CN110276109A - A kind of emulation mode of hypersonic aircraft plasma sheath electromagnetic property - Google Patents
A kind of emulation mode of hypersonic aircraft plasma sheath electromagnetic property Download PDFInfo
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Abstract
The invention discloses a kind of emulation modes of hypersonic aircraft plasma sheath electromagnetic property.This method are as follows: fluid emulation is carried out according to the geometric shape of hypersonic aircraft and flight parameter first, is determined by artificial intelligence and applies plasma collision frequency, plasma oscillation frequency and the electron gyro-frequency parameter of electromagnetic field condition down space everywhere；Then the grid file for extracting plasma target, is arranged incident electromagnetic wave parameter；Then using the current density of plasma medium part in the alternative manner zoning of plasma, using the current density at magnetic field boundaries condition calculating plasma medium and air interface, update is iterated using current density vectors single step more new formula；Plasma electromagnetic property is obtained finally by analysis time domain waveform.The present invention has the advantages that programming is simple, computational efficiency is high, realizes the efficient analysis to hypersonic aircraft plasma sheath.
Description
Technical field
The present invention relates to electromagnetic simulation technique field, especially a kind of hypersonic aircraft plasma sheath electromagnetism is special
The emulation mode of property.
Background technique
When aircraft hypersonic flight, aircraft surface and air generate fierce friction, and squeeze empty around
Gas, the air near aircraft are in viscous state, form the high-temperature area of a thousands of Kelvins, make ambient air
Ionization forms high temperature and pressure plasma sheath.Under normal circumstances, the electron density in plasma sheath can reach 1016~
1018m-3.High electron number densitiy can cause serious negative effect to the communication of aircraft, so needing to utilize numerical method pair
Propagation characteristic of the electromagnetic wave in plasma sheath is analyzed, and is mentioned to communicate under the conditions of the realization black barrier of hypersonic aircraft
For technical foundation.
Currently with the electromagnetic property of FDTD analysis hypersonic aircraft plasma sheath, there are two
A problem: (1) efficient emulation of high cyclotron frequency magnetized plasma is difficult to realize: since Nyquist sampling thheorem requires now
There are current density in finite difference calculus, electric field, magnetic field time step sufficiently small, so that the Electromagnetic Simulation of plasma be made to be difficult to height
Effect is realized；(2) for being difficult to handle at plasma medium and air interface, and it is unstable to easily lead to boundary numerical value, from
And the emulation of plasma medium electromagnetic property is difficult to realize.
Summary of the invention
The hypersonic aircraft plasma sheath that the purpose of the present invention is to provide a kind of adaptability is good, computational efficiency is high
Cover the emulation mode of electromagnetic property.
The technical solution for realizing the aim of the invention is as follows: a kind of hypersonic aircraft plasma sheath electromagnetic property
Emulation mode comprising the steps of:
Step 1 carries out fluid emulation according to the geometric shape of hypersonic aircraft, flight parameter and application electromagnetic field,
Plasma collision frequency, plasma oscillation frequency parameter and the electron gyro-frequency ginseng of space everywhere are determined by artificial intelligence
Number distribution；
Incident electromagnetic wave parameter is arranged in step 2, the grid file for extracting plasma target；
Step 3 uses the current density of plasma medium part in the alternative manner zoning of plasma, use
Then current density at magnetic field boundaries condition calculating plasma medium and air interface uses current density vectors single step
More new formula is iterated update；
Step 4 obtains plasma sheath electromagnetic property by analysis time domain waveform.
Compared with prior art, the present invention its remarkable advantage are as follows: (1) time step of current density vectors and electric field and magnetic
The time step of field is different, and such current density vectors use the time step progress difference less than electric and magnetic fields to make electric field
It is reduced with the iterative steps in magnetic field, then reduces and calculate the time, realize efficiently dividing for plasma Electromagnetic Characters of Target
Analysis；(2) for the processing of plasma medium and air interface, the numerical stability at interface is improved, is improved pair
The accuracy of plasma Electromagnetic Characters of Target analysis.
