CN110502864A - A kind of airframe and its electromagnet shield effect appraisal procedure - Google Patents
A kind of airframe and its electromagnet shield effect appraisal procedure Download PDFInfo
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- CN110502864A CN110502864A CN201910809451.2A CN201910809451A CN110502864A CN 110502864 A CN110502864 A CN 110502864A CN 201910809451 A CN201910809451 A CN 201910809451A CN 110502864 A CN110502864 A CN 110502864A
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- 230000000694 effects Effects 0.000 title claims abstract description 52
- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000004088 simulation Methods 0.000 claims abstract description 17
- 230000005684 electric field Effects 0.000 claims abstract description 16
- 230000005670 electromagnetic radiation Effects 0.000 claims abstract description 10
- 238000010586 diagram Methods 0.000 description 10
- 238000013461 design Methods 0.000 description 5
- 239000000945 filler Substances 0.000 description 5
- 238000012360 testing method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 235000013399 edible fruits Nutrition 0.000 description 2
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- 238000005457 optimization Methods 0.000 description 2
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Abstract
This application involves a kind of airframe electromagnet shield effect appraisal procedure, appraisal procedure includes: to establish the true gap structure model of gap structure respectively according to gap structure feature and electromagnet shield effect building and simplify gap structure model；Two models are emulated, and at least one structural parameters in gap structure model are simplified in variation, keep the simulation result of two models consistent, the structural parameters for simplifying gap structure model are obtained with this；Airframe model is constructed, and keeps the gap structure parameter in airframe model consistent with the structural parameters for simplifying gap structure model；It is arranged inside and outside electric field monitor and electromagnetic radiation source in airframe model, and emulates and obtains the first electromagnetism numerical value with airframe and the second electromagnetism numerical value except airframe, thus can get the electromagnet shield effect of airframe.
Description
Technical field
The application belongs to aircraft electromangnetic spectrum field, in particular to a kind of airframe electromagnet shield effect assessment side
Method and device.
Background technique
With the development of electronic technology, modern aircraft has been equipped with a large amount of electronic equipment, in addition, High power radar, electronics
The equipment of the high power radiation sources such as Jamming pod, High-Power Microwave equipment and electromagnetic pulse equipment and use, so that aircraft is flat
Stronger, more complicated electromagnetic environment is formed around platform.
The electromagnet shield effect of airframe is the important indicator parameter that aircraft adapts to external forceful electric power magnetic environment.Airframe
Electromagnet shield effect should be assessed at airplane design initial stage, to find the problem and to solve in time, evade design risk.
Existing airframe electromagnet shield effect means of testing and test scope are limited, and measuring accuracy is difficult to assess, and
It needs prototype to test, disconnects with airplane design process.
Summary of the invention
There is provided a kind of airframe electromagnet shield effect appraisal procedures for the purpose of the application, to solve or mitigate background
At least one problem in technology.
The technical solution of the application is: a kind of airframe electromagnet shield effect appraisal procedure, the appraisal procedure include:
True gap structure model and the institute of the gap structure are constructed according to gap structure feature and electromagnet shield effect
State that true gap structure model is corresponding to simplify gap structure model；
Emulate the true gap structure model and it is described simplify gap structure model, and simplify gap structure described in changing
At least one structural parameters in model, so that the emulation for simplifying gap structure model Yu the true gap structure model
As a result consistent, and the structural parameters of gap structure model are simplified described in acquisition；
The airframe model with the gap structure is constructed, and joins the gap structure in the airframe model
Number is consistent with the structural parameters for simplifying gap structure model；
Electric field monitor and electromagnetic radiation source are respectively set inside and outside the airframe model, the electromagnetic radiation source is released
The electromagnetic wave of preset frequency is put, and emulates the aircraft body structure model to obtain the first electromagnetism by the electric field monitor
Numerical value, and only remove the aircraft body structure model and simplify gap structure model to obtain the second electromagnetism numerical value, it is described
The difference of first electromagnetism numerical value and the second electromagnetism numerical value is the electromagnet shield effect of the airframe.
In one embodiment of the application, the gap structure includes airplane hatch cover and hatch door.
In one embodiment of the application, the structural parameters for simplifying fissures model include gap depth and slit width
Degree.
