阅读说明：本技术 一种相干多点源弹载干扰方法 (Coherent multi-point source missile-borne interference method ) 是由 赵忠凯 李泽 刘鲁涛 刘俊杰 陈�光 于 2021-09-01 设计创作，主要内容包括：本发明属于雷达干扰技术领域,具体涉及一种相干多点源弹载干扰方法。本发明采用了三元组干扰机,三元组中各干扰天线的幅度和相位共6个可调参数共同决定了等效散射点的位置；天线布局由二维变成三维,使得等效散射点的分布范围也得到极大的扩充,可在360°任意方位进行假目标的合成,更有利于提高干扰效果和增大的欺骗角度；同时飞行器无论如何转动,三元组干扰都不存在干扰盲区；由单一的角度干扰模式变为轨迹欺骗、压制干扰等多种干扰模式,提高了干扰效果和灵活性。本发明可以有效对单脉冲测角雷达实施干扰,为狭小空间载体、小型无人机等小型飞行载体突防提供有效的防护措施,为三元组干扰技术的应用提供支撑。(The invention belongs to the technical field of radar interference, and particularly relates to a coherent multi-point source missile-borne interference method. The invention adopts a triple interference unit, and the amplitude and phase of each interference antenna in the triple jointly determine the position of an equivalent scattering point by 6 adjustable parameters; the antenna layout is changed from two dimensions to three dimensions, so that the distribution range of equivalent scattering points is greatly expanded, a false target can be synthesized in any 360-degree direction, and the interference effect and the increased deception angle can be improved; meanwhile, no matter how the aircraft rotates, the triple interference has no interference blind area; the single angle interference mode is changed into a plurality of interference modes such as track deception and interference suppression, and the interference effect and flexibility are improved. The method can effectively interfere the monopulse angle measuring radar, provides effective protective measures for the small flying carrier such as a narrow space carrier and a small unmanned aerial vehicle for sudden defense, and provides support for the application of a triple interference technology.)

1. A coherent multi-point source missile-borne interference method is characterized by comprising the following steps:

step 1: acquiring a detection signal of a target monopulse radar through a triple jammer;

the triple interference unit adopts three interference antennas which are distributed in a regular triangle to form a triple interference structure;

step 2: analyzing parameter information of the target monopulse radar, and selecting an interference mode;

the first mode is as follows: changing the amplitude and phase parameters of the three interference antennas, controlling the vector to synthesize a false target point to generate different positions, generating a decoy trajectory graph of the false target, and performing false target trajectory deception interference on the target monopulse radar;

and a second mode: increasing the pulse emission frequency of the triple interference unit, generating a plurality of vector synthesis false target points which are distributed irregularly, causing multi-false-target suppression interference to a target monopulse radar, and suppressing a radar exposure area;

and a third mode: controlling the amplitude ratio and the phase difference of the three interference antennas to generate a triple maximum angle error approximate to cross-eye interference, and performing angle deception interference on the target monopulse radar to enable the target monopulse radar to point away from the triple jammer;

the azimuth indication angle of the target monopulse radar is as follows:

wherein the content of the first and second substances,respectively an azimuth angle and an opening angle of the interference antenna; alpha and beta are the amplitude ratio of interference signals of the second interference antenna and the third interference antenna relative to the first interference antenna in the direction of the monopulse radar; delta₁₂、δ₁₃Phase differences of the second interference antenna and the third interference antenna relative to the first interference antenna respectively;the actual angle information of the triple jammers is obtained;is a triplet of azimuthal gain coefficients toRepresenting the triad azimuth gain:

the triplet gain expression can be further expanded to:

when the amplitude ratio of the three interference antennas is approximately 1, the phase difference is approximately 120 degrees in pairs, namely delta₁₂＝120°，δ₁₃240 ° or δ₁₂＝240°，δ₁₃When the triple interference is 120 degrees, the triple gain reaches the maximum value, so that the maximum angle error of the triple interference is generated, and the target monopulse radar cannot lock the real information of the triple interference machine;

the distance between a false target generated by the triple interference machine and the real central point of the triple interference machine in the azimuth directionComprises the following steps:

wherein r is the distance from the antenna center of the target monopulse radar to the center of the triple jammer, namely the interference distance;

the correlation formula of the pitch angle is the same as the azimuth angle, and if theta is the pitch angle, the total distance d between a false target generated by the triple interference machine and the real central point of the triple interference machine_totalComprises the following steps:

