CN108549056A - Missile-borne radar traces into the corner reflector interference echo analogy method after moving target - Google Patents
Missile-borne radar traces into the corner reflector interference echo analogy method after moving target Download PDFInfo
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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
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Abstract
The invention belongs to Radar Technology field, discloses a kind of missile-borne radar and trace into the corner reflector interference echo analogy method after moving target, this method comprises the following steps：First calculate the Radar Cross Section of corner reflector；Again by the radius of rotary reflector and rotating speed, the Doppler frequency of corner reflector interference modulation sequence is calculated；Then amplitude and the delay that modulation sequence is interfered by corner reflector acquire corner reflector interference modulation sequence；Signal will finally be emitted with modulation sequence convolution to get corner reflector interference echo signal；The Doppler frequency brought is rotated to obtain corner reflector, enables sourceless seism object angle reflector that the target detection of speed to be taken as to arrive.
Description
Technical field
The corner reflector after moving target is traced into the invention belongs to Radar Technology field more particularly to a kind of missile-borne radar
Interference echo analogy method is primarily adapted for use in missile-borne radar under conditions of having tracked upper target, to discharging in target proximity
Corner reflector simulated, and carry out measures of effectiveness.
Background technology
In recent years, the interference of missile-borne radar moving target causes extensive concern in the field of corner reflector interference.Meter
The Doppler frequency of rotary reflector is calculated, the Radar Cross Section of corner reflector interference is calculated and calculates corner reflector interference
Amplitude be corner reflector interference simulation committed step.On radar emission signal to corner reflector, corner reflector reflects signal
It returns at radar, is equivalent to radar emission signal and have passed through modulation and obtain echo-signal, therefore to the simulation of corner reflector interference
It is exactly the simulation to modulation sequence, will finally emits signal again with modulation sequence convolution to get corner reflector interference echo signal.
Corner reflector is interfered, after target on guided missile tracking, in the same resolution cell of target, discharges one piece
Corner reflector, the corner reflector are not moved in fixed position, then according to the fixed position, are calculated corner reflector interference and are adjusted
The delay of sequence processed and amplitude, to obtain modulation sequence.But this method only regards no motion of corner reflector as fixation
Point target, do not have movement velocity, for pulse Doppler radar, can be detected as decoy, then corner reflector interferes
Lose interference effectiveness.
It is proposed across the sea now with method, it is diagonal anti-according to the hydrodynamic force coefficient of different sea conditions and corner reflector carrier
Emitter oscillating motion carries out modeling and simulating, to be derived by the micro-doppler model of corner reflector.But this method applies ring
Border has limitation, is only used for sea, and smaller by the Doppler frequency that sea speed is derived by, and is imitated to the interference of radar
Fruit is less apparent.Some scholars propose a kind of design of rotary-type corner reflector, and this method application environment is wide, still
It has higher requirements to the construction of corner reflector, because corner reflector is made of multiple movable small metallic plates, passes through rotation
Different Radar Cross Sections can be obtained by turning small metallic plate, and the Doppler frequency generated to rotation does not make a search.
In corner reflector interference, the Doppler frequency of corner reflector is accounted for, it is most important to success interference,
Because the Doppler frequency for improving chaff interferent is the bottleneck of current passive technology development, consider that the Doppler frequency of corner reflector is
One of the feasible method for realizing velocity gate deception, promotes the development of passive techniques.And existing method does not consider the more of corner reflector
General Le frequency regards corner reflector as a fixed point target, pulse Doppler radar can be made to tell true and false target, make to do
Disturb failure.
Invention content
In view of the above shortcomings of the prior art, the purpose of the present invention is to provide a kind of missile-borne radars to trace into moving target
Corner reflector interference echo analogy method afterwards rotates the Doppler frequency brought to obtain corner reflector, makes sourceless seism object
Corner reflector can be taken as the target detection of speed to arrive.
In order to achieve the above objectives, the present invention is realised by adopting the following technical scheme.
