CN103558773B - A kind of target location control system - Google Patents

Abstract

The present invention relates to a kind of target location control system, including calibrating installation, radio frequency target simulation main control computer, radiofrequency signal control unit, radio frequency source, target location control unit, array-fed system, and signal radiating curtain; Described array-fed system includes multiple signal channels; Each signalling channel in multiple signal channels includes Fine-precision control assembly and controls assembly with coarse positioning; Described signal radiating curtain installs multiple active antenna; Described signal radiating curtain adopts planar array structure, and planar array is made up of multiple four-tuple, and described four-tuple is made up of in planar array four adjacent active antennas; The wide-angle planar array structure that described signal radiating curtain adopts, than wide-angle spherical array simple in construction, easily manufactured and installed, simultaneously facilitates the maintenance in later stage; And having the test center of flexibility and changeability, the field such as measures of effectiveness test under the Hardware-in-loop Simulation Experimentation and complex electromagnetic environment of large-scale tested device has significant advantage.

Description

A kind of target location control system

Technical field

The present invention relates to a kind of radio frequency semi-true object emulation technology, especially a kind of target location control system, analyze method including novel array structure, Novel radiation unit group (four-tuple) operation principle, new positional control algorithm, synthesis field error.

Background technology

Presently used array target location control system mainly includes the subsystems such as signal radiating curtain, radio frequency source, array-fed system, computer control and calibrating installation. Wherein, the traditional structure of signal radiating curtain is spherical array form, and its sphere centre is positioned at above turret axis, and tested device is positioned at the region near sphere centre. The usual only one of which of test center of this spheric array column target simulation system, the tested device volume of adaptation is general all less, within its size is typically in 2m �� 2m �� 2m.

But, along with the development of radio frequency semi-true object emulation technology, the volume of tested device starts to develop to maximization direction, if tested device full-size is more than 40m. In the anechoic chamber, of the confined space, the parts of large-scale tested device diverse location/subsystem participates in test, it is necessary to multiple test centers or test center can change flexibly, to meet the l-G simulation test needs that same device interior is in the parts of diverse location.

Simultaneously, the application of semi-true object emulation technology constantly expands, the l-G simulation test of large-scale tested device is tested progressively to paying close attention to product potency test development by properties of product, and the measures of effectiveness test under complex electromagnetic environment such as such as large aircraft, naval vessel etc. is the hot subject of research at present.The test of product measures of effectiveness is different from the high accuracy needed for properties of product evaluation test, measures of effectiveness test is more concerned with how to build complex electromagnetic environment, and the ability to work that tested device is under complex electromagnetic environment, and do not pursue very high target location simulation precision. In above test, the spherical array target simulation system have single test center, being only applicable to small-sized tested device can not meet test requirements document, in the urgent need to constructing a kind of target location control system, to can better complete new test.

Summary of the invention

The technical problem to be solved in the present invention is to provide a kind of target location control system, and it is possible not only to change echo signal position on radiating curtain, it is also possible to change the test center of target position signal.

For solving above-mentioned technical problem, the present invention relates to a kind of target location control system, including calibrating installation, radio frequency target simulation main control computer, radiofrequency signal control unit, radio frequency source, target location control unit, array-fed system, and signal radiating curtain. Described array-fed system includes multiple signal channels, and the quantity of signalling channel determines the quantity of target. Described signal radiating curtain is provided with multiple active antenna. Each signalling channel in multiple signal channels all includes Fine-precision control assembly and controls assembly with coarse positioning. Described signal radiating curtain adopts planar array structure, and described planar array is made up of multiple four-tuple, and described four-tuple is made up of in planar array four adjacent active antennas.

The Fine-precision control assembly of described each signalling channel is made up of power divider and four subsequent leg. Described subsequent leg includes program controlled phase shifter, programmable attenuator, linear power amplifier.

The coarse positioning of described each signalling channel controls assembly and is made up of four groups of switch matrix and multiple power combiners. Often group switch matrix comprises multiple output port; Each output port of four groups of switch matrix is all connected with the corresponding input of power combiner. The quantity of described power combiner is equal with antenna amount on signal radiating curtain, and the outfan of power combiner is connected with four-tuple internal antenna on signal radiating curtain.

In described Fine-precision control assembly, each subsequent leg all controls in assembly the corresponding connection of one group of switch matrix with coarse positioning.