therefore, when the interference distance is constant, the distance between the false target point and the real central point of the triple jammer depends on the gain of the triple, so that the maximum triple angle error approximate to cross-eye interference can be generated by controlling the amplitude ratio of the three antennas to be approximately 1 and the phase difference to be approximately 120 degrees, angle deception interference is carried out on the target monopulse radar, and the target monopulse radar cannot lock the real information of the triple jammer;

and step 3: generating corresponding program control parameters according to the selected interference mode, and generating an interference signal to enable the target monopulse radar to be incapable of identifying the real information of the triple interference machine; in the flying motion, when the relative position of the triple jammers and the target monopulse radar is changed, the triple jammers calculate the data of the target monopulse radar in real time and adjust the interference mode or the position of the false target in real time.

Technical Field

The invention belongs to the technical field of radar interference, and particularly relates to a coherent multi-point source missile-borne interference method.

Background

The monopulse radar is widely applied by virtue of excellent anti-interference capability and accurate angle measurement technology. Coherent multi-point source interference is an electronic protection technology, and wave front distortion is generated on a transmitting signal by controlling the amplitude and phase relation among antenna signals, so that monopulse radar can be effectively resisted. The interference pattern of the monopulse radar can be mainly divided into incoherent interference and coherent interference, wherein cross-eye interference in the coherent interference is considered as the most effective interference pattern of the interference monopulse radar. However, the cross-eye jammer has a limited degree of freedom, and can optimize the interference performance only by adjusting the amplitude ratio and the phase difference between the two interfering antennas, so that the resulting wavefront distortion width is small, and an equivalent false target can be generated only in a certain range on the connection line of the two antennas. The requirement of the cross-eye interference system on parameter tolerance is strict, and the interference effect of the cross-eye interference can be influenced by small phase change, so that the cross-eye interference is greatly limited in practical application, and therefore, a new interference technology for searching higher freedom degree and wider parameter tolerance is very urgent.

The cross-eye interference technology is mainly applied to carriers such as large airplanes, ships or ground radars at the present stage, and the larger application carrier can provide longer interference base length, so that the interference effect of cross-eye interference is guaranteed. However, small application platforms such as small unmanned aerial vehicles cannot provide enough interference baseline arrangement space, and the cross-eye interference technology has a relatively strict parameter tolerance, so that an effective interference effect cannot be provided.

Disclosure of Invention

The invention aims to solve the problem that a limited single-pulse radar interference method cannot be realized by a carrier in a narrow space, and provides a coherent multi-point source missile-borne interference method.

The purpose of the invention is realized by the following technical scheme: the method comprises the following steps:

step 1: acquiring a detection signal of a target monopulse radar through a triple jammer;

the triple interference unit adopts three interference antennas which are distributed in a regular triangle to form a triple interference structure;

step 2: analyzing parameter information of the target monopulse radar, and selecting an interference mode;

the first mode is as follows: changing the amplitude and phase parameters of the three interference antennas, controlling the vector to synthesize a false target point to generate different positions, generating a decoy trajectory graph of the false target, and performing false target trajectory deception interference on the target monopulse radar;

and a second mode: increasing the pulse emission frequency of the triple interference unit, generating a plurality of vector synthesis false target points which are distributed irregularly, causing multi-false-target suppression interference to a target monopulse radar, and suppressing a radar exposure area;

and a third mode: controlling the amplitude ratio and the phase difference of the three interference antennas to generate a triple maximum angle error approximate to cross-eye interference, and performing angle deception interference on the target monopulse radar to enable the target monopulse radar to point away from the triple jammer;

the azimuth indication angle of the target monopulse radar is as follows:

wherein the content of the first and second substances,respectively an azimuth angle and an opening angle of the interference antenna; alpha and beta are the amplitude ratio of interference signals of the second interference antenna and the third interference antenna relative to the first interference antenna in the direction of the monopulse radar; delta₁₂、δ₁₃Phase differences of the second interference antenna and the third interference antenna relative to the first interference antenna respectively;the actual angle information of the triple jammers is obtained;is a triplet of azimuthal gain coefficients toRepresenting the triad azimuth gain:

the triplet gain expression can be further expanded to:

when the amplitude ratio of the three interference antennas is approximately 1, the phase difference is approximately 120 degrees in pairs, namely delta₁₂＝120°，δ₁₃240 ° or δ₁₂＝240°，δ₁₃When the triple interference is 120 degrees, the triple gain reaches the maximum value, so that the maximum angle error of the triple interference is generated, and the target monopulse radar cannot lock the real information of the triple interference machine;

