CN113238223A - Anti-stealth radar and aircraft detection method and device - Google Patents
Anti-stealth radar and aircraft detection method and device Download PDFInfo
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- CN113238223A CN113238223A CN202110566421.0A CN202110566421A CN113238223A CN 113238223 A CN113238223 A CN 113238223A CN 202110566421 A CN202110566421 A CN 202110566421A CN 113238223 A CN113238223 A CN 113238223A
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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
Abstract
The invention discloses a reverse 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 used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range. The anti-stealth radar provided by the invention utilizes the gravitational field of the aircraft to detect, and has excellent concealment. The invention also provides an aircraft detection method, an aircraft detection device and a computer-readable storage medium with the beneficial effects.
Description
Technical Field
The invention relates to the field of space surveying and mapping, in particular to an anti-stealth radar, an aircraft detection method, an anti-stealth radar device and a computer readable storage medium.
Background
With the development of science, people gradually send various aerospace devices to high altitude, however, in order to avoid air accidents or safe soil taking, the demand for timely grasping the position of an aircraft is increasing, namely, the demand of people for radar performance is higher and higher.
The existing radar is usually an active electromagnetic wave radar, and for the electromagnetic wave radar, a mature magnetic coating exists in the prior art, the magnetic coating can be used for absorbing electromagnetic waves actively sent by the radar, and the stealth effect of the electromagnetic waves with any frequency can be realized theoretically. Accordingly, when the traditional electromagnetic wave radar wants to find the stealth target, the stealth target can be detected only by increasing the power of the electromagnetic wave to ensure that the stealth coating reaches magnetic saturation. Increasing the power of the electromagnetic wave increases the possibility of the radar being attacked.
Therefore, how to detect the aircraft in a 'reverse stealth' manner while ensuring the concealment of 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 anti-stealth device and a computer readable storage medium, which aim to solve the problem that anti-stealth cannot be realized on the premise that the radar is concealed per se in the prior art.
In order to solve the technical problem, the invention provides 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 two magnetic induction elements are symmetrically arranged at the N pole end and the S pole end of the bar magnet; the middle position of a 0 magnetic point of the bar magnet is a symmetry axis of the two magnetic induction elements;
the processor is connected with the magnetic induction elements and used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range.
Optionally, in the anti-stealth radar, a long axis of the bar magnet rotates in a horizontal direction, and when the magnitudes of the voltage signals from the two magnetic induction elements are equal, the aircraft orientation 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 assemblies with different setting positions.
Optionally, in the anti-stealth radar, the gravitational field detection assemblies are arranged at different heights;
the processor is used for determining the aircraft azimuth information according to voltage signals generated by different gravitational field detection assemblies; denoising the voltage signal according to earth gravitational field information corresponding to each preset gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly; and determining the aircraft position information according to the aircraft position information and the distance information.
Optionally, in the anti-stealth radar, 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;
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 assembly 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 the 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 pole end and the S pole end of the bar magnet; the middle position of a 0 magnetic point of the bar magnet is a symmetry axis of the two magnetic induction elements; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range;
determining aircraft orientation information from the voltage signal;
and determining aircraft position information according to the aircraft position information.
Optionally, in the aircraft detection method, the determining aircraft orientation 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 orientation information according to the direction of the long axis of the bar magnet.
Optionally, in the aircraft detection method, the determining aircraft position information according to the aircraft position information includes:
when a plurality of gravitational field detection assemblies exist and are arranged at different heights, denoising the voltage signal according to preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly;
and determining the aircraft position information according to the aircraft position information and the distance information. 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 axially and symmetrically arranged at the N pole end and the S pole end of the bar magnet by taking the 0 magnetic point middle position of the bar magnet as an axis; the induction surfaces of the two magnetic induction elements face to the same side surface of the bar magnet; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range;
the orientation module is used for determining aircraft orientation information according to the voltage signal;
and the positioning module is used for determining the position information of the aircraft according to the orientation information of the aircraft.
A computer-readable storage medium having stored thereon a computer program which, when being executed by a processor, carries out the steps of the aircraft detection method according to any one of the preceding claims.