A kind of missile-borne radar traces into the corner reflector interference echo analogy method after moving target, and the corner reflector is
Dihedral Corner Reflectors are rotated, described method includes following steps：
Step 1, the linear FM signal s (t that missile-borne radar repeats to emit under the moment in m-th of pulse are obtainedm)；tmIt indicates
M-th of pulse repeats moment, m ∈ [1, Na], NaEmit pulse total number for missile-borne radar；
Step 2, remember that the width of corner reflector is a, a length of b, and inscribed when m-th of pulse repeats：Perpendicular to corner reflection
In the plane of the dihedral axis of device, the deflecting angle that incident ray deviates first direction is α, the first direction and corner reflector
Two face angles are respectively 45 °；The radius R of corner reflector is obtained according to the wide a of the corner reflector, and anti-according to the angle
Wide a, long b and the deviation angle alpha of emitter, obtain the Radar Cross Section σ of corner reflector；
Step 3, it obtains m-th of pulse and repeats the centre coordinate of corner reflector and the coordinate of guided missile under the moment, to basis
The coordinate of the centre coordinate of the corner reflection and the guided missile obtains the real-time oblique distance of corner reflector center and guided missile, and then obtains
Range gate number where corner reflector；
Step 4, if missile-borne radar is obtained comprising four antennas according to the relative position at corner reflector center and guided missile
Corner reflector deviates the azimuth and pitch angle that the antenna of missile-borne radar is directed toward in range gate where corner reflector；It calculates separately
Gain of the modulation value of corner reflector on four antennas of missile-borne radar in the range gate where corner reflector, and then obtain
Power of the modulation value of corner reflector on four antennas of missile-borne radar in range gate where corner reflector；
Step 5, the Doppler of the corner reflector under m-th of pulse repetition moment in the range gate where corner reflector is determined
Frequency, the Doppler frequency include by the relative position of corner reflector and guided missile change caused by the first Doppler frequency and by
Second Doppler frequency caused by the rotary motion of corner reflector；
Step 6, calculate in the range gate where corner reflector m-th of pulse repeat the moment under corner reflector in missile-borne thunder
Interference modulation value up on four antennas, so be calculated m-th of pulse repeat the moment under corner reflector in missile-borne radar four
Interference echo on root antenna.
It the characteristics of technical solution of the present invention and is further improved to：
(1) step 2 specifically includes following sub-step：
(2a) obtains the radius R of corner reflector according to the wide a of the corner reflector：
(2b) remembers that the crosspoint of radar emission signal and effective reflecting surface is A points, and radar emission signal travels to for the first time
On corner reflector and the crosspoint of corner reflector is B points, and radar emission signal second pass is multicast on corner reflector and corner reflection
The crosspoint of device is C points, then：
The distance between A points and B points
The distance between A points and C points LAC=LABcos(2α)；
The equivalent area of corner reflector
The Radar Cross Section of corner reflector
Wherein, λ indicates the wavelength of missile-borne radar transmitting signal.
(2) step 3 specifically includes following sub-step：
(3a) obtains corner reflector center and guided missile according to the centre coordinate of the corner reflection and the coordinate of the guided missile
Real-time oblique distance Rcn：
Wherein, cmx(tm) be guided missile x-axis coordinate, cmy(tm) be guided missile y-axis coordinate, cmz(tm) be guided missile z-axis sit
Mark, cx(tm) be corner reflector center x-axis coordinate, cy(tm) be corner reflector y-axis coordinate, cz(tm) be corner reflector z
Axial coordinate；
Range gate number n where (3b) corner reflector：
Wherein, RmIndicate the minimum irradiation distance of missile-borne radar, disrIndicate the distance resolution of missile-borne radar,<·>Table
Show that round operates.
(3) step 4 specifically includes following sub-step：
(4a) obtains the relative position [p at corner reflector center and guided missilex(tm),py(tm),pz(tm)]：
px(tm)=cx(tm)-cmx(tm)
py(tm)=cy(tm)-cmy(tm)
pz(tm)=cz(tm)-cmz(tm)
Wherein, px(tm) be corner reflector center and guided missile relative position x-axis distance, py(tm) it is in corner reflector
The y-axis distance of the relative position of the heart and guided missile, pz(tm) be corner reflector center and guided missile relative position z-axis distance；cmx
(tm) be guided missile x-axis coordinate, cmy(tm) be guided missile y-axis coordinate, cmz(tm) be guided missile z-axis coordinate, cx(tm) it is corner reflection
The x-axis coordinate at device center, cy(tm) be corner reflector y-axis coordinate, cz(tm) be corner reflector z-axis coordinate；
(4b) it is anti-to obtain the angle in the range gate where corner reflector according to the relative position at corner reflector center and guided missile
Emitter deviates the azimuth angle theta that the antenna of missile-borne radar is directed towardcAnd pitch angle
(4c) calculates separately the modulation value of the corner reflector in the range gate where corner reflector in missile-borne radar first
Gain G on antenna to the 4th antenna1、G2、G3、G4：
Wherein, θcIt is the azimuth that the antenna of corner reflector center deviation missile-borne radar is directed toward, θ0It is the antenna of missile-borne radar
The azimuth of direction, θsIt is the angle at the reception antenna azimuth beam center deviation transmitting antenna azimuth beam center of missile-borne radar
Degree, θ '0It is first zero width in the antenna radiation pattern orientation of missile-borne radar,It is corner reflector center deviation missile-borne radar
Antenna be directed toward pitch angle,It is the pitch angle that the antenna of missile-borne radar is directed toward,It is the reception antenna pitching of missile-borne radar
Beam center deviates the angle of transmitting antenna pitching beam center,It is first zero in the antenna radiation pattern pitching of missile-borne radar
Point width；
(4c) and then the modulation value of the corner reflector in the range gate where corner reflector is obtained in missile-borne radar first
Power P on antenna to the 4th antennar1、Pr2、Pr3、Pr4：
Wherein, PtIt is the transmission power of missile-borne radar, λ is the wavelength of missile-borne radar transmitting signal, and σ is the thunder of corner reflector
Up to scattering resonance state, RcnIt is the real-time oblique distance of corner reflector center and guided missile.