The present invention controls the change of composite signal radiation center position by the control algolithm of a kind of target location control system, described target location control system is by the programmable attenuator in control Fine-precision control assembly and program controlled phase shifter, thus changing amplitude and the phase place of four radiating element signals in corresponding four-tuple, and then control composite signal radiation center relative position in corresponding four-tuple, under its principle is shown in:

With rotation of rotary table center for initial point, four Radiative antenna elements respectively A, B, C, D in four-tuple, their the position angle of pitch and azimuth describe, and are divided into for ��_i(i=1,2,3,4) andIf the operating frequency of four-tuple antenna A, B, C, D is identical, being ��, the electric feed signal amplitude of each antenna radiation unit is E_i' (i=1,2,3,4), phase place is �� respectively_i(i=1,2,3,4), then on tested device antenna opening diametric plane, the electric field of each unit radiation signal is respectively

A: $E_1=\frac{E_1^{\′}}{R_1}{e}^{j({\mathrm{\β}}_1-{\mathrm{kR}}_1)}\·e^{j\mathrm{\ω}t}=E_1^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_1-{\mathrm{kR}}_1)}$

B: $E_2=\frac{E_2^{\′}}{R_2}{e}^{j({\mathrm{\β}}_2-{\mathrm{kR}}_2)}\·e^{j\mathrm{\ω}t}=E_2^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_2-{\mathrm{kR}}_2)}$

C: $E_3=\frac{E_3^{\′}}{R_3}{e}^{j({\mathrm{\β}}_3-{\mathrm{kR}}_3)}\·e^{j\mathrm{\ω}t}=E_3^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_3-{\mathrm{kR}}_3)}---\left(1\right)$

D: $E_4=\frac{E_4^{\′}}{R_4}{e}^{j({\mathrm{\β}}_4-{\mathrm{kR}}_4)}\·e^{j\mathrm{\ω}t}=E_4^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_4-{\mathrm{kR}}_4)}$

Wherein k=2 ��/�� is phase-shift constant, kR_iFor the phase contrast that transmission path produces. Above-mentioned electric field is represented by the electric field component of orientation and pitch orientation

$E_{z_i}=E_i\·{\mathrm{sin\θ}}_i$

Then, total electric field is represented by

$E_z=\underset{i=1}{\overset{4}{\Σ}}{E}_{z_i}=\underset{i=1}{\overset{4}{\Σ}}{E}_i\·{\mathrm{sin\θ}}_i$

Can try to achieve synthesis rink corner degree is

$\mathrm{\θ}=atan\left(\frac{E_z}{\sqrt{{E_x}^2+{E_y}^2}}\right)=atan\left(\frac{\underset{i=1}{\overset{4}{\Σ}}{E}_{z_i}}{\sqrt{{\left(\underset{i=1}{\overset{4}{\Σ}}{E}_{x_i}\right)}^2+{\left(E_{y_i}\right)}^2}}\right)---\left(4\right)$

Formula (4) is called angle scintillations equation.When small angle approximation, and by phase compensation, formula (4) can be reduced to

$\mathrm{\θ}=atan\frac{\underset{i=1}{\overset{4}{\Σ}}{E}_i^{\′\′}\·{\mathrm{\θ}}_i}{\underset{i=1}{\overset{4}{\Σ}}{E}_i^{\′\′}}---\left(5\right)$

By formula (5) it can be seen that the position (azimuth and the angle of pitch) of known four-tuple, by controlling the amplitude E of four radiating element signals_i' (i=1,2,3,4) obtains E_i" (i=1,2,3,4) can change equivalent energy radiation center relative position in four-tuple, thus realizing Fine-precision control.

Meanwhile, described target location control system controls the break-make of assembly breaker in middle matrix by controlling coarse positioning, thus changing composite signal radiation center to be in different four-tuple.

According to angle measuring principle it can be seen that the gradient direction of the electromagnetic wave that target apparent direction is target scattering that observes of reception antenna phase front on reception antenna bore face. Target location control system adopts four-tuple antenna array to carry out simulated target echo spatial parameter, and owing to four radiating elements produced electromagnetic field on reception antenna bore face is overlapped mutually, the phase front of this synthesis field is no longer a sphere, and is distorted. When reception antenna bore face, size cannot be ignored, and when being namely not to be regarded as a bit, due to the phase front distortion difference of synthesis field each point on antenna opening diametric plane, arrival bearing makes a mistake to cause reception antenna to judge, this error is called plane wave error. Below the mechanism of production of plane wave error is analyzed.