The anti-stealth radar provided by the invention 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 two magnetic induction elements are symmetrically arranged at the N pole end and the S pole end of the bar magnet; the middle position of a 0 magnetic point of the bar magnet is a symmetry axis of the two magnetic induction elements; the processor is connected with the magnetic induction elements and used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range.
The magnetic field is a spatial motion. Because the geometric mean and the arithmetic mean of the space motion process are not equal, the density of the space is changed, the gravitational field shows a unidirectional magnetic characteristic under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by checking the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, and 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 changed, and then is captured by the magnetic induction element and converted into a voltage signal, and the passive detection of the aircraft entering a scanning range is realized. The invention also provides an aircraft detection method, an aircraft detection device and a computer-readable storage medium with the beneficial effects.
Drawings
In order to more clearly illustrate the embodiments or technical solutions of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an embodiment of an anti-stealth radar provided in the present invention;
FIG. 2 is a front view of another embodiment of an anti-stealth radar provided by the present invention;
FIG. 3 is a side view of another embodiment of an anti-stealth radar provided by the present invention;
FIG. 4 is a schematic flow chart diagram illustrating one embodiment of a method for aircraft detection provided by the present invention;
fig. 5 is a schematic structural diagram of an embodiment of the aircraft detection device provided by the invention.
Detailed Description
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The core of the invention is to provide an anti-stealth radar, the structure diagram of one specific embodiment of which is shown in fig. 1, and is called as the first specific embodiment, and the first specific embodiment 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, and 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 pole end and the S pole end of the bar magnet 01; the middle position of the 0 magnetic point of the bar magnet 01 is a 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 position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by a change of a magnetic field signal received by the magnetic induction element 02 when the aircraft enters a scanning range.
In a preferred embodiment, the long axis of the bar magnet 01 rotates in the horizontal direction, and when the magnitude of the voltage signals from the two magnetic induction elements 02 is equal, the aircraft orientation information is determined according to the direction of the long axis of the bar magnet 01.
The distance from the aircraft to the magnetic induction element 02 influences the voltage generated by the magnetic induction element 02, so that when the voltage signals from the two magnetic induction elements 02 are equal, it is indicated that the distance from the aircraft to the two magnetic induction elements 02 is the same, and because the magnetic induction elements 02 are axisymmetric on the bar magnet 01 according to a 0 magnetic point median (generally, the center of the bar magnet 01), it can be obtained that the aircraft is located in the direction in the vertical plane of the bar magnet 01. Of course, according to specific circumstances, it may also be set that when the difference between the magnitudes of the voltages measured by the two magnetic induction elements 02 is smaller than a preset error range, it is determined that the distances from the aircraft to the two magnetic induction elements 02 at this time are the same.
Note that, in order to realize the above preferred embodiment, it is only necessary to rotate the long axis of the bar magnet 01 by a rotation amount in the horizontal direction, and it is not necessary that the bar magnet 01 is kept horizontal, and the rotation of the bar magnet 01 does not necessarily need to be 360 degrees, and may be a horizontal swing within a predetermined angle range.
In a preferred embodiment, the anti-stealth radar comprises a plurality of gravitational field detection assemblies arranged at different positions.
The positions of the gravitational field detection assemblies are different, the larger the difference of the directions of the aircrafts entering a scanning range, which are indicated by the gravitational field detection assemblies, is, the more accurate the finally obtained position information is, in addition, the direction of the flying object can only be determined by the single gravitational field detection assembly through the foregoing, the position information obtained by the direction information can be regarded as the direction which can only be indicated, the accuracy and the precision of detection can be further increased by further increasing the number of the gravitational field detection assemblies to more than two, and of course, the specific number can be correspondingly adjusted according to the actual situation.
As a special case of the above preferred embodiment, the gravitational field detection assemblies are arranged at different heights;
the processor 03 is used for determining the aircraft orientation information according to the voltage signals generated by the different gravitational field detection assemblies; denoising the voltage signal according to earth gravitational field information corresponding to each preset gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly; and determining the aircraft position information according to the aircraft position information and the distance information.