(4) step 5 specifically includes following sub-step：
(5a) is repeated the real-time oblique distance of moment hour angle reflector center and guided missile by m-th of pulseThe m-1 pulse
Repeat the real-time oblique distance of moment hour angle reflector center and guided missileIt calculates anti-by angle in the range gate where corner reflector
First Doppler frequency f caused by emitter and the variation of the relative position of guided missiler：
Wherein, λ indicates that the wavelength of missile-borne radar transmitting signal, PRT indicate the pulse repetition period；
(5b) sets the rotating speed of corner reflector as nr, then corner reflector repeats the moment to m-th of pulse weight in first pulse
The angle, θ rotated in the period at multiple moment；
Wherein, PRT indicates that pulse repetition period, % indicate remainder；
To obtain the light path d before corner reflector rotation according to the angle calculation of the rotation1With postrotational light path d2With
And optical path difference Δ d：
Wherein, R indicates the radius of corner reflector；
(5c) to obtain the rotary motion in the range gate where corner reflector by corner reflector caused by more than second
General Le frequencyWherein, v indicates the speed for the change in optical path length for obtaining optical path difference to time derivation.
(5) step 6 specifically includes following sub-step：
(6a) calculate in the range gate where corner reflector m-th of pulse repeat the moment under corner reflector in missile-borne radar
Interference modulation value c on four antennas1(tm)、c2(tm)、c3(tm)、c4(tm)：
Wherein, Pr1、Pr2、Pr3、Pr4Indicate the modulation sequence of corner reflector in first antenna of missile-borne radar to the 4th day
Power on line, frIndicate the first Doppler frequency caused by being changed by the relative position of corner reflector and guided missile, fvIt indicates by angle
Second Doppler frequency, t caused by the rotary motion of reflectormIndicate that m-th of pulse repeats the moment, τ indicates that corner reflector arrives
The delay time of guided missile, andC indicates the light velocity；
(6b) generates the full null sequence C that four length are total distance door number1(tm)、C2(tm)、C3(tm)、C4(tm), respectively will
Four interference modulation value c1(tm)、c2(tm)、c3(tm)、c4(tm) it is assigned to four full null sequence C1(tm)、C2(tm)、C3(tm)、C4
(tm) nth elements, to using four sequences after assignment as m-th of pulse repeat the moment under corner reflector in missile-borne thunder
Interference modulation sequence up on four antennas；
(6c) repeats interference echo of the corner reflector on four antennas of missile-borne radar under the moment to obtain m-th of pulse
r1(tm)、r2(tm)、r3(tm)、r4(tm)：
Wherein, s (tm) indicate the linear FM signal that missile-borne radar repeats to emit under the moment in m-th of pulse,It indicates
Convolution symbol.
The present invention has the following advantages that compared with prior art：1) present invention establishes the how general of rotation Dihedral Corner Reflectors
Model is strangled, the shortcomings that sourceless seism object is without Doppler frequency is overcome, enables corner reflector by radar as there is speed
Target detection arrive, ensure that interference effect；And Doppler model is ensure that based on Radar cross section model
The uniformity of block mold；The Doppler model application environment is wide, is suitable for the Dihedral Corner Reflectors of various constructions, Doppler's frequency
Rate is more easy to be arrived by detections of radar greatly.2) in the Radar cross section model of corner reflector, by the wide a of smaller corner reflector
Prodigious Radar Cross Section can be acquired with long b, illustrates that the corner reflector of small size can obtain high Radar Cross Section,
Radar Cross Section directly affects the amplitude of corner reflector interference echo, can make the Amplitude Ratio target echo of interference echo
Big more of amplitude, it is easier to be arrived by detections of radar；In addition it can also make the synthesis center of energy of corner reflector and target largely
Corner reflector is biased on ground, far from target, i.e. the synthesis center of energy of guided missile tracking far from target, so at this time interference effect compared with
It is good；And corner reflector is of low cost, highly practical.