the distance between a false target generated by the triple interference machine and the real central point of the triple interference machine in the azimuth directionComprises the following steps:

wherein r is the distance from the antenna center of the target monopulse radar to the center of the triple jammer, namely the interference distance;

the correlation formula of the pitch angle is the same as the azimuth angle, and if theta is the pitch angle, the total distance d between a false target generated by the triple interference machine and the real central point of the triple interference machine_totalComprises the following steps:

therefore, when the interference distance is constant, the distance between the false target point and the real central point of the triple jammer depends on the gain of the triple, so that the maximum triple angle error approximate to cross-eye interference can be generated by controlling the amplitude ratio of the three antennas to be approximately 1 and the phase difference to be approximately 120 degrees, angle deception interference is carried out on the target monopulse radar, and the target monopulse radar cannot lock the real information of the triple jammer;

and step 3: generating corresponding program control parameters according to the selected interference mode, and generating an interference signal to enable the target monopulse radar to be incapable of identifying the real information of the triple interference machine; in the flying motion, when the relative position of the triple jammers and the target monopulse radar is changed, the triple jammers calculate the data of the target monopulse radar in real time and adjust the interference mode or the position of the false target in real time.

The invention has the beneficial effects that:

aiming at small flying carriers such as small space carriers and small unmanned aerial vehicles, the invention can make up the defects of limited interference, strict parameter tolerance, single interference form and blind area of interference on the small flying carriers caused by cross eye interference. The triple interference unit is adopted, controllable variables are increased due to the addition of the antennas, the degree of freedom of an interference system is greatly improved, and the position of an equivalent scattering point is determined by 6 adjustable parameters including the amplitude and the phase of each interference antenna in the triple; the antenna layout is changed from two dimensions to three dimensions, so that the distribution range of equivalent scattering points is greatly expanded, cross-eye interference can only generate false targets on the connection line of two interference sources, triple interference can synthesize the false targets in any direction of 360 degrees, and the interference effect and the increased deception angle are improved; compared with cross eye interference, no matter how large the rotation angle of the platform is, namely, no matter how the aircraft rotates, the triple interference has no interference blind area; the single angle interference mode is changed into a plurality of interference modes such as track deception and interference suppression, and the interference effect and flexibility are improved. The method can effectively interfere the monopulse angle measuring radar, provides effective protective measures for the small flying carrier such as a narrow space carrier and a small unmanned aerial vehicle for sudden defense, and provides support for the application of a triple interference technology. According to the simulation result, the coherent multi-point source missile-borne interference method can form effective interference on the monopulse angle measuring radar, effectively improves the penetration resistance and the survival capability of the aircraft, and has important engineering application value.

Drawings

FIG. 1 is a flow chart of the present invention.

Fig. 2 is a schematic front cross-sectional view of a triple jammer.

Fig. 3 is a schematic diagram of a scenario in which a triple jammer interferes with a monopulse radar.

FIG. 4 is a scatter plot of a synthetic decoy of a triplet interference machine.

Fig. 5 is a schematic diagram of the spoofing trajectory of the triplet jammer synthetic decoy.

Fig. 6 is a graph showing the relationship between the phase difference between the triple interfering antenna 1 and the antenna 2 and the interference distance generated by the enemy radar.

Fig. 7 is a plot of the amplitude ratio of the triplets of interfering antennas 1 and 2 versus the distance of interference from an enemy radar.

Detailed Description

The invention is further described below with reference to the accompanying drawings.

The invention provides a coherent multi-point source missile-borne interference method, which is mainly used for solving the problem that a small flight carrier cannot realize a limited single-pulse radar interference method. In order to overcome the limitation of the prior cross eye technology, the invention adopts a novel coherent multi-point source interference structure, namely a triple structure, improves the degree of freedom of interference, reduces the defects of harsh parameter tolerance, increased interference form and blind area of interference by increasing the number of antennas, can obtain larger interference gain than the traditional cross eye interference, and reduces the requirement on the parameter tolerance.

The invention adopts three Archimedes spiral antennas distributed in a regular triangle to form a triple interference structure, and performs coherent multipoint source interference on the front surface of a projectile body in a narrow space of the projectile body, and the purpose of the invention is realized mainly by the following steps:

step one, in order to ensure higher isolation and better interference effect between interference antennas, an Archimedes spiral antenna is adopted as a triple interference antenna. The Archimedes spiral antenna has an ultra-wide frequency band, has a stable directional diagram, an axial ratio and input impedance on the frequency band, has a good radiation directional diagram, can realize a good ultra-wide band circular polarization effect, and is convenient to embed due to a small size.