When the gravitational field detection assemblies are at different heights, the influence of the earth gravitational field on the gravitational field detection assemblies at different heights needs to be eliminated, and after the influence of the earth gravitational field is eliminated, the voltage signal can be regarded as a voltage change completely caused by the magnetic field change caused by the gravitational field of the aircraft, and the voltage change is singly related to the distance between the aircraft and the gravitational field detection assemblies, so that the distance between the aircraft and the gravitational field detection assemblies can be obtained, and by combining the orientation information, the distance between the aircraft and the gravitational field detection assemblies is assumed to be x, the median plane of the bar magnet 01 of the gravitational field detection assemblies is α, the aircraft is located in the α plane, and the circle center of the distance (namely, the gravitational field detection assemblies) is on an arc with the radius of x, therefore, when two gravitational field detection assemblies exist and the two stress field detection assemblies respectively measure that the circular arcs can intersect, the coordinates of one point in the space can be determined and recorded as the position of the aircraft. In addition, the aforesaid "the gravitational field detection assemblies are disposed at different heights" includes a case where each of the gravitational field detection assemblies is located at a different height, and also includes a case where a part of the gravitational field detection assemblies is located at the same height and another part is located at another height.
It can be known from the above description that at least two gravitational field detection assemblies having intersection points on their vertical surfaces are required to determine the spatial three-dimensional coordinates of an aircraft, for example, a reverse-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 comprises a plurality of gravitational field detection assemblies which are arranged at different heights and have consistent midperpendicular planes, the gravitational field detection assemblies are arranged in the same plate-shaped antenna, the front view of the plate-shaped antenna is shown in fig. 2, the side view of the plate-shaped antenna is shown in fig. 3, and the plate-shaped antenna can rotate around a supporting shaft thereof in a horizontal plane so as to enlarge the scanning range of the radar. According to the method, the device space can be fully utilized, subsequent assembly is facilitated, the specific orientation of the aircraft does not need to be calculated, 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 orientation of the aircraft relative to the radar, the spatial distribution freedom of the assembly is improved, the gravitational field detection assemblies form different arrays according to actual needs, and then voltage signals acquired by the gravitational field detection assemblies are further introduced into the consideration factor of the height of the gravitational field detection assembly, so that 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 step can be adjusted correspondingly 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 additionally arranged for the anti-stealth radar, and since the two magnetic induction elements 02 are respectively located at different poles of the bar magnet 01, voltage signals generated by the two magnetic induction elements 02 are opposite in direction, so that the two voltage signals opposite in direction are converted into unidirectional voltage signals by the differential amplifier in the preferred embodiment, which is convenient for the subsequent processor 03 to process, and the circuit and installation cost are simplified.
On the basis of the addition 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 assembly and the processor 03.
The electric signals are amplified and then are easier to process by the processor 03, and are less susceptible to external interference, so that 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, and is used for amplifying the minute current of the magnetic induction element 02; or is disposed between the differential discharge circuit and the processor 03, and is configured to amplify 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 by using the linear hall element, the fidelity range of the voltage signal obtained by measurement is expanded, the calculation amount of signal processing is reduced, and the burden of the processor 03 is reduced. Of course, other magnetic induction elements 02 can be selected according to the actual situation.
The anti-stealth radar provided by the invention comprises a gravitational field detection assembly and a processor 03; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, and 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 pole end and the S pole end of the bar magnet 01; the middle position of the 0 magnetic point of the bar magnet 01 is a 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 position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by a change of a magnetic field signal received by the magnetic induction element 02 when the aircraft enters a scanning range. The magnetic field is a spatial motion. Because the geometric mean and the arithmetic mean of the space motion process are not equal, the density of the space is changed, the gravitational field shows a unidirectional magnetic characteristic under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by checking the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, and 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 is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering a scanning range is realized.
The invention also provides an aircraft detection method, a flow diagram of a specific embodiment of which is shown in fig. 4, and the method comprises the following steps:
s101: 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, and 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 pole end and the S pole end of the bar magnet 01; the middle position of the 0 magnetic point of the bar magnet 01 is a symmetry axis of the two magnetic induction elements 02; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02 when the aircraft enters the scanning range.
S102: and determining aircraft orientation information according to the voltage signal.