Description of the drawings
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
Obtain other attached drawings according to these attached drawings.
Fig. 1 is that a kind of missile-borne radar provided in an embodiment of the present invention traces into the corner reflector interference echo after moving target
The flow diagram of analogy method；
Fig. 2 a are the straight two sides corner reflector geometry graphics used in the embodiment of the present invention；
Fig. 2 b are the straight two sides corner reflector geometry vertical view used in the embodiment of the present invention；
Fig. 3 is the equivalent area schematic diagram of the straight two sides corner reflector used in the embodiment of the present invention；
Fig. 4 a are the vertical view of straight two sides corner reflector when being rotated in the embodiment of the present invention；
Fig. 4 b are the partial enlarged view of straight two sides corner reflector when being rotated in the embodiment of the present invention；
Fig. 5 a are interference echo time-domain diagram of the corner reflector on first antenna；
Fig. 5 b are interference echo time-domain diagram of the corner reflector on second antenna；
Fig. 5 c are interference echo time-domain diagram of the corner reflector on third root antenna；
Fig. 5 d are interference echo time-domain diagram of the corner reflector on the 4th antenna；
Fig. 6 is interference modulation sequence vertical view of the corner reflector on first antenna；
Fig. 7 is interference modulation sequence doppler characterization figure of the corner reflector on first antenna；
Fig. 8 is after pulse pressure and channel signal figure；
Fig. 9 is monopulse ranging figure；
Figure 10 a are the pulse interception angle result of target；
Figure 10 b are that the pulse of target surveys pitch angle result.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Referring to Fig.1, a kind of missile-borne radar provided in an embodiment of the present invention traces into the corner reflector interference after moving target
Analogue echoes method includes following steps：
Step 1, the transmitting signal of missile-borne radar is linear FM signal s (tm)。
Wherein, γ is the frequency modulation rate of missile-borne radar；Wherein tmFor m (m ∈ [1, Na], NaFor overall pulse number) a PRT (arteries and veins
Rush the repetition time) moment；
Step 2, with reference to Fig. 2 b, corner reflector radius R is obtained by the wide a of rotation Dihedral Corner Reflectors；With reference to Fig. 2 a, by rotating
The wide a of Dihedral Corner Reflectors, long b and in the plane perpendicular to dihedral axis, incident ray deviates a direction (direction and two
Face angle all at 45 °) angle [alpha] can obtain the Radar Cross Section σ of corner reflector with reference to Fig. 3.
As shown in Figure 3：
LAC=LABcos(2α)
Wherein, LABFor A points (crosspoint of radar emission signal and effective reflecting surface) in Fig. 2 b and B points, (radar emission is believed
Number first time travels on corner reflector and the crosspoint of corner reflector) between length；LACFor A points in Fig. 2 b, (radar emission is believed
Number and effective reflecting surface crosspoint) and C points (radar emission signal second pass is multicast to the phase on corner reflector with corner reflector
Intersection point) between length；AeFor the equivalent area of corner reflector；λ is the wavelength that missile-borne radar emits signal.
Step 3, the real-time oblique distance of the two, then the minimum irradiation by missile-borne radar are obtained by corner reflector coordinate and guided missile coordinate
Distance and distance resolution obtain the range gate n where corner reflector.