In one embodiment of the application, the gap depth is determined according to the gap actual depth；The slit width
Degree is set as variable, for matching the electromagnet shield effect characteristic of true gap structure.
In one embodiment of the application, the airframe model is according to the bay section distribution inside airframe, baffle
Distribution and device distribution building.
In one embodiment of the application, when airframe model construction, ignores cable complicated inside airframe
Harness, frame, hole and small device.
In one embodiment of the application, the electromagnetic radiation source load is plane wave.
In one embodiment of the application, minimum range of the plane wave away from airframe surface is greater than simulation frequency pair
Ten times for answering electromagnetic wavelength.
In one embodiment of the application, the difference includes that the first electromagnetism numerical value subtracts the second electromagnetism numerical value
And/or the second electromagnetism numerical value subtracts the first electromagnetism numerical value.
In addition, the airframe has electromagnet shield effect, the electromagnetism present invention also provides a kind of airframe
Shield effectiveness is determined according to as above any airframe electromagnet shield effect appraisal procedure.
The airframe electromagnet shield effect appraisal procedure of the application provides a kind of with true gap structure model
Equivalent method substitutes true fissures model using fissures model is simplified, had both remained the electromagnet shield effect of true fissures model
Characteristic, in turn avoids true fissures model generally existing flood tide mesh generation in simulations, substantially save computing resource and when
Between, in addition, the application can also quick and precisely assess the electromagnet shield effect of airframe at airplane design initial stage, set for aircraft
Meter is provided with reference to amendment foundation, gives the modeling method of airframe internal structure.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is the present processes flow diagram.
Fig. 2 is the true gap structure model (left side) at certain hatch door in one embodiment of the application and simplifies gap structure model
(right side) schematic diagram.
Fig. 3 is the true gap structure model (left side) at certain lid in one embodiment of the application and simplifies gap structure model
(right side) schematic diagram.
Fig. 4 is the electromagnet shield effect simulation result comparison diagram in gap at certain hatch door in above-described embodiment.
Fig. 5 is the electromagnet shield effect simulation result comparison diagram in gap at certain lid in above-described embodiment.
Fig. 6 is the hatch door (at forebody) of airframe and the position distribution of lid (at wing) in one embodiment of the application
Schematic diagram.
Fig. 7 is that schematic diagram is arranged in the electric field monitor in above-described embodiment inside airframe.
Fig. 8 is the electromagnet shield effect schematic diagram of noselanding gear well near zone in above-described embodiment.
Fig. 9 is the electromagnet shield effect schematic diagram of wing oil filler lid near zone in above-described embodiment.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
The application proposes that a kind of airframe electromagnet shield effect appraisal procedure based on numerical simulation, this method are suitable for
Airframe surface is equipped with all aircraft platforms that lid and hatch door etc. form gap structure, is the electromagnetic shielding of airframe
Measures of effectiveness provides foundation.
As shown in Figure 1, the application airframe electromagnet shield effect appraisal procedure includes the following steps:
S1, according to the true gap structure model of gap structure feature and electromagnet shield effect building gap structure and true
Gap structure model is corresponding to simplify gap structure model.
In this application, have apertured structure and generally include lid and hatch door etc..Simplify the structure of gap structure model
Parameter mainly includes gap depth and gap width, wherein gap depth is determining according to the actual (real) thickness in airframe, generally
It is chosen for 1 millimeter.The gap width for simplifying gap structure model is set as variable, can be used for matching the electromagnetism of true gap structure
Shield effectiveness characteristic.
Such as the true fissures model at the nose gear door of Fig. 1 left figure illustrated embodiment, it is corresponding to simplify gap
For model as shown in Fig. 1 right figure, the gap width after optimization is 0.2 millimeter (10-1000MHz frequency range) and 0.6 millimeter of (1000-
2000MHz frequency range), wherein simplifying gap is to blacken shown in straight line in Fig. 1 right figure.
True fissures model at the wing oil filler lid of Fig. 2 left figure illustrated embodiment, it is corresponding to simplify gap knot
For structure model as shown in Fig. 2 right figure, the gap width after optimization is 0.06 millimeter (100-200MHz frequency range), simplifies gap as figure
It is blackened shown in straight line in 2 right figures.