And step two, in the sudden defense stage of the small-sized flight carrier with the triple jammers, the target monopulse radar to be interfered transmits electromagnetic wave detection signals to irradiate the small-sized flight carrier in the front view direction, the triple jammers receive the detection signals of the target monopulse radar to be interfered and analyze the detection signals to obtain the relevant parameter information of the target monopulse radar to be interfered, and then the triple jammers interfere the relevant parameter information.

And step three, analyzing parameter data of the target monopulse radar to be interfered by the triple jammer, selecting different interference modes according to different data, generating corresponding program control parameters, and generating interference signals to enable the target monopulse radar to be interfered to be incapable of identifying real targets. The relevant parameter information of the target monopulse radar to be interfered comprises the position, frequency, incident angle, power and the like of a radar signal. In the flying motion, the relative position of a small flying carrier carrying a triple jammer and a target monopulse radar to be interfered is changed, the triple jammer carries out real-time calculation on data of the target monopulse radar to be interfered, the obtained relevant parameter information of the target monopulse radar to be interfered is also changed in real time, and the interference mode or the position of a false target is adjusted in real time according to the change of the space relative position of the small flying carrier and the target monopulse radar to be interfered.

And step four, the triple jammer transmits an interference signal to synthesize a false target in the space by calling the generated program control parameter, so as to interfere the target monopulse radar. The triple jammer controls the position of a vector synthesis point by controlling the amplitude and phase parameters of the three antennas, so as to achieve the purpose of jamming the monopulse radar. And generating a false target generated by the triple interference machine on a specified target point by generating corresponding program control parameters. Meanwhile, false target echoes sent by the triple jammers and detected by the target monopulse radar to be interfered have the same electromagnetic characteristics as those of the small-sized flight carrier.

Specifically, three interference modes can be classified.

The first mode is as follows: by changing the amplitude and phase parameters of the three antennas, the vector synthesis false target points are controlled to be generated at different positions, a decoy trajectory diagram of a false target is generated, and false target trajectory deception jamming is performed on the target monopulse radar to be interfered.

And a second mode: the interference suppression method can generate a plurality of vector synthesis false target points which are distributed irregularly in a certain interference range by improving the pulse transmitting frequency of the interference machine, suppress interference of a plurality of false targets caused by a target monopulse radar to be interfered, and suppress radar exposure areas.

And a third mode: the triple maximum angle error approximate to cross-eye interference is generated by controlling the amplitude ratio and the phase difference of the three antennas, and angle deception interference is carried out on the target monopulse radar to be interfered so that the monopulse radar points to deviate from the target.

For monopulse radar, the three-tuple jammer interference can be divided into azimuth and pitch angles. The azimuth indication angle of the monopulse radar is as follows:

in the formulaRespectively, the azimuth opening angle of the interference antenna, and α and β are the interference signal amplitude ratio of the interference antennas 2 and 3 relative to the interference antenna 1 in the monopulse radar direction. Delta₁₂,δ₁₃The phase difference of the interfering antennas 2,3, respectively, with respect to the antenna 1. First item on the right of equal sign of the above formulaFor the target true angle information, the second term is the triple azimuth gain:

the triplet gain expression can be further expanded to:

when the amplitude ratio of the three antennas is approximately 1, the phase difference is approximately 120 degrees in pairs, namely delta₁₂＝120°，δ₁₃240 ° or δ₁₂＝240°，δ₁₃When the triple gain reaches the maximum value 120 degrees, the maximum angle error of triple interference is generated, and the target monopulse radar to be interfered cannot lock the real target information of the small-sized flight carrier.

The distance between a false target generated by the triple interference and the central point of the real target of the small-sized flight carrier in the azimuth direction is

In the same way, the correlation formula of the pitch angle is the same as the azimuth angle, and theta is set as the pitch angle. The total distance between the false target generated by the triple interference and the real target central point of the small-sized flight carrier is

It is thus seen that the distance between the false target point and the real target center point of the small flying carrier depends on the size of the triplet gain when the interference distance is constant. Therefore, the triple maximum angle error approximate to cross-eye interference can be generated by controlling the amplitude ratio of the three antennas to be approximate to 1 and the phase difference to be approximate to 120 degrees, angle deception interference is carried out on the target monopulse radar to be interfered, and the target monopulse radar to be interfered can not lock real target information of the small-sized flight carrier.