Detailed description of the invention
Fig. 1 is the flow diagram of the emulation mode of hypersonic aircraft plasma sheath electromagnetic property of the present invention.
Fig. 2 is current density vectors spatial distribution schematic diagram in the present invention.
Fig. 3 is time step distribution schematic diagram in the present invention.
Fig. 4 is in the embodiment of the present invention using the schematic diagram of the method for the present invention verifying plasma object construction.
Fig. 5 is when using the method for the present invention and business software CST, Runge Kutta exponential time differencing in the embodiment of the present invention
The comparative result figure of domain finite differential analysis magnetized plasma Radar Cross Section.
Fig. 6 is that the method for the present invention is under the conditions of magnetized plasma high electron gyro-frequency in the embodiment of the present invention, electric current
Density hours step-length and electric field, magnetic field time step are schemed with the profiles versus that electron gyro-frequency changes.
Specific embodiment
Present invention is further described in detail in the following with reference to the drawings and specific embodiments.
For super speed vehicle, plasma sheath, plasma will form around aircraft during high-speed flight
Sheath and electromagnetic wave phase interaction mechanism are complex, and existing Finite-Difference Time-Domain Method is difficult to efficient analysis.
The emulation mode of hypersonic aircraft plasma sheath electromagnetic property of the present invention comprising the steps of:
Step 1 carries out fluid emulation according to the geometric shape of hypersonic aircraft, flight parameter and application electromagnetic field,
Plasma collision frequency, plasma oscillation frequency parameter and the electron gyro-frequency ginseng of space everywhere are determined by artificial intelligence
Number distribution；
Incident electromagnetic wave parameter is arranged in step 2, the grid file for extracting plasma target；
Step 3 uses the current density of plasma medium part in the alternative manner zoning of plasma, use
Then current density at magnetic field boundaries condition calculating plasma medium and air interface uses current density vectors single step
More new formula is iterated update；
Step 4 obtains plasma sheath electromagnetic property by analysis time domain waveform.
Further, plasma medium portion in the alternative manner zoning of plasma is used described in step 3
The current density divided, specific as follows:
The calculating of the current density of plasma medium part in region, formula are carried out using the iterative formula of plasma
It is as follows:
In formulaC=A-1B, A-1For the inverse square of matrix A
Battle array,It is third-order plant；ΔtcFor the time step that current density vectors update, ε is vacuum
Medium dielectric constant microwave medium, n are time step, and M is that current density vectors single step updates total step-length, and k is current density vectors single step update
Kth step in the process, ωpFor plasma oscillation frequency, I is three rank unit square matrixes, J=[Jx Jy Jz]TFor in plasma
Current density vectors；E=[Ex Ey Ez]TFor electric field strength in plasma；V is plasma collision frequency, ωx、ωy、ωz
For the x, y, z durection component of electron gyro-frequency.
Further, at the condition calculating plasma medium of use magnetic field boundaries described in step 3 and air interface
Current density, it is specific as follows:
The current density vectors of heating region are in Yee grid element center, calculate the formula of boundary current density such as
Under:
Wherein Δ Hx=H1x-H2x、ΔHy=H1y-H2y、ΔHz=H1z-H2zRespectively boundary face two sides changes of magnetic field amount
X, y, z durection component, H1x、H1y、H1zFor magnetic field size x, y, z durection component, H in medium 12x、H2y、H2zFor magnetic field in medium 2
Size x, y, z durection component, nx、ny、nzRespectively interface other unit normal vector x, y, z durection component, formula (2) discrete scheme
It is then as follows:
It is the interface in the direction x for normal vector, boundary is discrete the direction y and the tangential current density on the direction z
Format difference is as follows:
It is the interface in the direction y for normal vector, boundary is discrete the direction x and the tangential current density on the direction z
Format difference is as follows:
It is the interface in the direction z for normal vector, boundary is discrete the direction x and the tangential current density on the direction y
Format difference is as follows:
Wherein, i, j, k are respectively the space nodes on x, y, z direction, I, j, k-space node respectively on x, y, z direction are translated forward or backwardFor in x
Space nodes are on directionCurrent density,It is for space nodes in y-directionCurrent density,It is for space nodes in a z-directionCurrent density.