Wherein, RcnIt is the oblique distance of corner reflector center and guided missile, cmx(tm) be guided missile x-axis coordinate, cmy(tm) it is guided missile
Y-axis coordinate, cmz(tm) be guided missile z-axis coordinate, cx(tm) be corner reflector x-axis coordinate, cy(tm) be corner reflector y
Axial coordinate, cz(tm) be corner reflector z-axis coordinate, RmIt is the minimum irradiation distance of missile-borne radar, disrBe missile-borne radar away from
High Resolution；
Step 4, it by the relative coordinate of corner reflector and guided missile, obtains where corner reflector in range gate, corner reflector
Deviate missile-borne radar antenna be directed toward orientation and pitch angle, then by missile-borne radar antenna be directed toward azimuth, pitch angle,
First zero in the antenna radiation pattern pitching of first zero width, missile-borne radar in the antenna radiation pattern orientation of missile-borne radar
Width, orientation offset angle and pitching offset angle, obtain where corner reflector in range gate corner reflector modulation value four days
Line gain G1、G2、G3、G4, then substitute into radar equation, by respectively obtain where corner reflector in range gate four antennas angle
The power P of reflector modulation sequencer1、Pr2、Pr3、Pr4。
Wherein, θcIt is the azimuth that corner reflector deviates that the antenna of missile-borne radar is directed toward, θ0It is the antenna direction of missile-borne radar
Azimuth, θsIt is the angle at the reception antenna azimuth beam center deviation transmitting antenna azimuth beam center of missile-borne radar, θ ＇0
It is first zero width in the antenna radiation pattern orientation of missile-borne radar,It is the antenna direction that corner reflector deviates missile-borne radar
Pitch angle,It is the pitching that the antenna of missile-borne radar is directed toward,It is the reception antenna pitching beam center deviation of missile-borne radar
The angle of transmitting antenna pitching beam center,It is first zero width, P in the antenna radiation pattern pitching of missile-borne radarrIt is
The transmission power of missile-borne radar, λ are the wavelength of missile-borne radar transmitting signal, and σ is the Radar Cross Section of corner reflector, RcnIt is
The oblique distance at corner reflector center and guided missile；
Step 5, the Doppler frequency f of rotary reflectordChanged by the relative position of corner reflector and guided missile and is rotated
Movement causes.
5a) relative position of corner reflector and guided missile changes with moving for guided missile, by m (m ∈ [1, Na], Na
For overall pulse number) oblique distance of the corner reflector and guided missile at a PRT (pulse-recurrence time) momentWith m-1 (m ∈ [1, Na],
NaFor overall pulse number) oblique distance of the corner reflector and guided missile at a PRT (pulse-recurrence time) momentIt can be calculated at angle
Relative position changes the Doppler frequency f brought both in range gate where reflectorr：
Wherein, λ is the wavelength of missile-borne radar transmitting signal；
5b) is calculated corner reflector by the rotating speed nr of rotary reflector with reference to Fig. 4 and repeated the moment in first pulse
The angle, θ (θ ∈ [0, pi/2]) that rotates in the period at moment is repeated to m-th of pulse, then before and after calculating rotation by the goniometer
Optical path difference Δ d, optical path difference is then obtained into the speed v of change in optical path length, the speed by change in optical path length and rotation to time derivation
The radius R of corner reflector is finally found out in the Doppler frequency f that rotary motion is brought in range gate where corner reflectorv：
The angle of rotation：
Light path before rotation：
Postrotational light path：
Optical path difference：
Then the Doppler frequency of corner reflector is：
Wherein, λ is the wavelength of missile-borne radar transmitting signal, and PRT indicates that pulse repetition period, % indicate remainder；；
Step 6, the corresponding oblique distance R of the range gate as where corner reflector in the range gate where corner reflectorcn, angle can be obtained
Delay τ of the reflector from guided missile, then interfere by the corner reflector of four antennas the amplitude P of modulation valuer1、Pr2、Pr3、Pr4It is mostly general
Frequency displacement is strangled, the interference modulation value c of the corner reflector of four antennas can be obtained1(tm)、c2(tm)、c3(tm)、c4(tm), then generate
Four row length are the full null sequence C of total distance door number1(tm)、C2(tm)、C3(tm)、C4(tm), respectively by four interference modulation value c1
(tm)、c2(tm)、c3(tm)、c4(tm) it is assigned to four full null sequence C1(tm)、C2(tm)、C3(tm)、C4(tm) nth elements, i.e.,
It has obtained m-th of pulse and has repeated interference modulation sequence C of the corner reflector on four antennas of missile-borne radar under the moment1(tm)、C2
(tm)、C3(tm)、C4(tm)。
Wherein, c is the light velocity, frChange the Doppler frequency brought, f for corner reflector and guided missile relative positionvFor corner reflection
Device rotates the Doppler frequency brought, tmFor m (m ∈ [1, Na], NaFor overall pulse number) a PRT (pulse-recurrence time) moment；
Step 7, by C1(tm)、C2(tm)、C3(tm)、C4(tm) respectively with transmitting signal convolution, finally obtain four antennas
The echo r of corner reflector interference1(tm)、r2(tm)、r3(tm)、r4(tm)。
It can obtain, it is contemplated that after the Doppler frequency of corner reflector, corner reflector can be taken as the target of speed
It detects, interference effect is more preferable.
The effect of the present invention can be described further by following emulation experiment：
Simulated conditions：
The simulation parameter of emulation experiment 1 and emulation experiment 2 is provided by Tables 1 and 2.