Preferably, this step comprises:
when the voltage signals from the two magnetic induction elements 02 are equal in magnitude, determining the aircraft orientation information according to the direction of the long axis of the bar magnet 01.
S103: and determining aircraft position information according to the aircraft position information.
Preferably, this step comprises:
s1031: when a plurality of gravitational field detection assemblies exist and the gravitational field detection assemblies are arranged at different heights, denoising the voltage signal according to preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly.
S1032: and determining the aircraft position information according to the aircraft position information and the distance information.
It should be noted that, when there are a plurality of gravitational field detection assemblies with different installation heights, the gravitational field detection assemblies themselves are subjected to different earth gravities, so that the influence of the earth gravity on the gravitational field detection assemblies at different heights must be eliminated, and the earth gravitational field information, that is, the electrical signal data of the gravitational field detection assembly at the current height, which is only subjected to the earth gravity within the detection range, is corrected to the voltage signal after the aircraft is detected according to the earth gravitational field information, 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 specific beneficial effects may refer to the description of the anti-stealth radar in the foregoing, which is not further described herein.
The aircraft detection method provided by the invention comprises the steps of 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, and 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 pole end and the S pole end of the bar magnet 01; the middle position of the 0 magnetic point of the bar magnet 01 is a symmetry axis of the two magnetic induction elements 02; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02 when the aircraft enters a scanning range; aircraft position information is determined from the voltage signal. The magnetic field is a spatial motion. Because the geometric mean and the arithmetic mean of the space motion process are not equal, the density of the space is changed, the gravitational field shows a unidirectional magnetic characteristic under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by checking the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, and 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 is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering a scanning range is realized.
In the following, the aircraft detection device provided by the embodiment of the present invention is introduced, 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, where the aircraft detection device according to fig. 5 may include:
an obtaining module 100, configured to obtain 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 axially symmetrically arranged at the N pole end and the S pole end of the bar magnet 01 by taking the 0 magnetic point middle position 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 bar magnet 01; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02 when the aircraft enters a scanning range;
an orientation module 200 for determining aircraft position information from the voltage signal;
and the positioning module 300 is used for determining the aircraft position information according to the aircraft position information.
As a preferred embodiment, the orientation module 200 includes:
and the surface positioning unit is used for determining the aircraft orientation 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 height denoising unit is used for denoising the voltage signal according to preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly when a plurality of gravitational field detection assemblies exist and are arranged at different heights;
and the multi-component positioning unit is used for determining the aircraft position information according to the aircraft position information and the distance information.
The aircraft detection device provided by the invention is used for acquiring a voltage signal from a gravitational field detection assembly through the 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 axially symmetrically arranged at the N pole end and the S pole end of the bar magnet 01 by taking the 0 magnetic point middle position 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 bar magnet 01; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element 02 when the aircraft enters a scanning range; an orientation module 200 for determining aircraft position information from the voltage signal; and the positioning module 300 is used for determining the aircraft position information according to the aircraft position information. Because the geometric mean and the arithmetic mean of the space motion process are not equal, the density of the space is changed, the gravitational field shows a unidirectional magnetic characteristic under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by checking the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, and 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 is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering a scanning range is realized.
The aircraft detection device of this embodiment is used to implement the aircraft detection method, and therefore a specific implementation manner of the aircraft detection device can be seen in the above embodiment sections of the aircraft detection method, for example, the obtaining module 100, the orientation module 200, and the positioning module 300 are respectively used to implement steps S101, S102, and S103 in the aircraft detection method, so that the specific implementation manner thereof may refer to descriptions of corresponding embodiments of each section, and is not described herein again.
A computer-readable storage medium having stored thereon a computer program which, when being executed by a processor 03, carries out the steps of the aircraft detection method according to any one of the preceding claims. The anti-stealth radar provided by the invention comprises a gravitational field detection assembly and a processor 03; the gravitational field detection assembly comprises a bar magnet 01 and two magnetic induction elements 02, and 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 pole end and the S pole end of the bar magnet 01; the middle position of the 0 magnetic point of the bar magnet 01 is a 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 position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by a change of a magnetic field signal received by the magnetic induction element 02 when the aircraft enters a scanning range. The magnetic field is a spatial motion. Because the geometric mean and the arithmetic mean of the space motion process are not equal, the density of the space is changed, the gravitational field shows a unidirectional magnetic characteristic under the action of a magnetic field, and the gravitational field environment around the equipment can be determined by checking the magnetic field change caused by the gravitational field. By utilizing the principle, the electromagnetic stealth aircraft also has a gravitational field, and 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 is captured by the magnetic induction element 02 and converted into a voltage signal, and the passive detection of the aircraft entering a scanning range is realized.