According to formula (1), it is left out phase factor e^j��t, on arrival tested device antenna opening diametric plane, the electric field intensity of each unit radiation signal is respectively

A: $E_1=\frac{E_1^{\′}}{R_1}{e}^{j({\mathrm{\β}}_1-{\mathrm{kR}}_1)}$

B: $E_2=\frac{E_2^{\′}}{R_2}{e}^{j({\mathrm{\β}}_2-{\mathrm{kR}}_2)}$

C: $E_3=\frac{E_3^{\′}}{R_3}{e}^{j({\mathrm{\β}}_3-{\mathrm{kR}}_3)}---\left(6\right)$

D: $E_4=\frac{E_4^{\′}}{R_4}{e}^{j({\mathrm{\β}}_4-{\mathrm{kR}}_4)}$

Utilizing field superposition theorem, the total electric field strength that can obtain tested device Antenna aperture place is:

$\begin{array}{c}E(x,y,z)\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}{e}^{j({\mathrm{\β}}_i-{\mathrm{jkR}}_i)}\\ =\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}\cos ({\mathrm{\β}}_i-{\mathrm{kR}}_i)+j\frac{E_i^{\′}}{R_i}\sin ({\mathrm{\β}}_i-{\mathrm{kR}}_i)\\ =E_R+{\mathrm{jE}}_I\end{array}---\left(7\right)$

In formula:

Synthesis field real part: $E_R=\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}cos({\mathrm{\β}}_i-{\mathrm{kR}}_i)---\left(8\right)$

Synthesis field imaginary part: $E_I=\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}sin({\mathrm{\β}}_i-{\mathrm{kR}}_i)---\left(9\right)$

Then synthesis field amplitude: $\left|E(x,y,z)\right|=\sqrt{E_R^2+E_I^2}---\left(10\right)$

Synthesis field phase: $\mathrm{\ψ}=atan\left(\frac{E_I}{E_R}\right)---\left(11\right)$

(x_i,y_i,z_i) it is the coordinate of active antenna, (x, y z) are the coordinate of tested device antenna.

Based on above-mentioned error analysis, above-mentioned synthesis field plane wave error is analyzed processing by the present invention by the error analysis method of a kind of target location control system, and the error control method of described target location control system comprises the steps:

1) according to the caliber size of tested device antenna in radio frequency Hardware-in-loop Simulation Experimentation and test frequency, Hardware-in-loop Simulation Experimentation distance is calculated;

2) simultaneously according to the caliber size of tested antenna and test frequency, engineering experience formula the unit interval between four-tuple antenna is primarily determined that in planar array;

3) target location control system is drawn up with above-mentioned l-G simulation test distance and unit interval for the total electric field amplitude wave-shape under condition and total electric field phase waveform by computer mould;

4) by the total electric field amplitude wave-shape that obtains in above-mentioned steps with total electric field phase waveform compared with point source signal waveform, if there is obvious beam splitting in composite signal waveform, then at l-G simulation test apart from constant, adjustment unit spacing, until total electric field waveform compared with point source signal waveform without obvious beam splitting;

5) four-tuple antenna uses the determined l-G simulation test distance of above-mentioned steps and unit interval, it is possible to simulation point source signal, and can the site error of composite signal be controlled in rational scope.

Compared to prior art, present invention have the advantage that

1) signal radiating curtain adopts plane array, and wide-angle planar array structure, than wide-angle spherical array simple in construction, easily manufactured and installed, simultaneously facilitates the maintenance in later stage;

2) there is single test center with spheric array, suitable in compared with small-sized tested device, planar array structure has the test center of flexibility and changeability, making it more adapt to the Hardware-in-loop Simulation Experimentation of large-scale tested device, especially under complex electromagnetic environment, the field such as measures of effectiveness test of large-scale tested device has more unrivaled advantage;

3) by the error analysis in test is processed, it is possible to synthesis field plane wave error is compensated, obtains higher test accuracy, thus reaching the high performance-price ratio that pilot system is built.