Embodiment 1
The present embodiment analyzes the emulation mode of hypersonic aircraft plasma sheath electromagnetic property, in Finite Difference-Time Domain
It is proposed that current density vectors single step updates formula method plasma electromagnetic property and carries out analogue simulation, tool on the basis of point-score
Steps are as follows for body:
Step 1 carries out fluid emulation according to the geometric shape of hypersonic aircraft, flight parameter and application electromagnetic field,
Plasma collision frequency, plasma oscillation frequency parameter and the electron gyro-frequency ginseng of space everywhere are determined by artificial intelligence
Number distribution；
Incident electromagnetic wave parameter is arranged in step 2, the grid file for extracting plasma target；
Step 3 uses the current density of plasma medium part in the alternative manner zoning of plasma, use
Then current density at magnetic field boundaries condition calculating plasma medium and air interface uses current density vectors single step
More new formula is iterated update, specific as follows:
Described is iterated using current density vectors single step more new formula, plasma medium part in update area
Current density, it is specific as follows in conjunction with Fig. 1:
Step 3.1: n+1/2 moment magnetic field H is calculated by seamed edge n moment electric field E at the center of face；
Step 3.2: n moment electric field E is specific as follows by seamed edge n moment electric field E solution procedure at center:
Current density vectors spatial distribution is as shown in Fig. 2, be in Yee net center of a lattice.And electric field has three in Yee cellular
A durection component is respectively defined in the seamed edge position non-center position of Yee cellular, so the electric field intensity in center is not
It can directly acquire, but need to carry out space interpolation, formula are as follows:
The center step 3.3:Yee n+1/2 moment current density, Jn+1/2By the center Yee n moment electric field EnIt is counted
It calculates, specific as follows:
Current density vectors use different time steps from electric field, magnetic field, as shown in figure 3, formula is as follows:
In formulaC=A-1B, A-1For the inverse square of matrix A
Battle array,It is third-order plant；ΔtcFor the time step that current density vectors update, ε is vacuum
Medium dielectric constant microwave medium, n are time step, and M is that current density vectors single step updates total step-length, and k is current density vectors single step update
Kth step in the process, ωpFor plasma oscillation frequency, I is three rank unit square matrixes, J=[Jx Jy Jz]TFor in plasma
Current density vectors；E=[Ex Ey Ez]TFor electric field strength in plasma；V is plasma collision frequency, ωx、ωy、ωz
For the x, y, z durection component of electron gyro-frequency.
Current density, J at step 3.4:Yee grid seamed edge by Yee grid element center current density, Jn+1/2It is counted
It calculates, if the seamed edge currently calculated is not at zoning boundary, is calculated with formula (5a)~(5c)；If at current calculated position
In zoning boundary, then calculated with formula (7a)~(7f)；It is specific as follows:
The current density vectors acquired are in the center of Yee cellular, and when participating in electric field update, electric field is close with electric current
It is different to spend the spatial position being in.Electric field location is defined on seamed edge, and the center of Yee cellular is in current density vectors
Difference then needs to carry out the current density vectors J that space interpolation obtains seamed edge position, formula are as follows:
The current density design of boundary calculates calculation formula are as follows:
Wherein Δ Hx=H1x-H2x、ΔHy=H1y-H2y、ΔHz=H1z-H2zRespectively boundary face two sides changes of magnetic field amount
X, y, z durection component, H1x、H1y、H1zFor magnetic field size x, y, z durection component, H in medium 12x、H2y、H2zFor magnetic field in medium 2
Size x, y, z durection component, boundary current density formula (6) discrete scheme are as follows:
It is the interface in the direction x for normal vector, tangential current density of the boundary on the direction y and the direction z respectively
Discrete scheme is as follows:
It is the interface in the direction y for normal vector, tangential current density of the boundary on the direction x and the direction z respectively
Discrete scheme is as follows:
It is the z interface in direction for normal vector, tangential current density of the boundary on the direction x and the direction y respectively
Discrete scheme is as follows:
Wherein, i, j, k are respectively the space nodes on x, y, z direction, I, j, k-space node respectively on x, y, z direction are translated forward or backwardFor in x
Space nodes are on directionCurrent density,It is for space nodes in y-directionCurrent density,It is for space nodes in a z-direction Electric current
Density.
