CN116930895A - Non-contour ground bias source bias-inducing efficiency simulation and evaluation method - Google Patents

Non-contour ground bias source bias-inducing efficiency simulation and evaluation method Download PDF

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CN116930895A
CN116930895A CN202311190865.4A CN202311190865A CN116930895A CN 116930895 A CN116930895 A CN 116930895A CN 202311190865 A CN202311190865 A CN 202311190865A CN 116930895 A CN116930895 A CN 116930895A
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source
bias
inducing
target
main source
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CN116930895B (en
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邹雄
耿方志
王冰切
罗威
钱欢
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Air Force Early Warning Academy
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Air Force Early Warning Academy
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/40—Means for monitoring or calibrating
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/38—Jamming means, e.g. producing false echoes
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/08—Probabilistic or stochastic CAD

Abstract

The invention discloses a simulation and evaluation method for the bias-inducing efficiency of a non-contour ground bias-inducing source, which comprises the following steps: setting a simulation coordinate system, and constructing a ground surface model according to the position relation of the main source and the induced polarization source; constructing a key working model of a ground induced polarization source, a main source and a passive radar guided aerial target; establishing dynamic judgment conditions, updating the air target position in real time in simulation, and performing vision judgment and main source interception judgment; and carrying out Monte Carlo simulation by using a simulation model, judging the hit probability of the main source and the induced polarization source according to the drop point distribution condition of the aerial target, and further realizing induced polarization efficiency evaluation. The invention provides a ground bias-inducing source bias-inducing efficiency simulation method under non-equal-altitude conditions for the first time, which can quickly construct a ground surface model, can realize signal vision and main source signal interception and discrimination, is closer to real attack conditions, can examine bias-inducing efficiency under different conditions through parameter adjustment, and further guides reasonable arrangement of bias-inducing sources.

Description

Non-contour ground bias source bias-inducing efficiency simulation and evaluation method
Technical Field
The invention belongs to the field of electronic countermeasure simulation and evaluation, and in particular relates to a simulation and evaluation method for the bias-inducing efficiency of a non-equal-altitude ground bias-inducing source.
Background
The air target guided by the passive radar can find, track and destroy the radar by utilizing electromagnetic waves radiated by the ground radar, and the air target can form a great threat to a radar system. The current economic and effective method for resisting the targets mainly adopts an active polarization-inducing technology, an active polarization-inducing source is additionally arranged beside a large backbone radar, and under the condition that the space opening angle of the polarization-inducing source and the radar is small, the passive radar guidance targets are difficult to distinguish and track one radiation source.
Related patents of the radar bias-inducing system include a radar bias-inducing source simulation system (application number CN 202010070268.8), a UHF frequency band radar bias-inducing system (application number CN 201822200448.4) and the like, wherein the bias-inducing system mainly comprises a signal waveform generating unit, an optical transmission unit, bias-inducing devices and a monitoring part, and the number of bias-inducing sources is generally 3. The above patent mainly designs hardware and a control system of a bias-inducing source, and does not relate to a bias-inducing efficiency simulation and evaluation method. If the real-world countermeasure mode is adopted to evaluate the induced polarization efficiency of the induced polarization source, huge time and labor cost are brought, so that the evaluation by adopting the simulation modeling method becomes an efficient solution.
The patent of the induced polarization source induced polarization efficiency simulation has few reports, and related documents include ' radar anti-radiation attack induced polarization source station arrangement using combat simulation (firepower and command control, 2018, 43 (11): 151-155) ', anti-radiation missile radar induced polarization source configuration and combat efficiency analysis (release university report (natural science edition), 2007, 8 (3): 270-273) ', and the like, wherein the above documents mainly consider the induced polarization efficiency of the induced polarization source under the same-height condition, do not consider the terrain shielding problem under the non-same-height condition, and the radar main lobe interception factor is not considered, so the practical application range is limited.
Disclosure of Invention
Aiming at the defects or improvement demands of the prior art, the invention provides a simulation and evaluation method for the bias-inducing efficiency of a non-equal-altitude ground bias-inducing source, which aims to accurately estimate the probability of striking the bias-inducing source and a protection object thereof under the condition that the non-equal-altitude ground bias-inducing source is attacked by different targets, thereby solving the problem of optimizing and arranging the bias-inducing source.
In order to achieve the above purpose, the invention provides a non-contour ground bias source bias-inducing efficacy simulation model, which comprises 3 types of simulation objects: firstly, a main source in a bias system, namely a protected object, usually a ground radar, hereinafter referred to as a main source; secondly, the induced polarization sources, and a set of induced polarization system usually comprises 3 induced polarization sources; thirdly, an aerial target guided by the passive radar can be a reverse-radiation missile or a reverse-radiation unmanned aerial vehicle, and is hereinafter referred to as an aerial target. The signal radiated by the induced polarization source is led out from the main source, the pulse front edge leads the main source signal, and the pulse rear edge lags the main source signal, namely the induced polarization signal wraps the main source signal. The polarization inducing sources adopt a flickering working mode, namely the pulse fronts of the 3 polarization inducing sources are alternately advanced. On the array of the bias-inducing sources, 3 bias-inducing sources are not on a straight line, and form an approximate diamond with the main source, and the height of the bias-inducing sources is usually lower than or can be higher than that of the main source. The main source antenna adopts a circumferential scanning or side scanning and side tracking mode, the gain of the main source antenna in a certain direction is time-varying, the bias-inducing source antenna does not scan, and the azimuth is similar to that of an omni-directional antenna.