Accompanying drawing explanation

Fig. 1 is target location control system schematic diagram in the present invention;

Fig. 2 is midplane array structure schematic diagram of the present invention;

Fig. 3 is array-fed system schematic in the present invention;

Fig. 4 is the coordinate system setting up four-tuple mathematical model in the present invention;

Fig. 5 is the variable test center schematic diagram of composite signal in the present invention;

Fig. 6 is the measures of effectiveness test schematic diagram of large aircraft under complex electromagnetic environment in the present invention;

Fig. 7 is that in the present invention, unit interval is amplitude and the phase waveform figure of total electric field during 60mrad and point source electric field;

Fig. 8 is that in the present invention, unit interval is amplitude and the phase waveform figure of total electric field during 40mrad and point source electric field;

Fig. 9 is the measures of effectiveness test schematic diagram of large ship under complex electromagnetic environment in the present invention;

Description of reference numerals:

1 calibrating installation, 2 radio frequency target simulation main control computers, 3 radiofrequency signal control units, 4 radio frequency sources, 5 target location control units, 6 array-fed systems, 7 signal radiating curtains, 8 active antennas, 9 turntables, 10 tested devices, 11 anechoic chamber,s, 12 four-tuple, 13 power dividers, 14 program controlled phase shifters, 15 programmable attenuators, 16 linear power amplifiers, 17 switch matrix, 18 power combiners, 19 signal receiving units, 20 horizontal planes, 21 datum lines, 22 arrays, 23 targets, 24 array center, 25 azimuths, 26 pitching angle theta.

Detailed description of the invention

Below in conjunction with the drawings and specific embodiments, it is further elucidated with the present invention, it should be understood that following detailed description of the invention is merely to illustrate the present invention rather than restriction the scope of the present invention.

Embodiment 1

A kind of target location control system as shown in Figure 1, including calibrating installation 1, radio frequency target simulation main control computer 2, radiofrequency signal control unit 3, radio frequency source 4, target location control unit 5, array-fed system 6, and signal radiating curtain 7. Described array-fed system includes 4 tunnel signalling channels, and the quantity of signalling channel determines the quantity of target. Described signal radiating curtain adopts planar array structure as shown in Figure 2, and described signal radiating curtain is provided with 35 active antennas 8. Described planar array is made up of 24 four-tuple 12, and described four-tuple 12 is made up of in planar array four adjacent active antennas 8.

As it is shown on figure 3, the signalling channel of described feed system is 4 passages, wherein 3 echo signal passages, 1 interference signalling channel. The array-fed system of each passage includes Fine-precision control assembly and controls assembly with coarse positioning. The Fine-precision control assembly of each passage is made up of power divider 13 and four subsequent leg; Described every subsequent leg includes program controlled phase shifter 14, programmable attenuator 15, linear power amplifier 16.

The coarse positioning of described each signalling channel controls assembly and is made up of four groups of switch matrix 17 and 35 power combiners 18; Described four groups of switch matrix are represented by A, B, C, D branch path; Described A branch switch matrix 17 includes 10 output ports, comprises 10 A antennas in corresponding four-tuple 12; Described B branch switch matrix includes 8 output ports, comprises 8 B antennas in corresponding four-tuple 12; Described C branch switch matrix includes 10 output ports, includes 10 C antennas in corresponding four-tuple 12; Described D branch switch matrix includes 7 output ports, includes 7 D antennas in corresponding four-tuple 12. The input port number of described power combiner 18 is corresponding with signalling channel number consistent, and namely power combiner 18 is four-in-one synthesizer.

In the Fine-precision control assembly of described each signalling channel, each subsequent leg all controls in assembly the corresponding connection of one group of switch matrix 17 with coarse positioning; The quantity of described power combiner 18 is equal with antenna 8 quantity on signal radiating curtain 7, and the outfan of power combiner 18 is connected with four-tuple 12 internal antenna 8 on signal radiating curtain 7.

