CN113238223B - Anti-stealth radar, aircraft detection method and device - Google Patents
Anti-stealth radar, aircraft detection method and device Download PDFInfo
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- CN113238223B CN113238223B CN202110566421.0A CN202110566421A CN113238223B CN 113238223 B CN113238223 B CN 113238223B CN 202110566421 A CN202110566421 A CN 202110566421A CN 113238223 B CN113238223 B CN 113238223B
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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
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/887—Radar or analogous systems specially adapted for specific applications for detection of concealed objects, e.g. contraband or weapons
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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
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
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Abstract
The invention discloses an anti-stealth radar, which comprises a gravitational field detection assembly and a processor; the gravitational field detection assembly comprises a bar magnet and two magnetic induction elements, and the induction surfaces of the two magnetic induction elements face the same side surface of the bar magnet; the processor is connected with the magnetic induction elements and is used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft azimuth information according to the voltage signals and determining aircraft position information according to the aircraft azimuth information; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element. The anti-stealth radar provided by the invention utilizes the gravity field of the aircraft to detect, and has excellent concealment. The invention also provides an aircraft detection method and device with the beneficial effects, and a computer readable storage medium.
Description
Technical Field
The invention relates to the field of space mapping, in particular to an anti-stealth radar, an aircraft detection method, an aircraft detection device and a computer readable storage medium.
Background
With the development of science, people gradually send various aerospace equipment into high altitude, however, in order to avoid air accidents or territory safety, the requirement for timely mastering the position of an aircraft is also increasing, namely, the requirement of people on radar performance is higher.
The existing radar is usually an active electromagnetic wave radar, and aiming at the electromagnetic wave radar, a mature magnetic coating exists in the prior art, and the magnetic coating can be used for absorbing the radar to actively emit electromagnetic waves, so that the stealth effect on the electromagnetic waves with any frequency can be realized theoretically. Accordingly, in order to find a stealth target, the conventional electromagnetic wave radar can only detect the stealth target by increasing the power of electromagnetic waves so that the stealth coating reaches 'magnetic saturation'. Increasing the electromagnetic wave power in turn increases the likelihood of the radar being attacked.
Therefore, how to perform "anti-stealth" detection on the aircraft while ensuring the stealth of the own radar becomes a problem to be solved by those skilled in the art.
Disclosure of Invention
The invention aims to provide an anti-stealth radar, an aircraft detection method, an aircraft detection device and a computer readable storage medium, so as to solve the problem that the anti-stealth radar cannot be hidden on the premise of realizing self-concealment in the prior art.
In order to solve the technical problems, the invention provides an anti-stealth radar which comprises a gravitational field detection component and a processor;
The gravitational field detection assembly comprises a bar magnet and two magnetic induction elements, and the induction surfaces of the two magnetic induction elements face the same side surface of the bar magnet;
The two magnetic induction elements are symmetrically arranged at the N-terminal and the S-terminal of the strip magnet; wherein the 0 magnetic point of the bar magnet is the symmetry axes of the two magnetic induction elements;
The processor is connected with the magnetic induction elements and is used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft azimuth information according to the voltage signals and determining aircraft position information according to the aircraft azimuth information; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element.
Optionally, in the anti-stealth radar, the long axis of the bar magnet rotates in a horizontal direction, and when the voltage signals from the two magnetic induction elements are equal in magnitude, the aircraft azimuth information is determined according to the direction of the long axis of the bar magnet.
Optionally, in the anti-stealth radar, the anti-stealth radar includes a plurality of gravitational field detection components with different setting positions.
Optionally, in the anti-stealth radar, the gravitational field detection assembly is disposed at different heights;
The processor is used for determining the aircraft azimuth information according to voltage signals generated by different gravitational field detection components; denoising the voltage signal according to the preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of each gravitational field detection assembly corresponding to the aircraft; and determining the aircraft position information according to the aircraft azimuth information and the distance information.
Optionally, in the anti-stealth radar, the gravitational field detection assembly further includes a differential amplifier;
The differential amplifier is used for determining unidirectional voltage signals according to the voltage signals sent by the two magnetic induction elements;
the processor determines the distance information from the unidirectional voltage signal.