1 system emulation parameter of table
2 corner reflector simulation parameter of table
2) emulation content
Emulation experiment 1：In the present invention, target velocity is that the moving target of [50,0,0] discharges corner reflector interference.From
It is identical that Fig. 5 a, Fig. 5 b, Fig. 5 c and Fig. 5 d can be seen that the interference echo characteristic that different antennae receives, and only amplitude is different, institute
Analogous diagram to provide single antenna in emulation experiment of the present invention illustrates, you can know other antennas interference modulation sequence and
Echoing characteristics；From fig. 6, it can be seen that because the position of corner reflector immobilizes, the range gate where corner reflector becomes
Change it is minimum, can regard as where range gate do not change with umber of pulse, relation curve is straight line, i.e. distance where corner reflector
Door is fixed value；From figure 7 it can be seen that there are Doppler's frequencies that the rotary motion of corner reflector is brought in fixed range gate
Rate, it is consistent with theory analysis, the correctness of emulation is illustrated, so the corner reflector of rotation can be taken as the target of speed
It is arrived by detections of radar.
Emulation experiment 2：For further prove the interference of the method for the present invention be it is effective, can be from monopulse ranging and angle measurement
As a result it obtains.From figure 8, it is seen that the synthesis barycenter and target of corner reflector and target are in upward apart from each other, the explanation of distance
Corner reflector and target separate fully up in distance；Corner reflector and the synthesis barycenter of target change very little (because of target meeting
Have slower movement), meet corner reflector fixed position actual conditions；And the bright of lines secretly represents the big of amplitude
It is small, it is brighter to illustrate that amplitude is bigger (lower section lines represent interference echo, and top lines represent target echo), so corner reflector is dry
Disturb big more of amplitude of the Amplitude Ratio target echo of echo, it is easier to be arrived by detections of radar, illustrate Radar Cross Section mould
The validity of type, and simulation result is consistent with theory analysis, illustrates the correctness of emulation；It surveys as can be seen from Figure 9
Corner reflector and the synthesis centroid distance of target have error with ideal target range, illustrate that interference has played effect；From Figure 10 a
(theoretical value 0, so measured value and error overlap) and Figure 10 b can be seen that the reason of the measured value and target of radar tracking point
It is larger by value difference, it is because being added to corner reflector interference at this time, the synthesis barycenter of corner reflector and target successfully attracts
Radar so that radar forgoes one's aim, then tracks barycenter, illustrates that corner reflector interference plays effect.
Above-mentioned emulation experiment demonstrates effectiveness of the invention and correctness.Compared with traditional method, overcome passive
Chaff interferent does not have the shortcomings that Doppler frequency, enables corner reflector by radar as there is the target detection of speed to arrive；Angle is anti-
Emitter has high radar scattering area, and the amplitude of interference echo can be made larger；And the synthesis matter of corner reflector and target can be made
The heart is largely far from target, so good interference effect can be obtained.
One of ordinary skill in the art will appreciate that：Realize that all or part of step of above method embodiment can pass through
The relevant hardware of program instruction is completed, and program above-mentioned can be stored in computer read/write memory medium, which exists
When execution, step including the steps of the foregoing method embodiments is executed；And storage medium above-mentioned includes：ROM, RAM, magnetic disc or CD
Etc. the various media that can store program code.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, can easily think of the change or the replacement, and should all contain
Lid is within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (6)
1. a kind of missile-borne radar traces into the corner reflector interference echo analogy method after moving target, which is characterized in that described
Corner reflector is rotation Dihedral Corner Reflectors, and described method includes following steps：
Step 1, the linear FM signal s (t that missile-borne radar repeats to emit under the moment in m-th of pulse are obtainedm)；tmIt indicates m-th
Pulse repeats moment, m ∈ [1, Na], NaEmit pulse total number for missile-borne radar；
Step 2, remember that the width of corner reflector is a, a length of b, and inscribed when m-th of pulse repeats：Perpendicular to corner reflector
In the plane of dihedral axis, deflecting angle that incident ray deviates first direction is α, two of the first direction and corner reflector
Face angle is respectively 45 °；The radius R of corner reflector is obtained according to the wide a of the corner reflector, and according to the corner reflector
Wide a, long b and deviation angle alpha, obtain the Radar Cross Section σ of corner reflector；
Step 3, it obtains m-th of pulse and repeats the centre coordinate of corner reflector and the coordinate of guided missile under the moment, to according to described
The coordinate of the centre coordinate of corner reflection and the guided missile obtains the real-time oblique distance of corner reflector center and guided missile, and then it is anti-to obtain angle
Range gate number where emitter；
Step 4, if missile-borne radar obtains anti-at angle comprising four antennas according to the relative position at corner reflector center and guided missile
Corner reflector deviates the azimuth and pitch angle that the antenna of missile-borne radar is directed toward in range gate where emitter；It calculates separately at angle
Gain of the modulation value of corner reflector on four antennas of missile-borne radar in range gate where reflector, and then obtain anti-at angle
Power of the modulation value of corner reflector on four antennas of missile-borne radar in range gate where emitter；
Step 5, determine that m-th of pulse repeats the Doppler of corner reflector under the moment frequently in the range gate where corner reflector
Rate, the Doppler frequency include by caused first Doppler frequency of the relative position of corner reflector and guided missile variation and by angle
Second Doppler frequency caused by the rotary motion of reflector；
Step 6, calculate in the range gate where corner reflector m-th of pulse repeat the moment under corner reflector in missile-borne radar four
Interference modulation value on root antenna, so be calculated m-th of pulse repeat the moment under corner reflector in four days of missile-borne radar
Interference echo on line.