The present invention controls the change of composite signal radiation center position by the control algolithm of a kind of target location control system, described target location control system is by the programmable attenuator 15 in control Fine-precision control assembly and program controlled phase shifter 14, thus changing amplitude and the phase place of four radiating element signals in corresponding four-tuple, and then control composite signal radiation center relative position in corresponding four-tuple, its principle is as follows:

As shown in Figure 4 with rotation of rotary table center for initial point 24, four Radiative antenna elements respectively A, B, C, D in four-tuple, their azimuth, position 25 and the angle of pitch 26 describe, respectively ��_i(i=1,2,3,4) andIf the operating frequency of four-tuple antenna A, B, C, D is identical, being ��, the electric feed signal amplitude of each antenna radiation unit is E_i' (i=1,2,3,4), phase place is �� respectively_i(i=1,2,3,4), then on tested device antenna opening diametric plane, the electric field of each unit radiation signal is respectively as follows:

A: $E_1=\frac{E_1^{\′}}{R_1}{e}^{j({\mathrm{\β}}_1-{\mathrm{kR}}_1)}\·e^{j\mathrm{\ω}t}=E_1^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_1-{\mathrm{kR}}_1)}$

B: $E_2=\frac{E_2^{\′}}{R_2}{e}^{j({\mathrm{\β}}_2-{\mathrm{kR}}_2)}\·e^{j\mathrm{\ω}t}=E_2^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_2-{\mathrm{kR}}_2)}$

C: $E_3=\frac{E_3^{\′}}{R_3}{e}^{j({\mathrm{\β}}_3-{\mathrm{kR}}_3)}\·e^{j\mathrm{\ω}t}=E_3^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_3-{\mathrm{kR}}_3)}---\left(1\right)$

D: $E_4=\frac{E_4^{\′}}{R_4}{e}^{j({\mathrm{\β}}_4-{\mathrm{kR}}_4)}\·e^{j\mathrm{\ω}t}=E_4^{\′\′}\·e^{j(\mathrm{\ω}t+{\mathrm{\β}}_4-{\mathrm{kR}}_4)}$

Wherein k=2 ��/�� is phase-shift constant, kR_iFor the phase contrast that transmission path produces. Above-mentioned electric field is represented by the electric field component of orientation and pitch orientation:

$E_{z_i}=E_i\·{\mathrm{sin\θ}}_i$

Then, total electric field is represented by

$E_z=\underset{i=1}{\overset{4}{\Σ}}{E}_{z_i}=\underset{i=1}{\overset{4}{\Σ}}{E}_i\·{\mathrm{sin\θ}}_i$

Can try to achieve synthesis rink corner degree is

$\mathrm{\θ}=atan\left(\frac{E_z}{\sqrt{{E_x}^2+{E_y}^2}}\right)=atan\left(\frac{\underset{i=1}{\overset{4}{\Σ}}{E}_{z_i}}{\sqrt{{\left(\underset{i=1}{\overset{4}{\Σ}}{E}_{x_i}\right)}^2+{\left(\underset{i=1}{\overset{4}{\Σ}}{E}_{y_i}\right)}^2}}\right)---\left(4\right)$

Formula (4) is called angle scintillations equation. When small angle approximation, and by phase compensation, formula (4) can be reduced to

$\mathrm{\θ}=atan\frac{\underset{i=1}{\overset{4}{\Σ}}{E}_i^{\′\′}\·{\mathrm{\θ}}_i}{\underset{i=1}{\overset{4}{\Σ}}{E}_i^{\′\′}}---\left(5\right)$

By formula (5) it can be seen that the position (azimuth and the angle of pitch) of known four-tuple, by controlling the amplitude E of four radiating element signals_i' (i=1,2,3,4) obtains E_i" (i=1,2,3,4) can change equivalent energy radiation center relative position in four-tuple, thus realizing Fine-precision control.

Meanwhile, described target location control system controls the break-make of assembly breaker in middle matrix 17 by controlling coarse positioning, thus changing composite signal radiation center to be in different four-tuple.

Under the control of target location control unit and array-fed system, described target location control system can obtain different test center positions, namely, in Hardware-in-loop Simulation Experimentation process, be could alter that the test center of composite signal by relevant control, as shown in Figure 5. There is single test center with spheric array, suitable in compared with small-sized tested device, planar array structure has the test center of flexibility and changeability, making it more adapt to the Hardware-in-loop Simulation Experimentation of large-scale tested device, especially under complex electromagnetic environment, the field such as measures of effectiveness test of large-scale tested device has more unrivaled advantage.

