found after contrast simulation result and test result, it is poor in 3GHz frequency point emulation shield effectiveness and test
Value is greater than 6dB, is unsatisfactory for required precision.Since the simulation value of shield effectiveness is smaller, and the more big then shield effectiveness effect of conductivity
Preferably, therefore step-length 50S/m is selected to increase the value of conductivity and re-start above-mentioned simulation calculation.Finally work as εer0=1.18,
And σe0Meet required precision when=204.20, so that selected equivalent relative dielectric constant of the composite material under cabin structure is
1.18, equivalent conductivity 204.20.
As shown in figure 3, being εer0=1.18, and σe0When=204.20, screen that composite material emulates under cabin structure
It covers efficiency and tests the comparison of obtained shield effectiveness, the two is coincide preferably, and is met high-precision of the frequency point difference less than 6dB and wanted
It asks.It is indicated above the extracting method of composite material electromagnetic parameter under a kind of cabin structure of this patent proposition, can be aerospace
The electromagnetic protection design in device cabin provides the effective technology scheme that electrical parameter extracts.
In conclusion composite material Extraction of electromagnetic parameters method under cabin structure provided by the present invention, by constructing phase
To two sides be metal material, with four sides be composite material square body unit as cabin structure, for simulating
Composite material compartment environment.
And the present invention establishes electromagnetic parameter and shielding by homogenizing the composite material electromagnetic parameter under cabin structure
The computation model of efficiency, phase change coefficient；Then pass through the shield effectiveness and phase change coefficient under test composite material cabin structure, benefit
With the initial value of the computation model fitting test result inverting electromagnetic parameter of foundation；The electromagnetic parameter that finally inverting is obtained is initial
Value carries out simulation calculation shield effectiveness, and contrast simulation result and test result and constantly correcting emulate in electromagnetic parameter it is initial
Value, seeks the optimal solution for taking the electromagnetic parameter of the composite material under cabin structure.
It is discussed in detail although the contents of the present invention have passed through above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read above content, for of the invention
A variety of modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (9)
1. a kind of composite material Extraction of electromagnetic parameters method under cabin structure, which is characterized in that include step:
S1, the homogenization computation model for establishing composite material；
S2, shield effectiveness of the composite material under cabin structure and phase change coefficient are tested；
The Extraction of electromagnetic parameters of S3, composite material under cabin structure；Include:
S31, the initial value and equivalent conductivity initial value of composite material equivalent relative dielectric constant are obtained by fitting；
S32, the shield effectiveness that each frequency point of the composite material under cabin structure is obtained by simulation calculation；
S33, when the shield effectiveness of whole frequency points is all satisfied required precision, at the beginning of determining relative dielectric constant initial value and conductivity
Initial value is the electromagnetic parameter of the composite material under cabin structure, is otherwise re-started in terms of emulation by fixed step size amendment electromagnetic parameter
It calculates until meeting required precision.
2. composite material Extraction of electromagnetic parameters method under cabin structure as described in claim 1, which is characterized in that the S1
In, by the way that composite material is equivalent to homogeneous material, establish the shield effectiveness SE of composite materialcalComputation model, and establish
Phase change coefficient βcalWith composite material equivalent relative dielectric constant εer, equivalent conductivity σeBetween computation model.
3. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 2, which is characterized in that the S2
In, building composite material cabin structure is positive cube unit, and wherein two opposite side surfaces are set as metal material, remaining four side
Face is set as the unknown composite material of electromagnetic parameter, analog composite material compartment environment.
4. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 3, which is characterized in that the S2
In, receiving antenna is set in the center of composite material cabin structure, in the external setting transmitting of composite material cabin structure
Antenna simultaneously irradiates cabin structure；Transmitting antenna excitation irradiation under, by comparison whether there is or not when composite material cabin structure by connecing
The electric field strength and phase that antenna measurement is arrived are received, test shield effectiveness of the composite material under cabin structure and test phase transformation are obtained
Coefficient.
5. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 4, which is characterized in that composite material
Test shield effectiveness SE under cabin structuretestWith test phase change coefficient βtestCalculation formula are as follows:
Wherein, EtFor there are the electric fields that when composite material cabin structure, the receiving antenna of cabin structure center is detected
By force, EcaliFor there is no when composite material cabin structure, the electric field strength that receiving antenna detects, as electric field calibration value,For
Phase difference when electric field strength measures twice, l are the thickness of composite material.
6. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 5, which is characterized in that described
In S31, specifically: using the test shield effectiveness SE of composite material cabin structure obtained in S2testWith test phase change coefficient
βtest, with composite material shield effectiveness SE obtained in S1calWith phase change coefficient βcalComputation model be fitted, obtain it is compound
The initial value ε of material equivalent relative dielectric constanter0And its fitting upper and lower limits and composite material equivalent conductivity just
Initial value σe0And its fitting upper and lower limits.
7. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 6, which is characterized in that fitting condition
Are as follows:
8. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 6, which is characterized in that described
In S32, specifically:
Establish the simulation model with identical composite material cabin structure in S2；
Using composite material equivalent relative dielectric constant initial value εer0With equivalent conductivity initial value σe0Define the category of composite material
Property；
Excitation irradiation is carried out using with transmitting antenna identical in S2, the excitation amplitude and frequency point of transmitting antenna are set, and is arranged
The center of composite material cabin structure solves electric field；
The field intensity value of the center of composite material cabin structure when frequency point is set is obtained, and is tied in no composite material cabin
The calibration field intensity value of center when structure obtains the shielding effect of each frequency point of the composite material under cabin structure by comparing
Energy.
9. composite material Extraction of electromagnetic parameters method under cabin structure as claimed in claim 8, which is characterized in that described
In S33, specifically: by the shield effectiveness of each frequency point of the composite material obtained in S32 by simulation calculation under cabin structure
Assessment is compared with the test shield effectiveness of the composite material that obtains in S2 by measuring and calculation under cabin structure, if it exists
Frequency point is unsatisfactory for the case where required precision, corrects relative dielectric constant initial value or conductivity initial value, and re-start emulation
It calculates, until meeting required precision；Finally determine that the relative permittivity value and the conductivity value that meet required precision are cabin knot
The electromagnetic parameter of composite material under structure.
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| CN110472356A (en) * | 2019-08-21 | 2019-11-19 | 上海无线电设备研究所 | A kind of composite material electromagnetic parameters method under electromagnetic wave multiple angles of incidence degree |
| CN111122987A (en) * | 2019-12-26 | 2020-05-08 | 华北电力大学 | Magnetic field shielding effectiveness prediction method and system |
| CN112364524A (en) * | 2020-11-27 | 2021-02-12 | 上海无线电设备研究所 | Wide-frequency-band electromagnetic parameter acquisition method of multi-layer carbon fiber composite material |
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| CN110472356A (en) * | 2019-08-21 | 2019-11-19 | 上海无线电设备研究所 | A kind of composite material electromagnetic parameters method under electromagnetic wave multiple angles of incidence degree |
| CN110472356B (en) * | 2019-08-21 | 2023-07-07 | 上海无线电设备研究所 | Electromagnetic parameter calculation method for composite material under multiple incidence angles of electromagnetic waves |
| CN111122987A (en) * | 2019-12-26 | 2020-05-08 | 华北电力大学 | Magnetic field shielding effectiveness prediction method and system |
| CN111122987B (en) * | 2019-12-26 | 2020-12-04 | 华北电力大学 | Magnetic field shielding effectiveness prediction method and system |
| CN112364524A (en) * | 2020-11-27 | 2021-02-12 | 上海无线电设备研究所 | Wide-frequency-band electromagnetic parameter acquisition method of multi-layer carbon fiber composite material |
| CN112364524B (en) * | 2020-11-27 | 2022-12-23 | 上海无线电设备研究所 | Wide-frequency-band electromagnetic parameter acquisition method of multi-layer carbon fiber composite material |
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