2. a kind of missile-borne radar according to claim 1 traces into the corner reflector interference echo simulation side after moving target
Method, which is characterized in that step 2 specifically includes following sub-step：
(2a) obtains the radius R of corner reflector according to the wide a of the corner reflector：
(2b) remembers that the crosspoint of radar emission signal and effective reflecting surface is A points, and it is anti-that radar emission signal travels to angle for the first time
In emitter and the crosspoint of corner reflector is B points, and radar emission signal second pass is multicast on corner reflector and corner reflector
Crosspoint is C points, then：
The distance between A points and B points
The distance between A points and C points LAC=LABcos(2α)；
The equivalent area of corner reflector
The Radar Cross Section of corner reflector
Wherein, λ indicates the wavelength of missile-borne radar transmitting signal.
3. a kind of missile-borne radar according to claim 1 traces into the corner reflector interference echo simulation side after moving target
Method, which is characterized in that step 3 specifically includes following sub-step：
(3a) obtains the real-time of corner reflector center and guided missile according to the centre coordinate of the corner reflection and the coordinate of the guided missile
Oblique distance Rcn：
Wherein, cmx(tm) be guided missile x-axis coordinate, cmy(tm) be guided missile y-axis coordinate, cmz(tm) be guided missile z-axis coordinate, cx
(tm) be corner reflector center x-axis coordinate, cy(tm) be corner reflector y-axis coordinate, cz(tm) be corner reflector z-axis sit
Mark；
Range gate number n where (3b) corner reflector：
Wherein, RmIndicate the minimum irradiation distance of missile-borne radar, disrIndicate the distance resolution of missile-borne radar,<·>Indicate four
House five enters floor operation.
4. a kind of missile-borne radar according to claim 1 traces into the corner reflector interference echo simulation side after moving target
Method, which is characterized in that step 4 specifically includes following sub-step：
(4a) obtains the relative position [p at corner reflector center and guided missilex(tm),py(tm),pz(tm)]：
px(tm)=cx(tm)-cmx(tm)
py(tm)=cy(tm)-cmy(tm)
pz(tm)=cz(tm)-cmz(tm)
Wherein, px(tm) be corner reflector center and guided missile relative position x-axis distance, py(tm) it is corner reflector center and to lead
The y-axis distance of the relative position of bullet, pz(tm) be corner reflector center and guided missile relative position z-axis distance；cmx(tm) it is to lead
The x-axis coordinate of bullet, cmy(tm) be guided missile y-axis coordinate, cmz(tm) be guided missile z-axis coordinate, cx(tm) it is corner reflector center
X-axis coordinate, cy(tm) be corner reflector y-axis coordinate, cz(tm) be corner reflector z-axis coordinate；
(4b) obtains the corner reflector in the range gate where corner reflector according to the relative position at corner reflector center and guided missile
Deviate the azimuth angle theta that the antenna of missile-borne radar is directed towardcAnd pitch angle
(4c) calculates separately the modulation value of the corner reflector in the range gate where corner reflector in first antenna of missile-borne radar
Gain G to the 4th antenna1、G2、G3、G4：
Wherein, θcIt is the azimuth that the antenna of corner reflector center deviation missile-borne radar is directed toward, θ0It is the antenna direction of missile-borne radar
Azimuth, θsIt is the angle at the reception antenna azimuth beam center deviation transmitting antenna azimuth beam center of missile-borne radar, θ '0
It is first zero width in the antenna radiation pattern orientation of missile-borne radar,It is the antenna of corner reflector center deviation missile-borne radar
The pitch angle of direction,It is the pitch angle that the antenna of missile-borne radar is directed toward,Be missile-borne radar reception antenna pitching wave beam in
The heart deviates the angle of transmitting antenna pitching beam center,It is that first zero is wide in the antenna radiation pattern pitching of missile-borne radar
Degree；
(4c) and then the modulation value of the corner reflector in the range gate where corner reflector is obtained in first antenna of missile-borne radar
Power P to the 4th antennar1、Pr2、Pr3、Pr4：
Wherein, PtIt is the transmission power of missile-borne radar, λ is the wavelength of missile-borne radar transmitting signal, and σ is that the radar of corner reflector dissipates
Penetrate sectional area, RcnIt is the real-time oblique distance of corner reflector center and guided missile.