Optionally, in the anti-stealth radar, the anti-stealth radar further includes an amplifying circuit;
The amplifying circuit is used for amplifying the electric signal between the gravitational field detection component and the processor.
Optionally, in the anti-stealth radar, the magnetic induction element is a linear hall element.
An aircraft detection method, comprising:
Acquiring a voltage signal from a gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet and two magnetic induction elements, and the induction surfaces of the two magnetic induction elements face the same side surface of the bar magnet; the two magnetic induction elements are symmetrically arranged at the N-terminal and the S-terminal of the strip magnet; wherein the 0 magnetic point of the bar magnet is the symmetry axes of the two magnetic induction elements; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element;
Determining aircraft azimuth information from the voltage signal;
And determining the position information of the aircraft according to the position information of the aircraft.
Optionally, in the aircraft detection method, the determining the aircraft azimuth information according to the voltage signal includes:
and when the voltage signals from the two magnetic induction elements are equal in magnitude, determining the aircraft azimuth information according to the direction of the long axis of the bar magnet.
Optionally, in the aircraft detection method, the determining the aircraft position information according to the aircraft azimuth information includes:
When a plurality of gravitational field detection assemblies exist and are arranged at different heights, denoising the voltage signals according to the preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain the distance information of the aircraft corresponding to each gravitational field detection assembly;
And determining the position information of the aircraft according to the azimuth information and the distance information of the aircraft. An aircraft detection device comprising:
The acquisition module is used for acquiring a voltage signal from the gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet and two magnetic induction elements; the two magnetic induction elements are arranged at the N-terminal and the S-terminal of the bar magnet in an axisymmetric way by taking the middle position of the 0 magnetic point of the bar magnet as an axis; the induction surfaces of the two magnetic induction elements face the same side surface of the strip-shaped magnet; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element;
The azimuth module is used for determining aircraft azimuth information according to the voltage signals;
and the positioning module is used for determining the position information of the aircraft according to the position information of the aircraft.
A computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of an aircraft detection method as described in any of the preceding claims.
The anti-stealth radar provided by the invention comprises a gravitational field detection component and a processor; the gravitational field detection assembly comprises a bar magnet and two magnetic induction elements, and the induction surfaces of the two magnetic induction elements face the same side surface of the bar magnet; the two magnetic induction elements are symmetrically arranged at the N-terminal and the S-terminal of the strip magnet; wherein the 0 magnetic point of the bar magnet is the symmetry axes of the two magnetic induction elements; the processor is connected with the magnetic induction elements and is used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft azimuth information according to the voltage signals and determining aircraft position information according to the aircraft azimuth information; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element.
The magnetic field is a spatial motion. The geometric mean and the arithmetic mean of the space movement process are unequal, so that the density of the space is changed, the gravitational field shows unidirectional magnetic characteristics under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by detecting the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, the gravitational field of the aircraft acts on the bar magnet in the gravitational field detection assembly, so that the magnetic field of the bar magnet is transformed, and then the magnetic field is captured by the magnetic induction element and converted into a voltage signal, and the passive detection of the aircraft entering the scanning range is realized. The invention also provides an aircraft detection method and device with the beneficial effects, and a computer readable storage medium.
Drawings
For a clearer description of embodiments of the invention or of the prior art, the drawings that are used in the description of the embodiments or of the prior art will be briefly described, it being apparent that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained from them without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an embodiment of an anti-stealth radar according to the present invention;
FIG. 2 is a front view of another embodiment of the anti-stealth radar provided by the present invention;
FIG. 3 is a side view of another embodiment of the anti-stealth radar provided by the present invention;
FIG. 4 is a flow chart of one embodiment of an aircraft detection method provided by the present invention;
fig. 5 is a schematic structural view of an embodiment of an aircraft detection device provided by the present invention.