Above-mentioned novel target control system is applied in the measures of effectiveness test of large aircraft under complex electromagnetic environment as shown in Figure 6. During test, tested aircraft 10 whole machine installation is on turntable 9, the four-tuple antenna 8 installed in planar array 7 and discrete reception antenna receive the transmitting signal of diverse location equipment on tested aircraft 10, then under the control of master control 2, it is controlled by target location control unit 5 and array-fed system 6, by the four-tuple antenna 8 in planar array 7 to complex electromagnetic environment signals such as the echo signal needed for tested aircraft 10 radiation test, interference signals. Wherein the position of echo signal is controlled subsystem by Fine-precision control subsystem and coarse positioning and controls acquisition, the amplitude of four-tuple aerial radiation signal can be determined by the position of simulated target signal, and simulated target signal is produced with radio frequency source 3 by the radiofrequency signal control unit 2 in signal receiving unit 19.

Choosing of the unit interval of test distance and four-tuple can optimize design by control plane wave error, analyzes process as follows.

According to angle measuring principle it can be seen that the gradient direction of the electromagnetic wave that target apparent direction is target scattering that observes of reception antenna phase front on reception antenna bore face. Target location control system adopts four-tuple antenna array to carry out simulated target echo spatial parameter, and owing to four radiating elements produced electromagnetic field on reception antenna bore face is overlapped mutually, the phase front of this synthesis field is no longer a sphere, and is distorted. When reception antenna bore face, size cannot be ignored, and when being namely not to be regarded as a bit, due to the phase front distortion difference of synthesis field each point on antenna opening diametric plane, arrival bearing makes a mistake to cause reception antenna to judge, this error is called plane wave error. Below the mechanism of production of plane wave error is analyzed.

According to formula (1), it is left out phase factor e^j��t, on arrival tested device antenna opening diametric plane, the electric field intensity of each unit radiation signal is respectively

A: $E_1=\frac{E_1}{R_1}{e}^{j({\mathrm{\β}}_1-{\mathrm{kR}}_1)}$

B: $E_2=\frac{E_2^{\′}}{R_2}{e}^{j({\mathrm{\β}}_2-{\mathrm{kR}}_2)}$

C: $E_3=\frac{E_3^{\′}}{R_3}{e}^{j({\mathrm{\β}}_3-{\mathrm{kR}}_3)}---\left(6\right)$

D: $E_4=\frac{E_4^{\′}}{R_4}{e}^{j({\mathrm{\β}}_4-{\mathrm{kR}}_4)}$

Utilizing field superposition theorem, the total electric field strength that can obtain tested device Antenna aperture place is:

$\begin{array}{c}E(x,y,z)\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}{e}^{j({\mathrm{\β}}_i-{\mathrm{jkR}}_i)}\\ =\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}\cos ({\mathrm{\β}}_i-{\mathrm{kR}}_i)+j\frac{E_i^{\′}}{R_i}\sin ({\mathrm{\β}}_i-{\mathrm{kR}}_i)\\ =E_R+{\mathrm{jE}}_I\end{array}---\left(7\right)$

In formula:

Synthesis field real part: $E_R=\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}cos({\mathrm{\β}}_i-{\mathrm{kR}}_i)---\left(8\right)$

Synthesis field imaginary part: $E_I=\underset{i=1}{\overset{4}{\Σ}}\frac{E_i^{\′}}{R_i}sin({\mathrm{\β}}_i-{\mathrm{kR}}_i)---\left(9\right)$

Then synthesis field amplitude: $\left|E(x,y,z)\right|=\sqrt{E_R^2+E_I^2}---\left(10\right)$

Synthesis field phase: $\mathrm{\ψ}=atan\left(\frac{E_I}{E_R}\right)---\left(11\right)$

(x_i,y_i,z_i) it is the coordinate of active antenna, (x, y z) are the coordinate of tested device antenna.

By the caliber size of tested device antenna and test frequency, can calculate and obtain l-G simulation test distance, if this test distance is 35 meters, simultaneously according to the caliber size of tested device antenna and test frequency, the unit interval of four-tuple antenna is primarily determined that by engineering experience formula, it is set to 60mrad, operating frequency is 18GHz, according to above-mentioned computing formula (7)��(10), calculate amplitude distribution and the PHASE DISTRIBUTION of four-tuple antenna synthesis field, and with point source radiation antenna arrive tested device antenna radiation signal characteristic compare, the result of calculation obtained is as shown in Figure 7.