S2, it to true gap structure model and simplifies gap structure model and carries out electromagnet shield effect emulation, change simplifies
At least one structural parameters in gap structure model, so that simplifying the emulation of gap structure model Yu true gap structure model
As a result consistent, when result is consistent, obtains and record the structural parameters for simplifying gap structure model.
Since gap depth is usually varied less or is held essentially constant in true gap structure, and gap width is due to system
Making the reasons such as tolerance will cause variation, therefore in modeling and simulation, and it is logical to change the structural parameters simplified in gap structure model
It is often gap width, simplify gap structure model when emulation keeps simulation result consistent with true gap structure model, the essence of record
The structural parameters of simple gap structure model are gap width.
True fissures model is tied with the electromagnet shield effect emulation for simplifying fissures model in embodiment as shown in Figure 3 and Figure 4
Fruit comparison diagram, when simulation comparison result is more consistent, it was demonstrated that the slit width degree for simplifying fissures model chosen in above-mentioned steps
It is worth relatively reasonable.
S3, building have the airframe model of the gap structure, and join the gap structure in airframe model
Number is consistent with the structural parameters for simplifying gap structure model.
According to true distribution of the gap structure on airframe, chooses slot edge setting and simplify fissures model, simplify
The gap depth of gap structure model is traditionally arranged to be 1 millimeter, and gap width is the knot of the gap width recorded in above-mentioned steps
Fruit.
Be distributed when simulation model inside airframe constructs according to the main bay section distribution inside airframe, baffle,
Biggish device distribution of shape etc. is constructed.In addition, ignoring complexity inside airframe in airframe model construction
The factors such as cable harness, frame, hole and small device, these factors will increase dramatically simulation time, and simulation accuracy is not
Controllably.
The position distribution of nose gear door and wing oil filler lid in airframe, figure in embodiment as shown in Figure 6
Middle frame is the slot edge place of hatch door or lid.According to the slit width for simplifying gap structure model chosen in above-mentioned steps
Gap is simplified on degree, setting airframe surface.
Have when the organism internal structure of nose gear door region A1 is arranged, before and after landing gear compartment baffle carry out every
It is disconnected, be cockpit above landing gear compartment, separated between cockpit and landing gear compartment, ignore cable harness inside landing gear compartment,
Frame and the small device of installation etc..When the organism internal structure of wing oil filler lid region A2 is arranged, referring to above-mentioned
The organism internal structure of nose gear door region A1 is arranged, this place repeats no more.
S4, electric field monitor and electromagnetic radiation source are respectively set inside and outside airframe model, electromagnetic radiation source release is pre-
Determine the electromagnetic wave of frequency, and emulates aircraft body structure model to obtain the first electromagnetism numerical value by electric field monitor, and only
Removal aircraft body structure model and simplify gap structure model and other settings are constant to obtain the second electromagnetism numerical value, first is electric
Magnetic number value and the difference of the second electromagnetism numerical value are the electromagnet shield effect of airframe.
In this application, electric field monitor need to be arranged near the gap of internal body, to improve monitoring accuracy.In body
The electromagnetic radiation source of outside setting can be realized by loaded antenna or loaded planar wave.Wherein, when loaded planar wave, plane
The minimum range on pitch of waves airframe surface should be greater than ten times that simulation frequency corresponds to electromagnetic wavelength.
In the embodiment of the present application, in emulation twice, the numerical value that electric field monitor obtains is converted into dB value, passes through dB
The difference of value can get the electromagnet shield effect of lid or hatch door.Wherein, difference can be electric field monitor in second of emulation
The numerical value of acquisition subtracts the numerical value that electric field monitor obtains in emulation for the first time, or electric field monitor in emulation for the first time
The numerical value of acquisition subtracts the numerical value that electric field monitor obtains in second of emulation.
It is monitored in embodiment as shown in Figure 7 in nose gear door region and wing oil filler lid region setting electric field
Device successively carries out electromagnet shield effect emulation twice, calculates electromagnet shield effect, electromagnetism by the result of electric field monitor twice
Shield effectiveness simulation result is as shown in Figure 7 and Figure 8.Pass through the electricity for making the difference available corresponding site of attached drawing upper and lower in Fig. 7 or Fig. 8
Magnetic screen efficiency.