Detailed Description
In order to better understand the aspects of the present invention, the present invention will be described in further detail with reference to the accompanying drawings and detailed description. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The core of the invention is to provide an anti-stealth radar, a structural schematic diagram of one specific embodiment of which is shown in fig. 1, which is called as a specific embodiment I, and comprises a gravitational field detection component and a processor 03;
The gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, wherein the induction surfaces of the two magnetic induction elements 02 face the same side surface of the bar magnet 01;
The two magnetic induction elements 02 are symmetrically arranged at the N-terminal and the S-terminal of the bar magnet 01; wherein, the 0 magnetic point of the bar magnet 01 is the symmetry axis of the two magnetic induction elements 02;
The processor 03 is connected with the magnetic induction elements 02, and is used for receiving voltage signals generated by the two magnetic induction elements 02, determining aircraft azimuth information according to the voltage signals, and determining aircraft position information according to the aircraft azimuth information; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02.
In a preferred embodiment, the long axis of the bar magnet 01 rotates in the horizontal direction, and when the voltage signals from the two magnetic induction elements 02 are equal in magnitude, the aircraft azimuth information is determined based on the direction of the long axis of the bar magnet 01.
The distance between the air vehicle and the magnetic induction elements 02 influences the voltage generated by the magnetic induction elements 02, so that when the voltage signals from the two magnetic induction elements 02 are equal, the distance between the air vehicle and the two magnetic induction elements 02 is the same, and the air vehicle is positioned in the direction in the vertical plane of the bar magnet 01 because the magnetic induction elements 02 are axisymmetric on the bar magnet 01 according to the middle position of the 0 magnetic point (generally the center of the bar magnet 01). Of course, it may be set that when the difference between the voltages measured by the two magnetic induction elements 02 is smaller than the preset error range, it is determined that the distances from the aircraft to the two magnetic induction elements 02 are the same.
Note that, in order to achieve the above preferred embodiment, the long axis of the bar magnet 01 is required to be rotated horizontally, and the bar magnet 01 is not required to be kept horizontally, and the rotation of the bar magnet 01 does not necessarily need to be 360 degrees, and may be left-right swing within a predetermined angle range.
As a preferred embodiment, the anti-stealth radar comprises a plurality of gravitational field detection assemblies arranged at different positions.
The position of each gravitational field detection assembly is different, the larger the direction difference of the aircraft entering the scanning range is, the more accurate the final position information is, in addition, the single gravitational field detection assembly can only determine the direction of the flying object, the position information obtained by the position information can be regarded as the direction only, the gravitational field detection assembly is further increased to more than two gravitational field detection assemblies, the detection precision and accuracy can be further increased, and the specific quantity can be correspondingly adjusted according to actual conditions.
As a special case of one of the above preferred embodiments, the gravitational field detection assemblies are arranged at different heights;
The processor 03 is configured to determine the aircraft azimuth information according to voltage signals generated by different gravitational field detection components; denoising the voltage signal according to the preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of each gravitational field detection assembly corresponding to the aircraft; and determining the aircraft position information according to the aircraft azimuth information and the distance information.
When the gravitational field detection components are at different heights, the influence of the gravitational field of the earth on the gravitational field detection components at different heights is different, so that the influence of the gravitational field of the earth on the gravitational field detection components at different heights is required to be eliminated, after the influence of the gravitational field of the earth is eliminated, the voltage signal can be regarded as voltage change caused by magnetic field change completely caused by the gravitational field of the aircraft, the voltage change is singly related to the distance between the aircraft and the gravitational field detection components, the distance between the aircraft and the gravitational field detection components can be obtained according to the voltage change, the distance between the aircraft and the gravitational field detection components is x, the central vertical plane of the bar magnet 01 of the gravitational field detection components is alpha, the aircraft is positioned in the alpha plane, the circular arc with the radius x from the circle center (namely the gravitational field detection components) is visible, and when two gravitational field detection components exist and each measurement circular arc can intersect, the position of the aircraft can be determined as a coordinate in space. In addition, the aforementioned "the gravitational field detection components are disposed at different heights" includes the case where each of the gravitational field detection components is disposed at different heights, and also includes the case where a part of the gravitational field detection components are disposed at the same height and another part of the gravitational field detection components are disposed at other heights.