In one embodiment of the present invention, the simulation model construction mainly comprises the following steps:
(1) Setting up a simulation coordinate system and constructing a simplified earth surface model. An initial position of the 3-class simulation object is set, wherein the main source is usually positioned on the mountain top or the high land, the altitude of the induced polarization source is lower than that of the main source, and the altitude of the aerial object is Yu Zhu source. And constructing a near-conical earth surface model according to the coordinates and the position relation of the main source and the induced polarization source.
(2) And constructing key working models of a ground bias source and a main source, wherein the key working models comprise a bias source time sequence working model and a main source antenna scanning characteristic model.
(3) And constructing a working model of the aerial target, wherein the working model comprises a seeker direction-finding model and a maneuverability model, and acquiring a seeker direction-finding result and the position of the aerial target in real time.
(4) And establishing dynamic judgment conditions, wherein in the flight process of the air target, dynamic judgment is carried out according to the real-time position of the air target, including a visual judgment, a main source interception judgment and the like.
(5) And (3) performing strike probability estimation, setting initial positions and performance parameters of 3 types of simulation objects, allowing corresponding parameters to change within a preset range, performing Monte Carlo simulation, and judging the strike probability of the main source and the induced polarization source according to the drop point distribution condition of the aerial target.
In one embodiment of the invention, the ground surface model is constructed according to the positions of the induced polarization source and the main source, and the ground surface is divided into a near zone, a middle zone and a far zone; the near zone is constructed by a cone which takes a main source as a vertex and takes the connecting line of the main source and the nearest induced polarization source as a bus; the middle region is constructed by a conical ring with the vertical direction of the main source as an axis and the connecting line of the farthest bait and the nearest point of the edge of the near region as a bus; the distal zone is the portion of the horizontal surface at which the furthest bait is located, excluding the proximal and middle zones. The main source and the 3 bias-inducing sources are respectively positioned at A, B, C, D points, the heights are respectively、/>、/>、/>The horizontal projection distances from the 3 polarization-inducing sources to the main source are respectively +.>、/>、/>Square relative to main sourceThe azimuth angles are respectively->、/>、/>. Taking the projection of the main source at sea level as an origin and the direction of the right east asxThe axis and the north direction areyEstablishing a ground rectangular coordinate system with the axis and the vertical upward direction as the z axiso-xyzThen the main source coordinate is AThe polar coordinates of the 3 bias sources can be expressed as B +.>、C/>、D/>Rectangular coordinates can be expressed as B +.>、C/>、D。
The near zone is formed by a cone with A as the vertex and AB connection line as the bus, and the elevation angle of the conical surfaceβ B I.e. the ground gradient. And the O point is the projection of the A point on the horizontal plane where the B point is located, and the near-zone ground gradient is represented by the following formula:
or->(1)
The middle region is formed by a conical ring with AO as an axis and B ' -C connecting line as a bus, when seen from a top view, B ' -point is positioned on the connecting line of AC and is the same as B point, and the distance from B ' -point to A point is the same as that from B point to A point, and then the ground gradient of the middle region is represented by the following formula:
or->(2)
The far zone is the part of the horizontal plane where the point C is located except the near zone and the middle zone, and the gradient is 0.
The mathematical expression of the surface model of the earth is:
(3)
in one embodiment of the invention, a matrix for a time sequence working model of a bias source is usedSExpression, setting the flicker period of the induced polarization source asT S The timing matrix is expressed as:
(4)
in the formula, the firstiThe row represents the firstiThe time sequence of the induced polarization source, the firstjThe columns represent the timing of the 3 bias-inducing sources within a certain scintillation period.The larger the value, the more advanced the leading edge of the pulse of the bias source signal. If at firstiIf the bias source is destroyed。
Set the firstjPersonal (S)T s Inner firstiThe pulse front distinguishing parameters of the induced polarization sources are as followsk i,j If the pulse leading edge is most advanced, the value is set to 1, otherwise, the value is set to 0, and the following are:
(5)
in one embodiment of the invention, the antenna scanning modes are divided into two modes according to different main source types, one mode is circumferential scanning, and the main lobe width of the main source antenna is set asThe circumference scanning period isT a The main lobe dwell time in a certain orientation is then:
(6)
let the main lobe gain of the antenna beG t Average sidelobe gain ofG s Real-time antenna gain at simulationThe value of (2) can be obtained by the following formula:
(7)
in the formula ,nis a positive integer.
The other is scanning while tracking, and the main source tracking data rate is set asr d Beam dwell time ist a The antenna gain can be expressed as:
(8)
in one embodiment of the invention, the seeker direction-finding model of the aerial target employs phase interferometer direction-finding techniques.
The seeker antenna array at least comprises 2 antennas on an azimuth plane and a depression plane, the two antennas on the azimuth plane are respectively a first antenna and a second antenna, the connection line between the two antennas is called a base line, and the space isCalled the base line length, the angle between the signal direction and the base line +.>The angle of arrival of the signal, called azimuth, is the difference of the wave path of the signal arriving at the two antennas of the seeker:
(9)
the phase difference of the signals received by the first antenna and the second antennaThe method comprises the following steps:
(10)
in the formula Is the operating wavelength of the radiation source.
