CN103186697A - Method for AEWA (Airborne Early Warning Aircraft) radar detection target simulation - Google Patents

Abstract

The invention discloses a method for AEWA (Airborne Early Warning Aircraft) radar detection target simulation and mainly solves the problem that a radar cross section of a target guided missile in a half space cannot be calculated under high frequency in the prior art. The method is implemented by the following steps: establishing a model schematic diagram of the target guided missile by using commercial HFSS (High Frequency Structure Simulator) software, and performing triangulation on the model schematic diagram of the target guided missile by using commercial femap software; importing the model schematic diagram of the target guided missile after triangulation in the form of STL (Standard Template Library) text to acquire the profile data information of the target guided missile in the form of the STL text; introducing a green function in the half space into a physical optics method, and calculating the profile data information of the target guided in the form of STL text to acquire the radar cross section of the target guided missile in the half space; and calculating echo signals of the target guided missile received by radar according to the radar cross section of the target guided missile in the half space. According to the invention, the echo signals of the target guided missile can be accurately figured out. The method can be used for AEWA radar system stimulation, and provides technical support for maximally playing the power of a cruise missile weapon system.

Description

Early warning plane radar detection target simulation method

Technical field

The invention belongs to wireless communication field, relate to detection system and the detection method thereof of antenna resonant frequency, can be used for the early warning plane radar detection simulation.

Technical background

Early warning plane is a kind of perfect electronic equipments such as Reconnaissance, Long Range radar, data processing, enemy and we's identification and communication and navigation, commander's control, electronic countermeasure that are equipped with, integrate early warning, Command, Control, Communication And Intelligence, for searching for, monitor and follow the tracks of operational support aircraft aerial and that naval target is also commanded, guiding one's own side aircraft is carried out combat duty, play the effect of moving radar station and Air Operation Center.Early warning plane can reduce the influence of earth curvature and various atural objects, thereby can increase hunting zone and the detection range of radar greatly, increases pre-warning time.For the cruise missile's target of flight in the home radar chain blind area, early warning plane can and give a warning in remote discovery target, becomes the prominent anti-biggest threat of cruise missile's target.The core equipment of early warning plane is exactly its airborne radar, and therefore, simulation study is to carry out the early warning plane operation to use one of important content of research to the airborne early warn ing radar detection of a target.

Present early warning plane radar detection target simulator mainly comprises: early warning plane modeling, the modeling of missile-radars characteristic, clutter Modeling Research and guided missile detection obtain echoed signal.Conventional method is that above-mentioned four modules are calculated emulation respectively separately, in missile-radars characteristic MBM, a lot of RCS computer-aided analyses and optimizing Design Software bag have been emerged based on various high frequency algorithms at present, though the accurate emulation of free space TV university size objectives RCS can be simulated and can be finished in real time to these software packages, but up to the present, the RCS high frequency computing method about semispace target guided missile yet there are no report.

Summary of the invention

The purpose of this invention is to provide a kind of early warning plane radar detection target simulation method, can not under high frequency, calculate the problem of the RCS of semispace target guided missile to solve prior art, obtain target guided missile echoed signal.

For achieving the above object: technical scheme of the present invention comprises the steps:

(1) obtains the target guided missile shape data information of STL text formatting

1a) utilize HFSS software to set up the model synoptic diagram of target guided missile according to target guided missile physical size;

1b) from the discrete data point at the model synoptic diagram edge of target guided missile, take out 4 wherein adjacent points arbitrarily; Appoint the quadratic sum minimum criteria of the difference on both sides to carry out triangle division according to triangle to these 4, selected wherein 3 and connect;

1c) for remaining discrete data point, repeating step 1b), be joined together the target guided missile synoptic diagram after obtaining handling up to all discrete data points;

1d) the target guided missile synoptic diagram after will handling is with the output of STL text formatting, and extracts the shape data information of target guided missile from output file, for the target guided missile provides shape data accurately in the calculating of the RCS of semispace;

(2) calculate the target guided missile at the RCS σ of semispace

To introduce in the physical optics method at the Green function of semispace, the shape data of STL text formatting target guided missile will be calculated, obtain the target guided missile at the scattering cross-section σ of semispace:

$\sqrt{\mathrm{\σ}}=\underset{R\→\∞}{\lim }2\sqrt{\mathrm{\π}}R\frac{E_s\·{\hat{e}}_r}{E_o}\exp \left(\mathrm{jkR}\right)$