It can be known from the above description that, to determine the spatial three-dimensional coordinates of an aircraft, at least two gravitational field detection assemblies having an intersection point in the vertical plane are required, for example, an anti-hidden radar including two gravitational field detection assemblies, where the bar magnet 01 of one gravitational field detection assembly is horizontally disposed and rotates in the same horizontal plane, and the bar magnet 01 of the other gravitational field detection assembly is vertically disposed and rotates in a plane perpendicular to the ground surface.
As a further preferred embodiment, the anti-stealth radar includes a plurality of gravitational field detection assemblies disposed at different heights and having identical midpoints, the gravitational field detection assemblies are disposed in the same plate-shaped antenna, a front view of the plate-shaped antenna is shown in fig. 2, and a side view of the plate-shaped antenna is shown in fig. 3, and the plate-shaped antenna can rotate in a horizontal plane around a supporting shaft thereof so as to expand a scanning range of the radar. According to the embodiment, the equipment space can be utilized more fully, subsequent assembly is facilitated, the specific orientation of the aircraft is not required to be calculated any more, the orientation of the plate-shaped antenna when the voltages of the two magnetic induction elements 02 of the same gravitational field detection assembly are consistent, namely the direction of the aircraft relative to the radar, the spatial distribution freedom degree of the assembly is improved, the gravitational field detection assemblies form different arrays according to actual needs, and further the voltage signals acquired by the gravitational field detection assemblies are further led into the consideration factor of the height of the gravitational field detection assembly, so that the finally obtained position information is more accurate. The step of removing the earth gravitational field can be completed on a high-power amplifier, and of course, the method can be correspondingly adjusted according to actual conditions.
As a preferred embodiment, the gravitational field detection assembly further comprises a differential amplifier;
the differential amplifier is used for determining a unidirectional voltage signal according to the voltage signals sent by the two magnetic induction elements 02;
the processor 03 determines the distance information from the unidirectional voltage signal.
In the preferred embodiment, the differential amplifier is added to the anti-stealth radar, and since the two magnetic induction elements 02 are respectively located at different poles of the bar magnet 01, the voltage signals generated by the two magnetic induction elements 02 are opposite, so that the differential amplifier in the preferred embodiment is required to convert the two voltage signals with opposite directions into unidirectional voltage signals, which is convenient for the subsequent processor 03 to process, and the circuit and the installation cost are simplified.
On the basis of the differential amplifier, an amplifying circuit is further added to the anti-stealth radar;
the amplifying circuit is used for amplifying the electric signal between the gravitational field detection component and the processor 03.
The electric signal is amplified, so that the processor 03 is easier to process and is less prone to being interfered by the outside, and the detection precision and the detection accuracy are improved; still further, the amplifying circuit is a high power amplifier; it should be noted that the amplifying circuit may be disposed between the magnetic induction element 02 and the differential amplifying circuit, for amplifying the micro current of the magnetic induction element 02; or between the differential discharge circuit and the processor 03 for amplifying the unidirectional voltage signal.
In addition, the magnetic induction element 02 is a linear hall element, and the linear hall element can linearly convert the magnetic field intensity change into the electric signal change, so that the measurement accuracy can be further improved, the fidelity range of the voltage signal obtained by measurement is enlarged, the calculation amount of signal processing is reduced, and the burden of the processor 03 is reduced. Of course, other magnetic induction elements 02 may be selected according to the actual situation.
The anti-stealth radar provided by the invention comprises a gravitational field detection component and a processor 03; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, wherein the induction surfaces of the two magnetic induction elements 02 face the same side surface of the bar magnet 01; the two magnetic induction elements 02 are symmetrically arranged at the N-terminal and the S-terminal of the bar magnet 01; wherein, the 0 magnetic point of the bar magnet 01 is the symmetry axis of the two magnetic induction elements 02; the processor 03 is connected with the magnetic induction elements 02, and is used for receiving voltage signals generated by the two magnetic induction elements 02, determining aircraft azimuth information according to the voltage signals, and determining aircraft position information according to the aircraft azimuth information; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02. The magnetic field is a spatial motion. The geometric mean and the arithmetic mean of the space movement process are unequal, so that the density of the space is changed, the gravitational field shows unidirectional magnetic characteristics under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by detecting the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, the gravitational field of the aircraft acts on the bar magnet 01 in the gravitational field detection assembly, so that the magnetic field of the bar magnet 01 is transformed, and then the magnetic field is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering the scanning range is realized.