From result of calculation, in the test distances of 35 meters, 18GHz situation, when four-tuple antenna element separation is 60mrad, compared with the width phase distribution character of its composite signal is distributed mutually with the width of a source signal, there is beam splitting in the amplitude of composite signal, now it is difficult to obtain good precision by near-field effect error correction, it is therefore desirable to unit interval optimizes design further.

Other conditions are constant, only change unit interval so that it is be changed to 40mrad by 60mrad, and result of calculation is as shown in Figure 8. From result of calculation, in the test distances of 35 meters, 18GHz situation, when four-tuple antenna element separation is 40mrad, the width phase distribution character of its composite signal is distributed similar to the width of some source signal mutually, and is dull Changing Pattern, it does not have beam splitting, occur without many-valued, now can pass through near-field effect error correction and obtain good precision, thereby through the design of optimization Simulation pilot system, reach the high performance-price ratio that pilot system is built.

Based on above-mentioned analysis, above-mentioned synthesis field plane wave error is analyzed processing by the present invention by the error analysis method of a kind of target location control system, and the error control method of described target location control system comprises the steps:

1) according to the caliber size of tested device antenna in radio frequency Hardware-in-loop Simulation Experimentation and test frequency, Hardware-in-loop Simulation Experimentation distance is calculated;

2) simultaneously according to the caliber size of tested antenna and test frequency, engineering experience formula the unit interval between four-tuple antenna is primarily determined that in planar array;

3) target location control system is drawn up with above-mentioned l-G simulation test distance and unit interval for the total electric field amplitude wave-shape under condition and total electric field phase waveform by computer mould;

4) by the total electric field amplitude wave-shape that obtains in above-mentioned steps with total electric field phase waveform compared with point source signal waveform, if there is obvious beam splitting in composite signal waveform, then at l-G simulation test apart from constant, adjustment unit spacing, until total electric field waveform compared with point source signal waveform without obvious beam splitting;

5) four-tuple antenna uses the determined l-G simulation test distance of above-mentioned steps and unit interval, it is possible to simulation point source signal, and can the site error of composite signal be controlled in rational scope.

Embodiment 2

Target location control system of the present invention is applied in the radio frequency Hardware-in-loop Simulation Experimentation of large ship as shown in Figure 9. Described target location control system includes calibrating installation, radio frequency target simulation main control computer, radiofrequency signal control unit, radio frequency source, target location control unit, array-fed system and signal radiating curtain.

Described signal radiating curtain adopts planar array structure, and described signal radiating curtain is provided with 77 active antennas. Described planar array is made up of 60 four-tuple, and described four-tuple is made up of in planar array four adjacent active antennas.

The signalling channel of described feed system is 2 passages, wherein 1 echo signal passage, 1 interference signalling channel. The array-fed system of described each passage includes Fine-precision control assembly and controls assembly with coarse positioning. The Fine-precision control assembly of described each passage is made up of power divider 13 and four subsequent leg; Described every subsequent leg includes program controlled phase shifter 14, programmable attenuator 15, linear power amplifier 16.

The coarse positioning of described each passage controls assembly and is made up of four groups of switch matrix 17 and 77 power combiners 18; Described four groups of switch matrix 17 are represented by A, B, C, D branch path; Described A branch switch includes 21 output ports, comprises 21 A antennas in corresponding four-tuple 7; Described B branch switch includes 18 output ports, comprises 18 B antennas in corresponding four-tuple 7; Described C branch switch includes 21 output ports, includes 21 C antennas in corresponding four-tuple 7; Described D branch switch includes 17 output ports, includes 17 D antennas in corresponding four-tuple 7. The input port number of described power combiner 18 is corresponding with signalling channel number consistent, and namely power combiner is two-in-one synthesizer.

In described Fine-precision control assembly, each subsequent leg all controls in assembly the corresponding connection of one group of switch matrix 17 with coarse positioning; The outfan of described power combiner 18 is connected with the four-tuple antenna 8 on signal radiating curtain.

Fine-precision control principle is with embodiment 1, namely by controlling the amplitude E of four radiating element signals_i' (i=1,2,3,4) obtains E_i" (i=1,2,3,4), thus changing equivalent energy radiation center relative position in four-tuple.