Detecting the distance between the first antenna according to 3 bias-inducing sources and the distance between the main source antenna and the guide head，/>The subscript 4 indicates the main source, and the delay phase of each radiation source signal to the first antenna can be obtained:
(11)
for the first antenna, the firstjPersonal (S)T s Real part of composite signal of internal bias source and main sourceAnd imaginary part->The method comprises the following steps:
(12)
k i the air target tracking discrimination parameters are determined by the formulas (22) and (19).
Similarly, the real part of the second antenna detection synthesized signal can be obtainedA 2 And imaginary partB 2 The two antennas receive the phase difference of the synthesized signalCan be expressed as the argument after 2 complex conjugate multiplications, i.e
(13)
Obtaining the direction finding result of the azimuth plane, namely the signal arrival angle of the azimuth plane according to the formula (9). Similarly, the direction finding result of the plane can also be obtained by constructing an antenna array on the lower face>。
In one embodiment of the invention, the mobility model of the airborne target is built based on the speed and overload of the target. Discretizing the time of flight of an airborne target, as is knownPosition of the object in air at the moment->Speed sizeSpeed direction->The method comprises the steps of carrying out a first treatment on the surface of the Solving->Time position->Speed size->Speed direction->By analogy, a myriad of times +.>To obtain the diving track point corresponding to the target in the space>Equal to the time interval during which the pilot sends the control command.
Is provided withThe position of the aerial target at the moment is +.>At this time, the actual measurement direction of the seeker is +.>While the direction of the flight speed of the target is +.>Approximately considered as the last moment (>) The leader measures the angular direction. Elapsed time->Target arrival->, wherein />And->The included angle between them is->I.e. the->The included angle between the initial speed direction and the measured direction in time; />And->The included angle between them is->I.e. the->And the included angle between the initial speed direction and the two-point connecting line direction in time.
Is provided withAcceleration of gravity, ++>For the number of motorized overloads of the aerial target, +.>For maximum number of overload, the theory of kinetics is combined, in +.>In time, the maximum angle through which an aerial target can rotate is as follows:
(14)
if it isIndicating that the aerial target can be modified by maneuver with the actual overload +.>Completely correct tracking errors at this timeIs +.>The method comprises the steps of carrying out a first treatment on the surface of the If->The aerial target will be overloaded with maximum +.>Turning to the actual measurement direction, the number of overload used at this time +.>。
At this time, the turning radius of the aerial target is:
(15)
at the position ofIn time, the angle of turning of the aerial target is as follows:
(16)
in one embodiment of the invention, the visibility decision is based on the position of the aerial target and on the ground surface model, and the decision is based on the shielding problem of the induced polarization source signal.
The BO connecting line is taken as a reference direction, the azimuth of an aerial target relative to a bias inducing source is taken as alpha, and the elevation angle is taken asβ 1 . The tangential plane ABF of the B point relative to the cone is formed, wherein the F point is positioned on the vertical plane in the alpha direction and is the same as the A point, and the plane OAFE T plane OAB is not difficult to obtain
(17)
Because the coordinates of the main source and the induced polarization source are known, and the real-time coordinates of the aerial target can be obtained from the initial position and the motion condition, the elevation angle of the aerial target relative to the induced polarization source can be obtained in real timeβ i And the approximation of the mountain gradient in that directionβ i '. When (when)β i β i In the' case, the aerial target is in communication with the bias source, otherwise, the aerial target is not in communication.
Similarly, the result of the judgment of the air target and other induced polarization sources can be obtained.
Setting the tracking discrimination parameters of the aerial targetk i ，i=1, 2,3,4, subscript 4 denotes the main source, its initial value is determined by the pulse leading edge discrimination parameter, and if at a certain moment in the air target motion simulation processiIf the three polarization sources are not in communication with the aerial target, the judgment parameter of the polarization source is 0, and if the three polarization sources are not in communication with the aerial target, only the main source is in communication. Then the firstjIn the course of a blinking period,k i the values of (2) are:
(18)
(19)
in one embodiment of the invention, the main source interception decision is obtained by real-time calculation according to the scanning state of the main source antenna and the distance from the radiation source to the aerial target. When the main source, the bias inducing source and the aerial target can be seen, the pilot head of the aerial target detects the main source signal receivedAnd power of the bias source signal +.>The method comprises the following steps of:
(20)
(21)
wherein , and />Representing the main source and the firstiThe distance between each induced polarization source and the aerial target is calculated in real time according to coordinates, and the distance between each induced polarization source and the aerial target is calculated in real time> and />Representing the equivalent radiated power of the two, i.e. the product of the transmitted power and the antenna gain, +.>The antenna gain is received for the seeker.