The invention also provides an aircraft detection method, a flow schematic diagram of one specific embodiment of which is shown in fig. 4, comprising the following steps:
S101: acquiring a voltage signal from a gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, wherein the induction surfaces of the two magnetic induction elements 02 face the same side surface of the bar magnet 01; the two magnetic induction elements 02 are symmetrically arranged at the N-terminal and the S-terminal of the bar magnet 01; wherein, the 0 magnetic point of the bar magnet 01 is the symmetry axis of the two magnetic induction elements 02; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02.
S102: and determining the aircraft azimuth information according to the voltage signals.
Preferably, the step comprises:
When the voltage signals from the two magnetic induction elements 02 are equal in magnitude, the aircraft azimuth information is determined according to the direction of the long axis of the bar magnet 01.
S103: and determining the position information of the aircraft according to the position information of the aircraft.
Preferably, the step comprises:
S1031: when a plurality of gravitational field detection assemblies exist and are arranged at different heights, denoising the voltage signals according to the preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of each gravitational field detection assembly corresponding to the aircraft.
S1032: and determining the position information of the aircraft according to the azimuth information and the distance information of the aircraft.
It should be noted that when there are a plurality of gravitational field detection assemblies with different heights, the gravitational field detection assemblies are subject to different gravities, so that the influence of gravitational field on gravitational field detection assemblies with different heights caused by gravitational attraction must be eliminated, and the gravitational field information of the earth is the electrical signal data when the gravitational field detection assembly with the current height is only subject to gravitational attraction in the detection range, and the voltage signal after the aircraft is detected is corrected according to the gravitational field information of the earth, so that the voltage data only representing the aircraft can be obtained. Of course, the earth gravitational field information may be empirical data obtained through experiments in advance, and the specific beneficial effects may refer to the description of the anti-stealth radar described above, which is not described herein.
According to the aircraft detection method provided by the invention, the voltage signal is obtained from the gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, wherein the induction surfaces of the two magnetic induction elements 02 face the same side surface of the bar magnet 01; the two magnetic induction elements 02 are symmetrically arranged at the N-terminal and the S-terminal of the bar magnet 01; wherein, the 0 magnetic point of the bar magnet 01 is the symmetry axis of the two magnetic induction elements 02; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02; and determining the position information of the aircraft according to the voltage signals. The magnetic field is a spatial motion. The geometric mean and the arithmetic mean of the space movement process are unequal, so that the density of the space is changed, the gravitational field shows unidirectional magnetic characteristics under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by detecting the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, the gravitational field of the aircraft acts on the bar magnet 01 in the gravitational field detection assembly, so that the magnetic field of the bar magnet 01 is transformed, and then the magnetic field is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering the scanning range is realized.
The following describes an aircraft detection device provided in an embodiment of the present invention, and the aircraft detection device described below and the aircraft detection method described above may be referred to correspondingly.
Fig. 5 is a block diagram of an aircraft detection device according to an embodiment of the present invention, and referring to fig. 5, the aircraft detection device may include:
An acquisition module 100 for acquiring a voltage signal from the gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02; the two magnetic induction elements 02 are arranged at the N-terminal and the S-terminal of the bar magnet 01 in an axisymmetric manner by taking the middle position of the 0 magnetic point of the bar magnet 01 as an axis; the induction surfaces of the two magnetic induction elements 02 face the same side surface of the strip-shaped magnet 01; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02;
a position module 200 for determining aircraft position information from the voltage signals;
the positioning module 300 is configured to determine the position information of the aircraft according to the position information of the aircraft.