That is: $\mathrm{\σ}={\left(\underset{R\→\∞}{\lim }2\sqrt{\mathrm{\π}}R\frac{E_s\·{\hat{e}}_r}{E_o}\exp \left(\mathrm{jkR}\right)\right)}^2,$

In the formula, R is the round trip distance from the early warning plane radar to the target Missile Center, E _oBe the incident electric field,

Be the unit vector of target guided missile electric polarization direction, k is propagation constant, E _sFor target guided missile scattering electric field, under far field condition, arrive the distance of far field observation point much larger than the characteristics of target guided missile size according to the target guided missile, obtain E _sFollowing expression:

$E_s=-\mathrm{j\ω}{\∫\∫\∫}_v{\stackrel{\‾}{G}}_A(r,r^{\′})\·J\left(r^{\′}\right)d{r}^{\′}+\frac{k\·\hat{s}}{\mathrm{\ω}}{\∫\∫\∫}_v[G_x^{\mathrm{qe}}\frac{\∂}{\∂x}J\left(r^{\′}\right)+G_y^{\mathrm{qe}}\frac{\∂}{\∂y}J\left(r^{\′}\right)+G_z^{\mathrm{qe}}\frac{\∂}{\∂z}J\left(r^{\′}\right)]d{r}_s^{\′}$

In the formula, ω is the incident wave frequency, and J (r ') is current density, and k is propagation constant,

Be the unit vector of scattering wave polarised direction,

Be the Green function at semispace:

${\stackrel{\‾}{G}}_A(r,r^{\′})=\left[\begin{array}{ccc}{G}_A^{\mathrm{xx}}& 0& 0\\ 0& G_A^{\mathrm{yy}}& 0\\ G_A^{\mathrm{zx}}& G_A^{\mathrm{zy}}& G_A^{\mathrm{zz}}\end{array}\right]$

In the formula

$G_A^{\mathrm{xx}}=\frac{\mathrm{\μ}}{4\mathrm{\π}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+A_h^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{zx}}=-\frac{\mathrm{\μ}}{8\mathrm{\π}}\frac{\∂}{\∂x}{\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)\left[\frac{k_z}{k_{\mathrm{\ρ}}^2}(C_h^e-A_h^e)e^{-j{k}_{z}z}\right]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{zz}}=\frac{\mathrm{\μ}}{4\mathrm{\π}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+A_v^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{yy}}=G_A^{\mathrm{xx}}$ $G_A^{\mathrm{zy}}=G_A^{\mathrm{zx}};$

Be the scalar potential function:

$G_x^{\mathrm{qe}}=-\frac{j}{8\mathrm{\π\ϵ}}{\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+\frac{k^2{A}_h^e+k_z^2{C}_h^e}{k_{\mathrm{\ρ}}^2}{e}^{j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_y^{\mathrm{qe}}=G_x^{\mathrm{qe}}$

$G_z^{\mathrm{qe}}=\frac{1}{4\mathrm{\π\ϵ}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+C_v^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

Wherein:

$A_h^e=R_{\mathrm{TE}}{e}^{-j{k}_z{z}^{\′}},$ $C_h^e=-R_{\mathrm{TM}}{e}^{-j{k}_z{z}^{\′}},$ $A_v^e=R_{\mathrm{TE}}{e}^{-j{k}_z{z}^{\′}},$ $C_v^e=-R_{\mathrm{TM}}{e}^{-j{k}_z{z}^{\′}}$

In the formula, R _TE, R _TMBe fresnel reflection coefficient, k _x, k _y, k _zFor along the propagation constant on x, y, the z direction,

Be the second class zeroth order Hankel function, ε is specific inductive capacity;

The physical optics of current density, J (r ') is approximate:

$J\left(r^{\′}\right)=2\hat{n}\×H_0$

In the formula,

Be the method vector of target guided missile, H ₀The incident wave magnetic field intensity;

(3) calculate target guided missile echoed signal

Based on radar equation, consider radar system loss, radar operation wavelength, pulse peak power, radar system loss parameter situation, utilize the target guided missile at the scattering cross-section σ of semispace, calculate radar and receive target guided missile echo signal amplitude For:

In the formula: P _tBe the radar emission signal peak power, λ is the radar operation wavelength, and σ is that the target guided missile is long-pending in the RCS of semispace, G (α _T, β _T) be the radar antenna voltage gain, L is that radar emission receives composite loss, R is that radar arrives target Missile Center distance.