According to the main source antenna scanning characteristic model, the power of the main source and the induced polarization source signals detected by the seeker can be calculated, if the ratio of the power to the induced polarization source signals exceeds the instantaneous dynamic range of the seekerD r And if not, tracking the pilot head by the main source, otherwise, tracking the induced polarization source. Accordingly, the tracking discrimination parameters are further modified:
(22)
in one embodiment of the invention, monte Carlo simulation is used to determine the probability that the primary source and the bias source are hit. In each attack process of the air target, the landing judgment of the air target is carried out, a height judgment method is adopted, namely when the position of the air target is lower than the ground surface according to the ground surface model, the landing of the air target is judged, the attack process is terminated, and the time and the last time are recordedBefore) the position of the aerial target-> and />Then the target landing position is the average of the two, namely
(23)
When the distance between the landing point of the target in the air and a certain radiation source is smaller than the killing radius of the target warhead in the air, the target is identified to be hit, and a hit result is recorded.
And simulating in the set parameter variation range until all parameter values are simulated, recording the times of striking each radiation source, and dividing the times by all simulation times to obtain the striking probability of the radiation source.
In general, compared with the prior art, the above technical solution conceived by the present invention has the following beneficial effects:
(1) The invention provides a ground bias-inducing source bias-inducing efficiency simulation method under non-equal-altitude conditions for the first time, which can directly utilize the positions of a main source and a bias-inducing source to construct a ground surface model and provide support for simulating attack of an aerial target;
(2) The simulation method provided by the invention can judge whether the induced polarization source signal is blocked or not in real time, and judge whether the main source signal is intercepted or not in real time, so that the simulation method is closer to the real attack condition;
(3) The evaluation method provided by the invention can be used for examining the hit probability of the bias-inducing system under different conditions through parameter adjustment, so as to guide the reasonable arrangement of the bias-inducing sources.
Drawings
FIG. 1 is a schematic diagram of a bias-inducing system and an aerial target position relationship and a model of the surface of the earth in an embodiment of the present invention;
FIG. 2 is a schematic top view of a model of the surface of the earth in an embodiment of the invention;
FIG. 3 is a schematic diagram of a phase interferometer direction finding technique employed by a hollow target in an embodiment of the present invention;
FIG. 4 is a schematic diagram of a model of the target mobility in the hollow of an embodiment of the present invention;
FIG. 5 is a schematic diagram showing the discrimination of hollow targets and bias-inducing sources according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
According to the invention, an active bias-inducing and passive radar guidance target attack theory is utilized to establish a bias-inducing source working efficiency simulation model, simulation conditions such as a visual judgment and a signal intensity judgment are introduced in focus, a Monte Carlo simulation method is utilized to generate the distribution condition of falling points of the passive radar guidance target, the bias-inducing source and the damage probability of a protected object, and further the bias-inducing efficiency of the bias-inducing source under the non-equal-altitude condition is evaluated, so that guidance comments are provided for the optimal deployment of the bias-inducing source.
The invention includes 3 kinds of simulation objects: firstly, a main source in a bias system, namely a protected object, usually a ground radar, hereinafter referred to as a main source; secondly, the induced polarization sources, and a set of induced polarization system usually comprises 3 induced polarization sources; thirdly, an aerial target guided by the passive radar can be a reverse-radiation missile or a reverse-radiation unmanned aerial vehicle, and is hereinafter referred to as an aerial target.
In the invention, the signal radiated by the induced polarization source is led out from the main source, the front edge of the pulse leads the main source signal, and the rear edge of the pulse lags the main source signal, namely the induced polarization signal wraps the main source signal. The polarization inducing sources adopt a flickering working mode, namely the pulse fronts of the 3 polarization inducing sources are alternately advanced. On the array of the bias-inducing sources, 3 bias-inducing sources are not on a straight line, and form an approximate diamond with the main source, and the height of the bias-inducing sources is usually lower than or can be higher than that of the main source. The main source antenna adopts a circumferential scanning or side scanning and side tracking mode, the gain of the main source antenna in a certain direction is time-varying, the bias-inducing source antenna does not scan, and the azimuth is similar to that of an omni-directional antenna.
Air meshThe target measures the direction of the ground radiation source by using a phase interferometer direction-finding technology and performs direction tracking, performs uniform acceleration motion in a dive attack stage, and sets the gravity acceleration asThe maximum maneuvering overload number of the aerial target is +.>Initial speed is +.>Acceleration isaThe pilot head points to the main source direction initially, and when a certain bias source signal enters the pilot head first, the pilot head points to the bias source. Every interval +.>And second, the seeker sends the direction finding result to the flight control system once, and adjusts the attitude of the aerial target, so that the seeker flies along the direction of the direction finding result.
The direction finding result of the aerial target leader is given with reference to the leader coordinate system, which origin isTo center the reference antenna in the seeker antenna array,Zthe direction is the direction of the movement of the object,Xthe direction is the direction of the direction surface of the seekerZThe direction of the vertical axis is positive to the right,Yin the direction of the nodding surface of the seekerZThe direction of the vertical axis is positive downwards.
The simulation and evaluation of the non-contour ground bias source bias-inducing efficiency comprise the following steps:
(1) Setting the above-mentioned geodetic coordinate system and guide head coordinate system, and according to the coordinate and position relationship of main source and induced deflection source, constructing the geodetic surface model of approximate cone.