As a preferred embodiment, the azimuth module 200 includes:
And the plane positioning unit is used for determining the aircraft azimuth information according to the direction of the long axis of the bar magnet 01 when the voltage signals from the two magnetic induction elements 02 are equal in magnitude.
As a preferred embodiment, the positioning module 300 includes:
The difference denoising unit is used for denoising the voltage signal according to the preset earth gravitational field information corresponding to each gravitational field detection assembly when a plurality of gravitational field detection assemblies exist and are arranged at different heights, so as to obtain the distance information of the aircraft corresponding to each gravitational field detection assembly;
and the multi-component positioning unit is used for determining the aircraft position information according to the aircraft azimuth information and the distance information.
The aircraft detection device provided by the invention is used for acquiring voltage signals from a gravitational field detection assembly through an acquisition module 100; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02; the two magnetic induction elements 02 are arranged at the N-terminal and the S-terminal of the bar magnet 01 in an axisymmetric manner by taking the middle position of the 0 magnetic point of the bar magnet 01 as an axis; the induction surfaces of the two magnetic induction elements 02 face the same side surface of the strip-shaped magnet 01; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02; a position module 200 for determining aircraft position information from the voltage signals; the positioning module 300 is configured to determine the position information of the aircraft according to the position information of the aircraft. The geometric mean and the arithmetic mean of the space movement process are unequal, so that the density of the space is changed, the gravitational field shows unidirectional magnetic characteristics under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by detecting the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, the gravitational field of the aircraft acts on the bar magnet 01 in the gravitational field detection assembly, so that the magnetic field of the bar magnet 01 is transformed, and then the magnetic field is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering the scanning range is realized.
The aircraft detection device of the present embodiment is used to implement the foregoing aircraft detection method, so that the detailed description of the aircraft detection device may be found in the foregoing example portions of the aircraft detection method, for example, the acquisition module 100, the azimuth module 200, and the positioning module 300 are respectively used to implement steps S101, S102, and S103 in the foregoing aircraft detection method, so that the detailed description thereof may refer to the corresponding respective portion of the examples, and will not be repeated herein.
A computer-readable storage medium, on which a computer program is stored which, when executed by the processor 03, implements the steps of the aircraft detection method as described in any of the above. The anti-stealth radar provided by the invention comprises a gravitational field detection component and a processor 03; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, wherein the induction surfaces of the two magnetic induction elements 02 face the same side surface of the bar magnet 01; the two magnetic induction elements 02 are symmetrically arranged at the N-terminal and the S-terminal of the bar magnet 01; wherein, the 0 magnetic point of the bar magnet 01 is the symmetry axis of the two magnetic induction elements 02; the processor 03 is connected with the magnetic induction elements 02, and is used for receiving voltage signals generated by the two magnetic induction elements 02, determining aircraft azimuth information according to the voltage signals, and determining aircraft position information according to the aircraft azimuth information; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02. The magnetic field is a spatial motion. The geometric mean and the arithmetic mean of the space movement process are unequal, so that the density of the space is changed, the gravitational field shows unidirectional magnetic characteristics under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by detecting the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, the gravitational field of the aircraft acts on the bar magnet 01 in the gravitational field detection assembly, so that the magnetic field of the bar magnet 01 is transformed, and then the magnetic field is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering the scanning range is realized.
In this specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, so that the same or similar parts between the embodiments are referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
It should be noted that in this specification, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Those of skill would further appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both, and that the various illustrative elements and steps are described above generally in terms of functionality in order to clearly illustrate the interchangeability of hardware and software. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by the processor 0303, or in a combination of the two. The software modules may be disposed in Random Access Memory (RAM), memory, read Only Memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.
The anti-stealth radar, the aircraft detection method, the device and the computer readable storage medium provided by the invention are described in detail above. The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the method of the present invention and its core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.