The iterative formula in magnetic field is identical as common Finite-Difference Time-Domain Method
The electric field value E at step 3.5:n+1 moment is by n+1/2 at Yee cellular face center n+1/2 moment magnetic field H and seamed edge
Moment current density, J is calculated and is obtained, and as the initial value for calculating n+2 quarter electric field E, return step 3.1, until n is equal to regulation
Time iteration step number, iteration terminate.
Step 4, by analyzing time domain waveform, plasma sheath electromagnetic property is obtained.
In conjunction with Fig. 4, Fig. 5, the method emulates magnetized plasma dielectric cube according to the present invention, magnetization
A height of 0.6m × the 0.6m of bulk length and width × 0.6m of plasma cube；The additional magnetic field along Z axis positive direction；Plasma
The angular frequency of bodyp=2 π × 28.7 × 108Rad/s, collision frequency vc=2 × 108Hz, electron gyro-frequency ωce=2 π ×
108Rad/s meets stability condition；Plane wave is the incidence of edge+Z axis, and polarization direction is X-direction；Mesh generation having a size of
0.005m, observed frequency 300MHz；Total time iterative steps are 2000 steps.Calculated result is as shown in figure 5, verifying the method for the present invention
Correctness.
If Fig. 6 is current density time step and electric field, magnetic field under the conditions of magnetized plasma high electron gyro-frequency
Time step is with electron gyro-frequency change profile comparison diagram.For the magnetized plasma under the conditions of high electron gyro-frequency,
To the difference of electric field, magnetic field and current density in existing Runge Kutta exponential time differencing Finite-Difference Time-Domain Method (RKE-FDTD)
Using identical time step, and the time step of current density vectors is different from the time step of electric and magnetic fields, Qian Zhe little
In the latter, such current density vectors use the time step progress difference less than electric and magnetic fields to make changing for electric and magnetic fields
Number of riding instead of walk is reduced, and is then reduced and is calculated the time.
In conclusion current density vectors list is used in the present invention when hypersonic aircraft heating region calculates
Step more new formula is iterated update, and rest part uses conventional Time-domain finite difference calculus iteration, can accurate simulation calculating
High electron gyro-frequency plasma sheath electromagnetic property.
Claims (3)
1. a kind of emulation mode of hypersonic aircraft plasma sheath electromagnetic property, which is characterized in that include following step
It is rapid:
Step 1 carries out fluid emulation according to the geometric shape of hypersonic aircraft, flight parameter and application electromagnetic field, by imitating
True information determines plasma collision frequency, plasma oscillation frequency parameter and the electron gyro-frequency parameter of space everywhere point
Cloth；
Incident electromagnetic wave parameter is arranged in step 2, the grid file for extracting plasma target；
Step 3, using the current density of plasma medium part in the alternative manner zoning of plasma, use magnetic field
Then current density at boundary condition calculating plasma medium and air interface is updated using current density vectors single step
Formula is iterated update；
Step 4 obtains plasma sheath electromagnetic property by analysis time domain waveform.