Assuming that the positions of the main source and the 3 bias-inducing sources are respectively at four points A, B, C, D in FIG. 1, the heights are respectively、、/>、/>The horizontal projection distances from the 3 polarization-inducing sources to the main source are respectively +.>、/>、/>Azimuth angles relative to the main source are +.>、/>、/>. Taking the projection of the main source at sea level as an origin and the direction of the right east asxThe axis and the north direction areyThe vertical upward direction of the axis is z axis to establish a ground rectangular coordinate system, and the main source coordinate is A ∈ ->The polar coordinates of the bias source can be expressed as B +.>、C/>、D/>Rectangular coordinates can be expressed as B +.>、C、D/>The above parameters are used as the basis for constructing the surface model of the earth.
Because the main source is highest in height and is positioned at the point A, the induced polarization source closest to the main source is positioned at the point B, and the induced polarization source farthest is positioned at the point C, the surface of the earth can be divided into a near zone, a middle zone and a far zone. From the top view of fig. 2, each zone is centered on point a, the near zone is a circular zone with a radius no greater than the distance from point B, the middle zone is a zone with a radius from point B to the distance from point C, and the far zone is a zone with a radius exceeding the distance from point C, as shown in fig. 1.
The near zone is formed by a cone with A as the vertex and AB connection line as the bus, and the elevation angle of the conical surfaceβ B I.e. the ground gradient. As shown in fig. 1, the O point is the projection of the a point on the horizontal plane where the B point is located, and then the near-zone ground gradient is represented by the following formula:
or->(1)
The middle region is formed by a conical ring with AO as an axis and B ' -C connecting line as a bus, when seen from a top view, B ' -point is positioned on the connecting line of AC and is the same as B point, and the distance from B ' -point to A point is the same as that from B point to A point, and then the ground gradient of the middle region is represented by the following formula:
or->(2)
The far zone is the part of the horizontal plane where the point C is located except the near zone and the middle zone, and the gradient is 0.
The mathematical expression of the surface model of the earth is:
(3)
in the model of the earth surface, the horizontal projection distance of the initial position G point of the aerial target relative to the main source isThe azimuth is +.>The initial height is +.>Then G point coordinates->Can be expressed as:
(4)
the distances between the G point and the A, B, C, D point are respectively as follows:
(5)
(2) And constructing key working models of a ground bias source and a main source, wherein the key working models comprise a bias source time sequence working model and a main source antenna scanning characteristic model.
Matrix for bias source time sequence working modelSExpression, setting the flicker period of the induced polarization source asT S The timing matrix is expressed as:
(6)
in the formula, the firstiThe row represents the firstiThe time sequence of the induced polarization source, the firstjThe columns represent the timing of the 3 bias-inducing sources within a certain scintillation period.The larger the value, the more advanced the leading edge of the pulse of the bias source signal. If at firstiThe individual bias-inducing sources have been destroyed,then。
Set the firstjPersonal (S)T s Inner firstiThe pulse front distinguishing parameters of the induced polarization sources are as followsk i,j If the pulse front is most advanced, the value is 1, otherwise, the value is 0, and then
(7)
According to different main source types, the antenna scanning modes are divided into two types, one type is circumferential scanning, and the main lobe width of the main source antenna is set asThe circumference scanning period isT a The main lobe dwell time in a certain orientation is then:
(8)
let the main lobe gain of the antenna beG t Average sidelobe gain ofG s Real-time antenna gain at simulationThe value of (2) can be obtained by the following formula:
(9)
in the formula ,nis a positive integer.
The other is scanning while tracking, and the main source tracking data rate is set asr d Beam dwell time ist a The antenna gain can be expressed as:
(10)
(3) And constructing a working model of the passive radar guided aerial target, wherein the working model comprises a seeker direction-finding model and a maneuverability model, and acquiring a seeker direction-finding result and the position of the aerial target in real time.
The seeker direction-finding model of the aerial target adopts a phase interferometer direction-finding technology, and the basic principle diagram is shown in figure 3.
The seeker antenna array at least comprises 2 antennas on an azimuth plane and a depression plane, the two antennas on the azimuth plane are respectively a first antenna and a second antenna, the connection line between the two antennas is called a base line, and the space isCalled the base line length, the angle between the signal direction and the base line +.>The angle of arrival of the signal, called azimuth, is the difference of the wave path of the signal arriving at the two antennas of the azimuth of the seeker is:
(11)
the phase difference of the signals received by the first antenna and the second antennaThe method comprises the following steps:
(12)
in the formula Is the operating wavelength of the radiation source.
Detecting the distance between the first antenna according to 3 bias-inducing sources and the distance between the main source antenna and the guide head，/>The subscript 4 indicates the main source, and the delay phase of each radiation source signal to the first antenna can be obtained:
(13)
for the first antenna, the firstjPersonal (S)T s Real part of composite signal of internal bias source and main sourceAnd imaginary part->The method comprises the following steps: />
(14)
k i The determination parameters for tracking the aerial target are determined by the formulas (25) and (22).