Finally, the airframe has electromagnet shield effect, the electromagnetism present invention also provides a kind of airframe
Shield effectiveness is determined according to above-mentioned airframe electromagnet shield effect appraisal procedure.
The airframe electromagnet shield effect appraisal procedure of the application has the advantages that
1) the present processes provide the equivalent method of lid or the true fissures model of hatch door, using simplifying fissures model
True fissures model is substituted, the electromagnet shield effect characteristic of true fissures model has both been remained, has in turn avoided true fissures model
Generally existing flood tide mesh generation in simulations substantially saves computing resource and time.
2) the present processes can quick and precisely assess the electromagnet shield effect of airframe at airplane design initial stage, be
Airplane design is provided with reference to amendment foundation, gives the modeling method of airframe internal structure.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of airframe electromagnet shield effect appraisal procedure, which is characterized in that the appraisal procedure includes
The true gap structure model of the gap structure and described true is constructed according to gap structure feature and electromagnet shield effect
Real gap structure model is corresponding to simplify gap structure model；
Emulate the true gap structure model and it is described simplify gap structure model, and simplify gap structure model described in changing
In at least one structural parameters so that the simulation result for simplifying gap structure model Yu the true gap structure model
Unanimously, and described in acquisition the structural parameters of gap structure model are simplified；
Construct the airframe model with the gap structure, and make gap structure parameter in the airframe model with
The structural parameters for simplifying gap structure model are consistent；
Electric field monitor and electromagnetic radiation source are respectively set inside and outside the airframe model, the electromagnetic radiation source release is pre-
Determine the electromagnetic wave of frequency, and emulates the aircraft body structure model to obtain the first electromagnetism number by the electric field monitor
Value, and only remove the aircraft body structure model and simplify gap structure model to obtain the second electromagnetism numerical value, described the
The difference of one electromagnetism numerical value and the second electromagnetism numerical value is the electromagnet shield effect of the airframe.
2. airframe electromagnet shield effect appraisal procedure as described in claim 1, which is characterized in that the gap structure packet
Include airplane hatch cover and hatch door.
3. airframe electromagnet shield effect appraisal procedure as described in claim 1, which is characterized in that described to simplify slit die
The structural parameters of type include gap depth and gap width.
4. airframe electromagnet shield effect appraisal procedure as claimed in claim 3, which is characterized in that the gap depth root
It is determined according to the gap actual depth；
The gap width is set as variable, for matching the electromagnet shield effect characteristic of true gap structure.
5. airframe electromagnet shield effect appraisal procedure as described in claim 1, which is characterized in that the airframe mould
Type is constructed according to bay section distribution, baffle distribution and the device distribution inside airframe.
6. airframe electromagnet shield effect appraisal procedure as claimed in claim 5, which is characterized in that the airframe mould
Type ignores cable harness, frame, hole and small device complicated inside airframe when constructing.
7. airframe electromagnet shield effect appraisal procedure as described in claim 1, which is characterized in that the electromagnetic radiation source
It is realized by loaded planar wave or antenna.
8. airframe electromagnet shield effect appraisal procedure as claimed in claim 7, which is characterized in that the plane wave is away from winged
The minimum range of machine body surface is greater than ten times that simulation frequency corresponds to electromagnetic wavelength.
9. airframe electromagnet shield effect appraisal procedure as described in claim 1, which is characterized in that the difference includes institute
State that the first electromagnetism numerical value subtracts the second electromagnetism numerical value and/or the second electromagnetism numerical value subtracts the first electromagnetism numerical value.
10. a kind of airframe, which is characterized in that the airframe has electromagnet shield effect, the electromagnet shield effect
It is determined according to airframe electromagnet shield effect appraisal procedure as described in any one of claim 1 to 9.
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Cited By (4)
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| CN113056184A (en) * | 2021-03-15 | 2021-06-29 | 上海应用技术大学 | Shielding net simulation design method based on optimized interference signal and whole framework |
| CN113311250A (en) * | 2020-02-26 | 2021-08-27 | 上海飞机制造有限公司 | Cable braided shielding layer shielding effectiveness evaluation method, device, equipment and medium |
| CN116187109A (en) * | 2023-04-27 | 2023-05-30 | 北京航天天美科技有限公司 | Radio frequency interface window structure simulation optimization method |
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Application publication date: 20191126 |