The present invention has following advantage:

1. the present invention utilizes HFSS software to set up the model synoptic diagram of target guided missile, utilize commercial femap software that the model synoptic diagram of target guided missile is carried out triangle division, target guided missile synoptic diagram after the triangle division is exported with the STL text formatting, and from output file, extract the shape data information of target guided missile, for the target guided missile provides shape data accurately in the calculating of the RCS of semispace.

2. the present invention introduces the semispace Green function in the physical optical method, and calculating is quick, simple, has solved prior art and can not calculate the target guided missile in the problem of the RCS of semispace under high frequency.

3. the present invention can calculate the echoed signal of target guided missile accurately according to the RCS of the target guided missile that calculates at semispace under high frequency.

Description of drawings

Fig. 1 is realization flow figure of the present invention.

Specific implementation process

With reference to Fig. 1, performing step of the present invention is as follows:

Step 1 is obtained the target guided missile shape data information of STL text formatting.

In order to calculate the target guided missile in the RCS of semispace, must obtain the shape data of the target guided missile of STL text formatting, its obtaining step is as follows:

1a) utilize software to set up the model synoptic diagram of target guided missile according to target guided missile physical size, this software comprises commercial HFSS software and commercial CST software;

1b) the model synoptic diagram of target guided missile is opened in triangle division software, software begins to carry out automatically triangle division, after software demarcation finishes, obtains the target guided missile synoptic diagram after the triangle division, and this software comprises commercial femap software and commercial Ansys software.

1c) the target guided missile synoptic diagram after the triangle division is exported with the STL text formatting, and from output file, extracted the shape data information of target guided missile, for the target guided missile provides shape data accurately in the calculating of the RCS of semispace;

Step 2 is calculated the target guided missile at the RCS σ of semispace.

In order to calculate target guided missile echoed signal, must at first calculate the target guided missile at the RCS σ of semispace, its calculation procedure is as follows:

2a) the current density, J (r ') of calculating target guided missile

Physical optical method gives simple clear and definite value for the current density, J (r ') on target guided missile surface, and current density is the incident magnetic field H ₀Twice, so the calculating formula of current density, J (r ') as:

In the formula

Be the method vector of target guided missile, H ₀Be incident magnetic field;

2b) the scattered field E of calculating target guided missile _s

In physical optical method, carry out the integration stack by the shape data to STL text formatting target guided missile and calculate, obtain the scattered field E of target guided missile _sAs follows:

In the formula, ω is the incident wave frequency, and k is propagation constant,

Be the unit vector of scattering wave polarised direction,

Be the Green function at semispace:

${\stackrel{\‾}{G}}_A(r,r^{\′})=\left[\begin{array}{ccc}{G}_A^{\mathrm{xx}}& 0& 0\\ 0& G_A^{\mathrm{yy}}& 0\\ G_A^{\mathrm{zx}}& G_A^{\mathrm{zy}}& G_A^{\mathrm{zz}}\end{array}\right]$

In the formula

$G_A^{\mathrm{xx}}=\frac{\mathrm{\μ}}{4\mathrm{\π}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+A_h^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{zx}}=-\frac{\mathrm{\μ}}{8\mathrm{\π}}\frac{\∂}{\∂x}{\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)\left[\frac{k_z}{k_{\mathrm{\ρ}}^2}(C_h^e-A_h^e)e^{-j{k}_{z}z}\right]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{zz}}=\frac{\mathrm{\μ}}{4\mathrm{\π}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+A_v^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{yy}}=G_A^{\mathrm{xx}}$ $G_A^{\mathrm{zy}}=G_A^{\mathrm{zx}};$

Be the scalar potential function:

$G_x^{\mathrm{qe}}=-\frac{j}{8\mathrm{\π\ϵ}}{\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+\frac{k^2{A}_h^e+k_z^2{C}_h^e}{k_{\mathrm{\ρ}}^2}{e}^{j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_y^{\mathrm{qe}}=G_x^{\mathrm{qe}}$

$G_z^{\mathrm{qe}}=\frac{1}{4\mathrm{\π\ϵ}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+C_v^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

Wherein:

$A_h^e=R_{\mathrm{TE}}{e}^{-j{k}_z{z}^{\′}},$ $C_h^e=-R_{\mathrm{TM}}{e}^{-j{k}_z{z}^{\′}},$ $A_v^e=R_{\mathrm{TE}}{e}^{-j{k}_z{z}^{\′}},$ $C_v^e=-R_{\mathrm{TM}}{e}^{-j{k}_z{z}^{\′}}$

In the formula, R _TE, R _TMBe fresnel reflection coefficient, k _x, k _y, k _zFor along the propagation constant on x, y, the z direction,

Be the second class zeroth order Hankel function, ε is specific inductive capacity;

2c) calculate the target guided missile at the RCS σ of semispace

Scattered field E according to the target guided missile _sCalculate the target guided missile at the scattering cross-section σ of semispace:

$\sqrt{\mathrm{\σ}}=\underset{R\→\∞}{\lim }2\sqrt{\mathrm{\π}}R\frac{E_s\·{\hat{e}}_r}{E_o}\exp \left(\mathrm{jkR}\right)$

That is: $\mathrm{\σ}={\left(\underset{R\→\∞}{\lim }2\sqrt{\mathrm{\π}}R\frac{E_s\·{\hat{e}}_r}{E_o}\exp \left(\mathrm{jkR}\right)\right)}^2,$

In the formula, R is the round trip distance from the early warning plane radar to the target Missile Center, E _oBe the incident electric field,

Be the unit vector of target guided missile electric polarization direction, k is propagation constant.

Step 3 is calculated target guided missile echoed signal

Based on radar equation, consider radar system loss, radar operation wavelength, pulse peak power, radar system loss parameter situation, utilize target guided missile that step 2 calculates at the scattering cross-section σ of semispace, calculate radar and receive target guided missile echo signal amplitude

For:

In the formula: P _tBe the radar emission signal peak power, λ is the radar operation wavelength, and σ is that the target guided missile is long-pending in the RCS of semispace, G (α _T, β _T) be the radar antenna voltage gain, L is that radar emission receives composite loss, R is that radar arrives target Missile Center distance.

Calculate target guided missile echoed signal, be the early warning plane radar and receive target guided missile echoed signal, finish early warning plane radar detection target simulation process.

Claims (2)

1. an early warning plane radar detection target simulation method comprises the steps:

(1) obtains the target guided missile shape data information of STL text formatting

1a) utilize HFSS software to set up the model synoptic diagram of target guided missile according to target guided missile physical size;

1b) from the discrete data point at the model synoptic diagram edge of target guided missile, take out 4 wherein adjacent points arbitrarily; Appoint the quadratic sum minimum criteria of the difference on both sides to carry out triangle division according to triangle to these 4, selected wherein 3 and connect;

1c) for remaining discrete data point, repeating step 1b), be joined together the target guided missile synoptic diagram after obtaining handling up to all discrete data points;

1d) the target guided missile synoptic diagram after will handling is with the output of STL text formatting, and extracts the shape data information of target guided missile from output file, for the target guided missile provides shape data accurately in the calculating of the RCS of semispace;

(2) calculate the target guided missile at the RCS σ of semispace

To introduce in the physical optics method at the Green function of semispace, the shape data of STL text formatting target guided missile will be calculated, obtain the target guided missile at the scattering cross-section σ of semispace:

$\sqrt{\mathrm{\σ}}=\underset{R\→\∞}{\lim }2\sqrt{\mathrm{\π}}R\frac{E_s\·{\hat{e}}_r}{E_o}\exp \left(\mathrm{jkR}\right)$

That is: $\mathrm{\σ}={\left(\underset{R\→\∞}{\lim }2\sqrt{\mathrm{\π}}R\frac{E_s\·{\hat{e}}_r}{E_o}\exp \left(\mathrm{jkR}\right)\right)}^2,$

In the formula, R is the round trip distance from the early warning plane radar to the target Missile Center, E _oBe the incident electric field, Be the unit vector of target guided missile electric polarization direction, k is propagation constant, E _sFor target guided missile scattering electric field, under far field condition, arrive the distance of far field observation point much larger than the characteristics of target guided missile size according to the target guided missile, obtain E _sFollowing expression:

$E_s=-\mathrm{j\ω}{\∫\∫\∫}_v{\stackrel{\‾}{G}}_A(r,r^{\′})\·J\left(r^{\′}\right)d{r}^{\′}+\frac{k\·\hat{s}}{\mathrm{\ω}}{\∫\∫\∫}_v[G_x^{\mathrm{qe}}\frac{\∂}{\∂x}J\left(r^{\′}\right)+G_y^{\mathrm{qe}}\frac{\∂}{\∂y}J\left(r^{\′}\right)+G_z^{\mathrm{qe}}\frac{\∂}{\∂z}J\left(r^{\′}\right)]{{\mathrm{dr}}^{\′}}_s$

In the formula, ω is the incident wave frequency, and J (r ') is current density, and k is propagation constant, Be the unit vector of scattering wave polarised direction,

Be the Green function at semispace:

${\stackrel{\‾}{G}}_A(r,r^{\′})=\left[\begin{array}{ccc}{G}_A^{\mathrm{xx}}& 0& 0\\ 0& G_A^{\mathrm{yy}}& 0\\ G_A^{\mathrm{zx}}& G_A^{\mathrm{zy}}& G_A^{\mathrm{zz}}\end{array}\right]$

In the formula

$G_A^{\mathrm{xx}}=\frac{\mathrm{\μ}}{4\mathrm{\π}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+A_h^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{zx}}=-\frac{\mathrm{\μ}}{8\mathrm{\π}}\frac{\∂}{\∂x}{\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)\left[\frac{k_z}{k_{\mathrm{\ρ}}^2}(C_h^e-A_h^e)e^{-j{k}_{z}z}\right]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{zz}}=\frac{\mathrm{\μ}}{4\mathrm{\π}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+A_v^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_A^{\mathrm{yy}}=G_A^{\mathrm{xx}}$ $G_A^{\mathrm{zy}}=G_A^{\mathrm{zx}};$

Be the scalar potential function:

$G_x^{\mathrm{qe}}=-\frac{j}{8\mathrm{\π\ϵ}}{\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+\frac{k^2{A}_h^e+k_z^2{C}_h^e}{k_{\mathrm{\ρ}}^2}{e}^{j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

$G_y^{\mathrm{qe}}=G_x^{\mathrm{qe}}$

$G_z^{\mathrm{qe}}=\frac{1}{4\mathrm{\π\ϵ}}(-\frac{j}{2}){\∫}_{-\∞}^{+\∞}\frac{k_{\mathrm{\ρ}}}{k_z}{H}_0^{\left(2\right)}\left(k_{\mathrm{\ρ}}\mathrm{\ρ}\right)[e^{-j{k}_z|z-z^{\′}|}+C_v^e{e}^{-j{k}_{z}z}]d{k}_{\mathrm{\ρ}}$

Wherein:

$A_h^e=R_{\mathrm{TE}}{e}^{-j{k}_z{z}^{\′}},$ $C_h^e=-R_{\mathrm{TM}}{e}^{-j{k}_z{z}^{\′}},$ $A_v^e=R_{\mathrm{TE}}{e}^{-j{k}_z{z}^{\′}},$ $C_v^e=-R_{\mathrm{TM}}{e}^{-j{k}_z{z}^{\′}}$

In the formula, R _TE, R _TMBe fresnel reflection coefficient, k _x, k _y, k _zFor along the propagation constant on x, y, the z direction,

Be the second class zeroth order Hankel function, ε is specific inductive capacity;

The physical optics of current density, J (r ') is approximate:

$J\left(r^{\′}\right)=2\hat{n}\×H_0$

In the formula, Be the method vector of target guided missile, H ₀The incident wave magnetic field intensity;

(3) calculate target guided missile echoed signal

Based on radar equation, consider radar system loss, radar operation wavelength, pulse peak power, radar system loss parameter situation, utilize the target guided missile at the scattering cross-section σ of semispace, calculate radar and receive target guided missile echo signal amplitude

For:

In the formula: P _tBe the radar emission signal peak power, λ is the radar operation wavelength, and σ is that the target guided missile is long-pending in the RCS of semispace, G (α _T, β _T) be the radar antenna voltage gain, L is that radar emission receives composite loss, R is that radar arrives target Missile Center distance.

2. early warning plane radar detection target simulation method according to claim 1, it is characterized in that: appointing the quadratic sum minimum criteria of the difference on both sides to carry out triangle division according to triangle to adjacent 4 described step 1b), is to utilize commercial femap software to carry out triangle division.

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