Similarly, the real part of the second antenna detection synthesized signal can be obtainedA 2 And imaginary partB 2 The two antennas receive the phase difference of the synthesized signalCan be expressed as the argument after 2 complex conjugate multiplications, i.e
(15)
Obtaining the direction finding result of the azimuth plane, namely the signal arrival angle of the azimuth plane according to the formula (9). Similarly, the direction finding result of the plane can also be obtained by constructing an antenna array on the lower face>。
In one embodiment of the invention, the mobility model of the airborne target is built based on the speed and overload of the target. Discretizing the time of flight of an airborne target, as is knownTime of day air meshTarget position->Speed sizeSpeed direction->The method comprises the steps of carrying out a first treatment on the surface of the Solving->Time position->Speed size->Speed direction->By analogy, a myriad of times +.>To obtain the diving track point corresponding to the target in the space, as shown in figure 4 +.>Equal to the time interval during which the pilot sends the control command.
Is provided withThe position of the aerial target at the moment is +.>At this time, the actual measurement direction of the seeker is +.>While the direction of the flight speed of the target is +.>Approximately considered as the last moment (>) The leader measures the angular direction. Elapsed time->Target arrival->, wherein />And->The included angle between them is->I.e. the->The included angle between the initial speed direction and the measured signal direction in time; />And->The included angle between them is->I.e. the->And the included angle between the initial speed direction and the two-point connecting line direction in time.
Theory of binding kinetics, inIn time, the maximum angle through which an aerial target can rotate is as follows:
(16)
if it isIndicating that the aerial target can be modified by maneuver with the actual overload +.>The tracking error is completely corrected, the number of overloads used at this time +.>The method comprises the steps of carrying out a first treatment on the surface of the If->The aerial target will be overloaded with maximum +.>Turning to the actual measurement direction, the number of overload used at this time +.>。
From aerodynamic theory, the turning radius of the aerial target is:
(17)/>
as can be seen from FIG. 4, there are, within a small angular rangeThen
(18)
Vector quantityIs +.>。
In the aerial target seeker coordinate system, the direction。
According to the coordinate transformation, the ground coordinate is obtainedIs tied to the direction of movement of the hollow target。
To sum up, byThe vector +.>Is +.>And direction->Therefore, at +.>The point of the moment of time of the aerial target->The coordinates of (2) are:
(19)
and so on, obtaining different moments in the flight processTrack points +.>。
(4) And establishing dynamic judgment conditions, wherein in the flight process of the air target, dynamic judgment is carried out according to the real-time position of the air target, including a visual judgment, a main source interception judgment and the like.
The vision judgment is carried out in real time according to the position of an aerial target and according to a ground surface model, and the judgment is carried out by considering the shielding problem of a bias-inducing source signal.
In FIG. 5, the BO line is taken as the reference direction, the azimuth of the aerial target relative to the bias source is alpha, and the elevation angle isβ 1 . The tangential plane ABF of the B point relative to the cone is formed, wherein the F point is positioned on the vertical plane in the alpha direction and is the same as the A point, and the plane OAFE T plane OAB is not difficult to obtain
(20)
Because the coordinates of the main source and the induced polarization source are known, and the real-time coordinates of the aerial target can be obtained from the initial position and the motion condition, the elevation angle of the aerial target relative to the induced polarization source can be obtained in real timeβ i And the approximation of the mountain gradient in that directionβ i '. When (when)When the device is used, the aerial target and the induced polarization source are in a common view, otherwise, the aerial target and the induced polarization source are not in a common view.
Similarly, the result of the judgment of the air target and other induced polarization sources can be obtained.
Setting the tracking discrimination parameters of the aerial targetk i ，i=1, 2,3,4, subscript 4 denotes the main source, its initial value is determined by the pulse leading edge discrimination parameter, and if at a certain moment in the air target motion simulation processiIf the three polarization sources are not in communication with the aerial target, the judgment parameter of the polarization source is 0, and if the three polarization sources are not in communication with the aerial target, only the main source is in communication. Then the firstjIn the course of a blinking period,k i the values of (2) are:
(21)/>
(22)
the main source interception judgment is obtained by carrying out real-time calculation according to the scanning state of the main source antenna and the distance from the radiation source to the aerial target. When the main source, the bias inducing source and the aerial target can be seen, the pilot head of the aerial target detects the main source signal receivedAnd power of the bias source signal +.>The method comprises the following steps of:
(23)
(24)
wherein , and />Representing the main source and the firstiThe distance between each induced polarization source and the aerial target is calculated in real time according to coordinates, and the distance between each induced polarization source and the aerial target is calculated in real time> and />Representing the equivalent radiated power of the two, i.e. the product of the transmitted power and the antenna gain, +.>The antenna gain is received for the seeker.
According to the main source antenna scanning characteristic model, the power of the main source and the induced polarization source signals detected by the seeker can be calculated, if the ratio of the power to the induced polarization source signals exceeds the instantaneous dynamic range of the seekerD r And if not, tracking the pilot head by the main source, otherwise, tracking the induced polarization source. Accordingly, the tracking discrimination parameter of the formula (21) is further corrected:
(25)
(5) And (3) performing strike probability estimation, setting initial positions and performance parameters of simulation objects, allowing corresponding parameters to change within a preset range, performing Monte Carlo simulation, and judging the strike probability of the main source and the induced polarization source according to the drop point distribution condition of the aerial target.
The parameter variation in Monte Carlo simulation includes the initial distance of the horizontal plane from the aerial target to the main sourceAnd initial orientation->. Total number of simulations +.>By the number of changes in the initial distance->And the number of changes in the initial orientation +.>Determination, i.e.