Meanwhile, described target location control system controls the break-make of assembly breaker in middle matrix 17 by controlling coarse positioning, thus changing composite signal radiation center to be in different four-tuple.

During test, tested naval vessel entirety 10 is arranged on turntable, the four-tuple antenna 8 installed in planar array 10 and discrete reception antenna receive the transmitting signal of diverse location equipment on tested naval vessel 10, then under the control of main control computer 2, it is controlled by target location control unit 5 and array-fed system 6, radiates the complex electromagnetic environment signals such as the required echo signal of 10 tests, interference signal to tested naval vessel by the four-tuple antenna 8 in planar array 7.Wherein the position of echo signal is controlled subsystem by Fine-precision control subsystem and coarse positioning and controls acquisition, the amplitude of four-tuple aerial radiation signal can be determined by the position of simulated target signal, and simulated target signal is produced with radio frequency source 3 by the radiofrequency signal control unit 2 in signal receiving unit 19. Test distance and unit interval can optimize design by calculating, and the principle of optimality, plane wave error control step are identical with enforcement 1. All the other features of the present embodiment and advantage are identical with embodiment 1.

Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned embodiment, also includes the technical scheme being made up of above technical characteristic combination in any.

Claims (7)

1. a target location control system, including calibrating installation, radio frequency target simulation main control computer, radiofrequency signal control unit, radio frequency source, target location control unit, array-fed system, and signal radiating curtain, it is characterized in that, described array-fed system includes multiple signal channels; Each signalling channel in multiple signal channels all includes Fine-precision control assembly and controls assembly with coarse positioning; Described signal radiating curtain is provided with multiple active antenna; Described signal radiating curtain adopts planar array structure; Described planar array is made up of multiple four-tuple, and described four-tuple is made up of in planar array four adjacent active antennas.

2. the target location control system described in claim 1, it is characterised in that the Fine-precision control assembly in described each signalling channel is made up of power divider and four subsequent leg; Described subsequent leg includes program controlled phase shifter, programmable attenuator, linear power amplifier.

3. the target location control system described in claim 1, it is characterised in that the coarse positioning in described each signalling channel controls assembly and is made up of four groups of switch matrix and multiple power combiners; Often group switch matrix includes multiple output port; Described coarse positioning controls each output port of four groups of switch matrix in assembly and is all connected with the corresponding input of power combiner; The outfan of described power combiner is connected with the four-tuple internal antenna on signal radiating curtain.

4. the target location control system described in any one in claim 1,2,3, it is characterised in that in described Fine-precision control assembly, each subsequent leg all controls in assembly the corresponding connection of one group of switch matrix with coarse positioning.

5. the control algolithm of the target location control system described in claim 1, it is characterized in that, described target location control system is by the programmable attenuator in control Fine-precision control assembly and program controlled phase shifter, change amplitude and the phase place of four active antenna signals in corresponding four-tuple, and then control composite signal radiation center relative position in corresponding four-tuple.

6. the control algolithm of the target location control system described in claim 5, it is characterised in that described target location control system controls the break-make of assembly breaker in middle matrix by controlling coarse positioning, changes composite signal radiation center and is in different four-tuple.

7. the error analysis method of a target location control system, it is characterised in that the error control method of described target location control system comprises the steps:

1) according to the caliber size of tested device antenna in radio frequency Hardware-in-loop Simulation Experimentation and test frequency, Hardware-in-loop Simulation Experimentation distance is calculated;

2) simultaneously according to the caliber size of tested device antenna and test frequency, engineering experience formula the unit interval between four-tuple antenna is primarily determined that in planar array;

3) target location control system is drawn up with above-mentioned l-G simulation test distance and unit interval for the total electric field amplitude wave-shape under condition and total electric field phase waveform by computer mould;

4) by the total electric field amplitude wave-shape that obtains in above-mentioned steps with total electric field phase waveform compared with point source signal waveform, if there is obvious beam splitting in composite signal waveform, then at l-G simulation test apart from constant, adjustment unit spacing, until total electric field waveform compared with point source signal waveform without obvious beam splitting;

5) four-tuple antenna uses the determined l-G simulation test distance of above-mentioned steps and unit interval, it is possible to simulation point source signal, and can the site error of composite signal be controlled in rational scope.