2. the emulation mode of hypersonic aircraft plasma sheath electromagnetic property according to claim 1, feature
It is, using the current density of plasma medium part in the alternative manner zoning of plasma described in step 3,
It is specific as follows:
The calculating of the current density of plasma medium part in region is carried out using the iterative formula of plasma, formula is such as
Under:
In formulaC=A-1B, A-1For the inverse matrix of matrix A,It is third-order plant；ΔtcFor the time step that current density vectors update, ε is vacuum intermediary
Electric constant, n are time step, and M is that current density vectors single step updates total step-length, and k is current density vectors single step renewal process
In kth step, ωpFor plasma oscillation frequency, I is three rank unit square matrixes, J=[Jx Jy Jz]TFor electric current in plasma
Density Vector；E=[Ex Ey Ez]TFor electric field strength in plasma；V is plasma collision frequency, ωx、ωy、ωzFor electricity
The x, y, z durection component of sub- cyclotron frequency.
3. the emulation mode of hypersonic aircraft plasma sheath electromagnetic property according to claim 1, in step 3
The described current density using at magnetic field boundaries condition calculating plasma medium and air interface, specific as follows:
The current density vectors of heating region are in Yee grid element center, and the formula for calculating boundary current density is as follows:
Wherein Δ Hx=H1x-H2x、ΔHy=H1y-H2y、ΔHz=H1z-H2zThe respectively x, y, z of boundary face two sides changes of magnetic field amount
Durection component, H1x、H1y、H1zFor magnetic field size x, y, z durection component, H in medium 12x、H2y、H2zFor magnetic field size x in medium 2,
Y, z durection component, nx、ny、nzRespectively interface other unit normal vector x, y, z durection component, formula (2) discrete scheme are then as follows:
It is the interface in the direction x, the discrete scheme of tangential current density of the boundary on the direction y and the direction z for normal vector
It is as follows respectively:
It is the interface in the direction y, the discrete scheme of tangential current density of the boundary on the direction x and the direction z for normal vector
It is as follows respectively:
It is the interface in the direction z, the discrete scheme of tangential current density of the boundary on the direction x and the direction y for normal vector
It is as follows respectively:
Wherein, i, j, k are respectively the space nodes on x, y, z direction,
I, j, k-space node respectively on x, y, z direction are translated forward or backward For space in the x direction
Node isCurrent density,It is for space nodes in y-directionElectricity
Current density,It is for space nodes in a z-directionCurrent density.
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| CN112257261A (en) * | 2020-10-22 | 2021-01-22 | 西安电子科技大学 | Antenna, aircraft platform and plasma sheath integrated simulation analysis method |
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| CN110837688A (en) * | 2019-09-30 | 2020-02-25 | 西安电子科技大学 | Total field/scattered field plane wave source generation method in plasma sheath 3D-FDTD modeling |
| CN111259514A (en) * | 2019-12-26 | 2020-06-09 | 兰州空间技术物理研究所 | Full-flow numerical simulation system of Hall thruster and full-flow numerical simulation method using same |
| CN111665014A (en) * | 2020-05-20 | 2020-09-15 | 中国科学院力学研究所 | Hypersonic aircraft boundary layer electron density diagnostic system based on high-frequency electrostatic probe |
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| CN112257261A (en) * | 2020-10-22 | 2021-01-22 | 西安电子科技大学 | Antenna, aircraft platform and plasma sheath integrated simulation analysis method |
| CN116008946A (en) * | 2023-03-27 | 2023-04-25 | 中国人民解放军63921部队 | Automatic judging method and system for plasma sheath of near space high dynamic aircraft |
| CN116008946B (en) * | 2023-03-27 | 2023-06-09 | 中国人民解放军63921部队 | Automatic judging method and system for plasma sheath of near space high dynamic aircraft |
| CN117217065A (en) * | 2023-10-07 | 2023-12-12 | 北京航空航天大学 | Fuel system gap radio frequency discharge characteristic analysis method based on dynamic sheath analysis |
| CN117864385A (en) * | 2024-03-11 | 2024-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic aircraft plasma sheath control device and flow field parameter algorithm |
| CN117864385B (en) * | 2024-03-11 | 2024-05-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic aircraft plasma sheath control device and flow field parameter algorithm |
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