(26)
For example, if the initial distance is varied from 3000 m to 5000 m, with an interval of 200 mThe initial azimuth change range is 0-90 degrees, the interval is 10 degrees, and the initial azimuth change range is +.>Total number of simulations->。
In the simulation of each attack process of the air target, the landing judgment of the air target is carried out, a height judgment method is adopted, namely, when the position of the air target is lower than the ground surface according to the ground surface model, the landing of the air target is judged, the attack process is terminated, and the time and the last time are recordedBefore) the position of the aerial target-> and />The target landing position is the average of the two, i.e +.>
(27)
When the distance between the landing point of the target in the air and a certain radiation source is smaller than the killing radius of the target warhead in the air, the target is identified to be hit, and a hit result is recorded.
Simulating in the set parameter variation range until all the parameter values are simulated, and recording the hit times of each radiation sourceDividing by all simulation times to obtain the hit probability of the radiation source>。
(28)
According to the probability of the radiation source being hit, the induced polarization efficiency of the 3 induced polarization sources is estimated, the positions of the 3 induced polarization sources can be adjusted according to the result, and the purpose of optimizing the arrangement positions of the induced polarization sources is achieved.
It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.

Claims (10)

1. A simulation and evaluation method for the bias-inducing efficiency of a non-contour ground bias-inducing source is characterized by comprising the following steps:
(1) Setting a simulation coordinate system, and constructing a near-cone earth surface model according to the coordinates and the position relation of the main source and the induced polarization source;
(2) Constructing key working models of a ground bias source and a main source, wherein the key working models comprise a bias source time sequence working model and a main source antenna scanning characteristic model;
(3) Constructing a working model of an aerial target, wherein the working model comprises a seeker direction-finding model and a maneuverability model, and acquiring a seeker direction-finding result and the position of the aerial target in real time;
(4) Establishing dynamic judgment conditions, wherein in the flight process of an air target, dynamic judgment is carried out according to the real-time position of the air target, including a viewing judgment and a main source interception judgment;
(5) And (3) performing strike probability estimation, setting initial positions and performance parameters of simulation objects, allowing corresponding parameters to change within a preset range, performing Monte Carlo simulation, and judging the strike probability of the main source and the induced polarization source according to the drop point distribution condition of the aerial target.
2. The method for simulating and evaluating the bias-inducing efficacy of a non-contour ground bias source according to claim 1, wherein the model of the surface of the earth is determined by the positions of the main source and the bias-inducing source, and the surface of the earth is divided into a near zone, a middle zone and a far zone; the near zone is constructed by a cone which takes a main source as a vertex and takes the connecting line of the main source and the nearest induced polarization source as a bus; the middle region is constructed by a conical ring with the vertical direction of the main source as an axis and the connecting line of the farthest bait and the nearest point of the edge of the near region as a bus; the far zone is the part of the horizontal plane where the furthest bait is located, excluding the near zone and the middle zone; the heights of the main source and the 3 bias-inducing sources are respectively、/>、/>、/>The horizontal projection distances from the 3 polarization-inducing sources to the main source are respectively +.>、/>、/>Azimuth angles relative to the main source are +.>、/>、/>By projection of the sea level of the main sourceoThe point is used as the origin of coordinates to construct a rectangular coordinate systemo-xyz，xThe axis is in the forward direction of the east,ythe axis is in the north direction of the right,zthe axis is in a vertically upward direction, and the mathematical expression of the earth surface model is:
(1)。
3. the method for simulating and evaluating the bias-inducing efficiency of a non-contour ground bias-inducing source as claimed in claim 1, wherein the bias-inducing source is operated by blinking, the front of the radiated signal pulse is alternately advanced in the first phasejEach flicker periodT s In, the firstiThe pulse front distinguishing parameters of the induced polarization sources are as followsk i,j ，i=1, 2,3, when the pulse front is most advancedk i,j Assigning a value of 1, otherwise, 0; the main source antenna is in scanning state, the scanning mode is circumference scanning or scanning-while-tracking, the gain of the main source antenna in a certain direction is time-varying。
4. The method for simulating and evaluating the bias-inducing efficiency of the non-contour ground bias-inducing source according to claim 1, wherein a pilot head direction-finding model of the aerial target adopts a phase interferometer direction-finding technology, and a signal direction measurement result is obtained in real time in the flight process of the aerial target; the antenna array of the seeker of the aerial target at least comprises 2 antennas on an azimuth plane and a depression plane, the two antennas of the azimuth plane are respectively a first antenna and a second antenna, the connecting line between the two antennas is called a base line, and the space isCalled the base line length, the angle between the signal direction and the base line +.>The angle of arrival of the signal, called azimuth plane, the phase difference of the signals received by the first antenna and the second antenna +.>The method comprises the following steps:
(2)
in the formula Is the operating wavelength of the radiation source;
according to the distance between 3 bias-inducing sources and the main source antenna and the first antenna，i=1, 2,3,4, obtain the delay phase of each radiation source signal arriving at the first antenna:
(3)
for the first antenna, the polarization-inducing source and the main source synthesize a real signalA part (C)And imaginary part->The method comprises the following steps:
(4)
wherein ,k i tracking discrimination parameters for an aerial target; similarly, the real part of the second antenna detection synthesized signal can be obtainedA 2 And imaginary partB 2 The two antennas receive the phase difference of the synthesized signalCan be expressed as the argument after 2 complex conjugate multiplications, i.e
(5)
Obtaining the direction finding result of the azimuth plane, namely the signal arrival angle of the azimuth plane according to the formula (2)The method comprises the steps of carrying out a first treatment on the surface of the And similarly, obtaining a nodding-up direction finding result.