Claims (10)
1. An anti-stealth radar is characterized by comprising a processor and a plurality of gravitational field detection assemblies arranged at different heights;
The gravitational field detection assembly comprises a bar magnet and two magnetic induction elements, and the induction surfaces of the two magnetic induction elements face the same side surface of the bar magnet;
The two magnetic induction elements are symmetrically arranged at the N-terminal and the S-terminal of the strip magnet; wherein the 0 magnetic point of the bar magnet is the symmetry axes of the two magnetic induction elements;
The processor is connected with the magnetic induction elements and is used for receiving voltage signals generated by the two magnetic induction elements and determining the azimuth information of the aircraft according to the voltage signals generated by different gravitational field detection assemblies; denoising the voltage signal according to the preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of each gravitational field detection assembly corresponding to the aircraft; determining the position information of the aircraft according to the azimuth information and the distance information of the aircraft; when the aircraft enters the scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element.
2. The anti-stealth radar according to claim 1, wherein the long axis of the bar magnet rotates in a horizontal direction, and the aircraft azimuth information is determined according to the direction of the long axis of the bar magnet when the voltage signals from the two magnetic induction elements are equal in magnitude.
3. An anti-stealth radar according to claim 2, wherein the anti-stealth radar comprises a plurality of differently positioned gravitational field detection assemblies.
4. An anti-stealth radar according to claim 3, wherein the gravitational field detection assembly further comprises a differential amplifier;
The differential amplifier is used for determining unidirectional voltage signals according to the voltage signals sent by the two magnetic induction elements;
the processor determines the distance information from the unidirectional voltage signal.
5. The anti-stealth radar according to any one of claims 1 to 4, wherein the anti-stealth radar further comprises an amplification circuit;
The amplifying circuit is used for amplifying the electric signal between the gravitational field detection component and the processor.
6. The anti-stealth radar of claim 1, wherein the magnetic induction element is a linear hall element.
7. A method of aircraft detection comprising:
Acquiring a voltage signal from a gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet and two magnetic induction elements, and the induction surfaces of the two magnetic induction elements face the same side surface of the bar magnet; the two magnetic induction elements are symmetrically arranged at the N-terminal and the S-terminal of the strip magnet; wherein the 0 magnetic point of the bar magnet is the symmetry axes of the two magnetic induction elements; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element;
Determining aircraft azimuth information from the voltage signal;
determining aircraft position information according to the aircraft azimuth information;
the determining aircraft location information from the aircraft azimuth information includes:
When a plurality of gravitational field detection assemblies exist and are arranged at different heights, denoising the voltage signals according to the preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain the distance information of the aircraft corresponding to each gravitational field detection assembly;
And determining the position information of the aircraft according to the azimuth information and the distance information of the aircraft.
8. The aircraft detection method of claim 7, wherein said determining aircraft position information from said voltage signal comprises:
and when the voltage signals from the two magnetic induction elements are equal in magnitude, determining the aircraft azimuth information according to the direction of the long axis of the bar magnet.
9. An aircraft detection device, comprising:
The acquisition module is used for acquiring a voltage signal from the gravitational field detection assembly; the gravitational field detection assembly comprises a bar magnet and two magnetic induction elements; the two magnetic induction elements are arranged at the N-terminal and the S-terminal of the bar magnet in an axisymmetric way by taking the middle position of the 0 magnetic point of the bar magnet as an axis; the induction surfaces of the two magnetic induction elements face the same side surface of the strip-shaped magnet; when the aircraft enters a scanning range, the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element;
The azimuth module is used for determining aircraft azimuth information according to the voltage signals;
the positioning module is used for determining the position information of the aircraft according to the position information of the aircraft;
The positioning module comprises:
The difference denoising unit is used for denoising the voltage signal according to the preset earth gravitational field information corresponding to each gravitational field detection assembly when a plurality of gravitational field detection assemblies exist and are arranged at different heights, so as to obtain the distance information of the aircraft corresponding to each gravitational field detection assembly;
and the multi-component positioning unit is used for determining the aircraft position information according to the aircraft azimuth information and the distance information.
10. A computer-readable storage medium, characterized in that it has stored thereon a computer program which, when executed by a processor, implements the steps of the aircraft detection method according to claim 7 or 8.
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