Compared with the prior art, the invention can overcome the defects of limited interference, strict parameter tolerance, single interference form and blind area of interference on the small flying carrier caused by cross-eye interference aiming at small flying carriers such as small space carriers, small unmanned aerial vehicles and the like. The triple interference system has the advantages that controllable variables are increased due to the fact that the antennas are added, the degree of freedom of the interference system is greatly improved, and the position of an equivalent scattering point is determined by 6 adjustable parameters including the amplitude and the phase of each interference antenna in the triple; the antenna layout is changed from two dimensions to three dimensions, so that the distribution range of equivalent scattering points is greatly expanded, cross-eye interference can only generate false targets on the connection line of two interference sources, triple interference can synthesize the false targets in any direction of 360 degrees, and the interference effect and the increased deception angle are improved; compared with cross eye interference, no matter how large the rotation angle of the platform is, namely, no matter how the aircraft rotates, the triple interference has no interference blind area; the single angle interference mode is changed into a plurality of interference modes such as track deception and interference suppression, and the interference effect and flexibility are improved.

The method can effectively interfere the monopulse angle measuring radar, provides effective protective measures for the small flying carrier such as a narrow space carrier and a small unmanned aerial vehicle for sudden defense, and provides support for the application of a triple interference technology. According to the simulation result, the coherent multi-point source missile-borne interference method can form effective interference on the monopulse angle measuring radar, effectively improves the penetration resistance and the survival capability of the aircraft, and has important engineering application value.

Example 1:

as shown in fig. 1 to 7, the present invention is a coherent multi-point source missile-borne interference method, which adopts three archimedes spiral antennas distributed in a regular triangle to form a triple interference structure, and performs coherent multi-point source interference on the front surface of a projectile body in a small space of the projectile body, wherein the purpose of the method mainly comprises the following steps:

step one, in order to ensure higher isolation and better interference effect between interference antennas, an Archimedes spiral antenna is adopted as a triple interference antenna. The Archimedes spiral antenna has an ultra-wide frequency band, has a stable directional diagram, an axial ratio and input impedance on the frequency band, has a good radiation directional diagram, can realize a good ultra-wide band circular polarization effect, and is convenient to embed due to a small size.

And step two, in the sudden defense stage of the small-sized flight carrier, the target monopulse radar to be interfered transmits an electromagnetic wave detection signal to irradiate the front view direction of the small-sized flight carrier, the triple jammer receives the detection signal of the target monopulse radar to be interfered and analyzes the detection signal to obtain the relevant parameter information of the target monopulse radar to be interfered, and then the triple jammer interferes the target monopulse radar to be interfered.

Fig. 2 is a schematic front cross-sectional view of a missile-borne triple jammer. The jammer is formed by 3 antenna array elements, and 3 antenna array elements are the equilateral triangle structure. r is the distance from the center of the radar antenna to the center of the jammer, namely the interference distance; d_pIs a phase comparison monopulse radar antenna aperture

And step three, analyzing parameter data of the target monopulse radar to be interfered by the triple jammer, selecting different interference modes according to different data, generating corresponding program control parameters, and generating interference signals to enable the target monopulse radar to be interfered to be incapable of identifying real targets. The relevant parameter information of the target monopulse radar to be interfered comprises the position, frequency, incident angle, power and the like of a radar signal. In the flying motion, the relative position of the small flying carrier and a target monopulse radar to be interfered is changed, the triple jammer carries out real-time calculation on the data of the target monopulse radar to be interfered, the obtained relevant parameter information of the target monopulse radar to be interfered is also changed in real time, and the interference mode or the false target position is adjusted in real time according to the change of the relative position of the small flying carrier and the target monopulse radar to be interfered.

And step four, the triple interference system transmits an interference signal to synthesize a false target in the space by calling the generated program control parameter, so as to interfere the target monopulse radar to be interfered. As shown in fig. 4, a scatter point distribution diagram of a decoy is synthesized for a triplet jammer. The triple interference system controls the position of a vector synthesis point by controlling the amplitude and phase parameters of the three antennas, so as to achieve the purpose of interfering the monopulse radar. And generating a false target generated by the triple interference machine on a specified target point by generating corresponding program control parameters. Meanwhile, false target echoes sent by the triple jammers and detected by the target monopulse radar to be interfered have the same electromagnetic characteristics as those of the small-sized flight carrier.