The embodiments are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same or similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
It is to be noted that, in the present 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. Also, 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 an … …" does not exclude the presence of other identical 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 components and steps have been described above generally in terms of their functionality in order to clearly illustrate this 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 implementation. 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 processor 0303, or in a combination of the two. A software module may reside 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 apparatus, and the computer-readable storage medium provided by the present invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (12)
1. An anti-stealth radar is characterized by comprising 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 pole end and the S pole end of the bar magnet; the middle position of a 0 magnetic point of the bar magnet is a symmetry axis of the two magnetic induction elements;
the processor is connected with the magnetic induction elements and used for receiving voltage signals generated by the two magnetic induction elements, determining aircraft position information according to the voltage signals and determining aircraft position information according to the aircraft position information; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range.
2. The anti-stealth radar of claim 1, wherein a long axis of the bar magnet rotates in a horizontal direction, and the aircraft orientation information is determined according to a direction of the long axis of the bar magnet when the voltage signals from the two magnetic induction elements are equal in magnitude.
3. The anti-stealth radar of claim 2, comprising a plurality of gravity field detection assemblies disposed in different positions.
4. The anti-stealth radar of claim 3, wherein the gravitational field detection assemblies are disposed at different heights;
the processor is used for determining the aircraft azimuth information according to voltage signals generated by different gravitational field detection assemblies; denoising the voltage signal according to earth gravitational field information corresponding to each preset gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly; and determining the aircraft position information according to the aircraft position information and the distance information.
5. The anti-stealth radar of claim 4, wherein the gravitational field detection component 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;
the processor determines the distance information from the unidirectional voltage signal.
6. The anti-stealth radar of any one of claims 1 to 5, further comprising an amplification circuit;
the amplifying circuit is used for amplifying the electric signal between the gravitational field detection assembly and the processor.
7. The anti-stealth radar of claim 1, wherein the magnetic induction element is a linear hall element.
8. An aircraft detection method, comprising:
acquiring a voltage signal from the 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 pole end and the S pole end of the bar magnet; the middle position of a 0 magnetic point of the bar magnet is a symmetry axis of the two magnetic induction elements; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range;
determining aircraft orientation information from the voltage signal;
and determining aircraft position information according to the aircraft position information.
9. The aircraft detection method of claim 8 wherein determining aircraft bearing information from the voltage signal comprises:
and when the voltage signals from the two magnetic induction elements are equal in magnitude, determining the aircraft orientation information according to the direction of the long axis of the bar magnet.
10. The aircraft detection method of claim 9 wherein determining aircraft position information from the aircraft position information comprises:
when a plurality of gravitational field detection assemblies exist and are arranged at different heights, denoising the voltage signal according to preset earth gravitational field information corresponding to each gravitational field detection assembly to obtain distance information of the aircraft corresponding to each gravitational field detection assembly;
and determining the aircraft position information according to the aircraft position information and the distance information.
11. 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 axially and symmetrically arranged at the N pole end and the S pole end of the bar magnet by taking the 0 magnetic point middle position of the bar magnet as an axis; the induction surfaces of the two magnetic induction elements face to the same side surface of the bar magnet; the voltage signal is a voltage change signal caused by the change of the magnetic field signal received by the magnetic induction element when the aircraft enters a scanning range;
the orientation module is used for determining aircraft orientation information according to the voltage signal;
and the positioning module is used for determining the position information of the aircraft according to the orientation information of the aircraft.
12. A computer-readable storage medium, characterized in that a computer program is stored on the computer-readable storage medium, which computer program, when being executed by a processor, carries out the steps of the aircraft detection method according to one of claims 8 to 10.
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