5. a kind of missile-borne radar according to claim 1 traces into the corner reflector interference echo simulation side after moving target
Method, which is characterized in that step 5 specifically includes following sub-step：
(5a) is repeated the real-time oblique distance of moment hour angle reflector center and guided missile by m-th of pulseThe m-1 pulse repeats
The real-time oblique distance of moment hour angle reflector center and guided missileIt calculates in the range gate where corner reflector by corner reflector
First Doppler frequency f caused by relative position variation with guided missiler：
Wherein, λ indicates that the wavelength of missile-borne radar transmitting signal, PRT indicate the pulse repetition period；
(5b) sets the rotating speed of corner reflector as nr, then corner reflector is when first pulse repeats the moment and repeated to m-th of pulse
The angle, θ rotated in the period at quarter；
Wherein, PRT indicates that pulse repetition period, % indicate remainder；
To obtain the light path d before corner reflector rotation according to the angle calculation of the rotation1With postrotational light path d2And light
Path difference Δ d：
Wherein, R indicates the radius of corner reflector；
(5c) to obtain the rotary motion in the range gate where corner reflector by corner reflector caused by the second Doppler
FrequencyWherein, v indicates the speed for the change in optical path length for obtaining optical path difference to time derivation.
6. a kind of missile-borne radar according to claim 1 traces into the corner reflector interference echo simulation side after moving target
Method, which is characterized in that step 6 specifically includes following sub-step：
(6a) calculates m-th of pulse in the range gate where corner reflector and repeats under the moment corner reflector in missile-borne radar four
Interference modulation value c on antenna1(tm)、c2(tm)、c3(tm)、c4(tm)：
Wherein, Pr1、Pr2、Pr3、Pr4Indicate the modulation sequence of corner reflector on first antenna of missile-borne radar to the 4th antenna
Power, frIndicate the first Doppler frequency caused by being changed by the relative position of corner reflector and guided missile, fvIt indicates by corner reflection
Second Doppler frequency, t caused by the rotary motion of devicemIndicate that m-th of pulse repeats the moment, τ indicates corner reflector to guided missile
Delay time, andC indicates the light velocity；
(6b) generates the full null sequence C that four length are total distance door number1(tm)、C2(tm)、C3(tm)、C4(tm), respectively by four
Interfere modulation value c1(tm)、c2(tm)、c3(tm)、c4(tm) it is assigned to four full null sequence C1(tm)、C2(tm)、C3(tm)、C4(tm)
Nth elements, to repeat under the moment corner reflector in missile-borne radar four using four sequences after assignment as m-th of pulse
Interference modulation sequence on antenna；
(6c) repeats interference echo r of the corner reflector on four antennas of missile-borne radar under the moment to obtain m-th of pulse1
(tm)、r2(tm)、r3(tm)、r4(tm)：
Wherein, s (tm) indicate the linear FM signal that missile-borne radar repeats to emit under the moment in m-th of pulse,Indicate convolution symbol
Number.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109459736A (en) * | 2019-01-04 | 2019-03-12 | 北京环境特性研究所 | A kind of radar drone design method and apparatus |
| CN112105937A (en) * | 2019-09-12 | 2020-12-18 | 深圳市大疆创新科技有限公司 | Antenna directional pattern testing method, device and storage medium |
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| CN113391275A (en) * | 2020-03-12 | 2021-09-14 | 中国人民解放军火箭军装备部装备项目管理中心 | Large complex target equivalent simulation method and device adopting electronic angle inversion |
| SE2000154A1 (en) * | 2020-09-08 | 2022-03-09 | Anders Widman | Doppler-compensated radar interference with interference technology chirp stealer |
| CN113009475A (en) * | 2021-02-22 | 2021-06-22 | 佛山科学技术学院 | Radar reflector, radar detection system, radar signal detection method and device |
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