5. The method for simulating and evaluating the bias-inducing efficiency of the non-contour ground bias-inducing source according to any one of claims 1 to 4, wherein the mobility model of the aerial target considers the speed, overload and signal direction measurement results of the target and can update the position of the aerial target in real time; is provided withgThe acceleration of the gravity is that,for the maximum maneuver overload number of the aerial target, the maximum maneuver overload of the aerial target is +.>The overload number of the air target at a certain moment is +.>The movement speed is +.>In the seeker coordinate system, the included angle between the seeker direction and the antenna array normal line direction is +.>At discrete time intervals +.>In the interior, the maximum angle that the aerial target can turn +.>The method comprises the following steps:
(6)
if it isIndicating that the aerial target can be modified by maneuver with the actual overload +.>The tracking error is completely corrected, the number of overloads used at this time +.>The method comprises the steps of carrying out a first treatment on the surface of the If->The aerial target will be overloaded with maximum +.>Turning to the actual measurement direction, the number of overload used at this time +.>；
Turning radius of aerial targetThe method comprises the following steps:
(7)
at the position ofIn time, the angle of turning of the aerial target +.>The method comprises the following steps:
(8)。
6. the method for simulating and evaluating the bias-inducing efficiency of the non-contour ground bias-inducing source according to any one of claims 1 to 4, wherein the vision decision and the main source interception decision are performed according to the real-time position of the aerial target in the flying process of the aerial target to form the aerial target tracking discrimination parameters.
7. The method for simulating and evaluating the bias-inducing performance of a non-contour ground bias-inducing source according to any one of claims 1 to 4, wherein the visual decision is based on the position of an airborne target and on a ground surface model to make a real-time decision as to the elevation angle of the airborne target relative to the bias-inducing sourceβ i Not less than the approximation of the slope of the mountain in that directionβ i ' the aerial target is in sight with the bias source, otherwise, the aerial target is out of sight.
8. The method for simulating and evaluating the bias-inducing performance of a non-contour ground bias source as claimed in claim 7, wherein the main source interceptsThe judgment is obtained by real-time calculation according to the scanning state of the main source antenna and the distance from the radiation source to the aerial target, when the main source, the induced polarization source and the aerial target can be seen, the pilot head of the aerial target detects the main source signal receivedAnd power of the bias source signal +.>The method comprises the following steps of:
(9)
(10)
wherein , and />Representing the main source and the firstiThe distance between each induced polarization source and the aerial target is calculated in real time according to coordinates, and the distance between each induced polarization source and the aerial target is calculated in real time> and />Representing the equivalent radiation power of both, +.>The antenna gain is received for the seeker.
9. The method for simulating and evaluating the bias-inducing performance of a non-contour ground bias-inducing source according to claim 8, wherein the forming of the aerial target tracking discrimination parameters comprises:
according toThe main source antenna scanning characteristic model calculates the power of the main source and the induced polarization source signals detected by the seeker, if the ratio of the power to the induced polarization source signals exceeds the instantaneous dynamic range of the seekerD r The seeker tracks the main source, otherwise the guide head tracks the bias-inducing source; accordingly, the tracking discrimination parameters of the aerial targetThe method comprises the following steps:
(11)
(12)。
10. the method for simulating and evaluating the bias-inducing efficiency of the non-contour ground bias-inducing source according to any one of claims 1 to 4, wherein the simulation model is used to develop a monte carlo simulation, and the probability of striking the main source and the bias-inducing source is determined according to the drop point distribution of the aerial target, so as to evaluate the bias-inducing efficiency;
the parameter variation in Monte Carlo simulation includes the initial distance of the horizontal plane from the aerial target to the main sourceAnd an initial orientationTotal number of simulations->By the number of changes in the initial distance->And the number of changes in the initial orientation +.>Determination, i.e.
(13)
In the simulation of each attack process of the air target, the landing judgment of the air target is carried out, a height judgment method is adopted, namely when the position of the air target is lower than the ground surface according to the ground surface model, the landing of the air target is judged, the attack process is terminated, and the moment and the last moment are recordedPosition of previous aerial target-> and />The target landing position is the average value of the two;
when the distance between the falling point of the target in the air and a certain radiation source is smaller than the killing radius of the target warhead in the air, the target is identified to be hit, and a hit result is recorded;
simulating in the set parameter variation range until all the parameter values are simulated, and recording the hit times of each radiation source，i=1, 2,3,4 divided by all simulation times, i.e. the probability of striking of the radiation source +.>；
According to the probability of the radiation source being hit, the induced polarization efficiency of the 3 induced polarization sources is estimated, the positions of the 3 induced polarization sources can be adjusted according to the result, and the purpose of optimizing the arrangement positions of the induced polarization sources is achieved by performing simulation again.
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