Specifically, three interference modes can be classified.

The first mode is as follows: by changing the amplitude and phase parameters of the three antennas, the vector synthesis false target points are controlled to be generated at different positions, a decoy trajectory diagram of a false target is generated, and false target trajectory deception jamming is performed on the target monopulse radar to be interfered, as shown in fig. 5.

And a second mode: by increasing the pulse transmitting frequency of the jammer, a plurality of vector synthesis false target points which are distributed irregularly are generated in a certain interference range, the target monopulse radar to be interfered causes multiple false targets to suppress interference, and the radar exposure area is suppressed, as shown in fig. 4.

And a third mode: the triple maximum angle error approximate to cross-eye interference is generated by controlling the amplitude ratio and the phase difference of the three antennas, and angle deception interference is carried out on the target monopulse radar to be interfered so that the monopulse radar points to deviate from the target.

For monopulse radar, the three-tuple jammer interference can be divided into azimuth and pitch angles. The azimuth indication angle of the monopulse radar is as follows:

in the formulaRespectively, the azimuth opening angle of the interference antenna, and α and β are the interference signal amplitude ratio of the interference antennas 2 and 3 relative to the interference antenna 1 in the monopulse radar direction. Delta₁₂,δ₁₃The phase difference of the interfering antennas 2,3, respectively, with respect to the antenna 1. First item on the right of equal sign of the above formulaFor the target true angle information, the second term is the triple azimuth gain:

the triplet gain expression can be further expanded to:

when the amplitude ratio of the three antennas is approximately 1, the phase difference is approximately 120 degrees in pairs, namely delta₁₂＝120°，δ₁₃240 ° or δ₁₂＝240°，δ₁₃When the triple gain reaches the maximum value 120 degrees, the maximum angle error of triple interference is generated, and the target monopulse radar to be interfered cannot lock the real target information of the small-sized flight carrier.

The distance between a false target generated by the triple interference and the central point of the real target of the small-sized flight carrier in the azimuth direction is

In the same way, the correlation formula of the pitch angle is the same as the azimuth angle, and theta is set as the pitch angle. The total distance between the false target generated by the triple interference and the real target central point of the small-sized flight carrier is

It is thus seen that at a given interference distance, the magnitude of the distance between the decoy point and the projectile depends on the magnitude of the triplet gain. Therefore, the triple maximum angle error approximate to cross-eye interference can be generated by controlling the amplitude ratio of the three antennas to be approximate to 1 and the phase difference to be approximate to 120 degrees, angle deception interference is carried out on the target monopulse radar to be interfered, and the target monopulse radar to be interfered can not lock real target information of the small-sized flight carrier.

In order to facilitate the practical application of the triple jammer, if the diameter of an aircraft of a small-sized flight carrier is 1m, the distance between antennas for installing the triple jammer is 0.866m, the distance r between a radar and the jammer is 1km, the plane rotation angles of the radar and the jammer are 0, and the relationship between the jamming distance generated by the triple jammer and the amplitude phase parameter of the jammer antenna is simulated. Fig. 6 is a relation curve between the phase difference between the triple interfering antenna 1 and the antenna 2 and the interference distance generated by the target monopulse radar to be interfered when the amplitude ratio and the phase difference parameter of the triple interfering antenna 2 and the antenna 3 are common values. Fig. 7 is a relationship curve between the amplitude ratio of the triple interfering antenna 1 and the antenna 2 and the interference distance generated by the target monopulse radar to be interfered when the amplitude ratio and the phase difference parameter of the triple interfering antenna 2 and the antenna 3 are common values. As can be seen from fig. 6, the phase difference between the triad of interfering antennas 1 and 2 is in the range of (110 °,130 °), and the interference distances are substantially all above 20m, 20 times the diameter of the aircraft. The phase difference between the triad interference antenna 1 and the antenna 2 is within a range of (105 degrees and 135 degrees), and the interference distance is basically more than 10m and is 10 times of the diameter of the aircraft. As can be seen from fig. 7, the amplitude ratio between the triad interference antenna 1 and the antenna 2 is within the range of (0.9,1.1), the interference distance is substantially above 20m, which is 20 times the diameter of the aircraft, and the amplitude ratio between the triad interference antenna 1 and the antenna 2 is within the range of (0.8,1.2), and the interference distance is substantially above 10m, which is 10 times the diameter of the aircraft. Such a disturbance distance is very significant for an aircraft with a diameter of 1 m.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.