CN209913833U - Low-altitude aircraft defense system - Google Patents
Low-altitude aircraft defense system Download PDFInfo
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- CN209913833U CN209913833U CN201921126262.7U CN201921126262U CN209913833U CN 209913833 U CN209913833 U CN 209913833U CN 201921126262 U CN201921126262 U CN 201921126262U CN 209913833 U CN209913833 U CN 209913833U
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Abstract
The application provides a low-altitude aircraft defense system, wherein, the system includes: the detection radar is used for scanning the first area to detect the low-altitude aircraft appearing in the first area and obtain the position information of the low-altitude aircraft; the video monitoring device is used for tracking the low-altitude aircraft according to the position information of the low-altitude aircraft and displaying a video image of the low-altitude aircraft through the display; the interference device is used for sending interference signals of a plurality of working frequency bands to a second area through the transmitting antenna array when the position information of the low-altitude aircraft is in the second area, and the interference signals are used for interfering the communication link of the low-altitude aircraft; and the monitoring center platform is used for generating alarm information when the position information of the low-altitude aircraft is in the second area, generating a first control instruction according to the alarm information, and sending the first control instruction to the interference device. The multi-azimuth interference on the low-altitude aircraft can be realized, so that the low-altitude aircraft is forced to land or return.
Description
Technical Field
The application relates to the technical field of defense of low-altitude aircrafts (including small-sized fixed-wing aircrafts, gyroplanes, helicopters, unmanned planes, hovercars, flying containers and other flying targets below 3000 meters in true height), in particular to a defense system of the low-altitude aircrafts.
Background
Along with the continuous popularization of low-altitude aircrafts, the low-altitude aircrafts bring more convenience to daily life of people. However, the low-altitude aircraft has the characteristics of small volume, high speed, strong concealment and the like, and is easily used by lawbreakers for smuggling drugs, throwing dangerous objects, illegally shooting and the like, so that great challenges are brought to social security and precaution.
Therefore, how to ensure that each area is not interfered and invaded by a small-sized low-altitude aircraft to maintain social security becomes a difficult problem to be solved urgently.
Disclosure of Invention
The application provides a low-altitude aircraft defense system to realize carrying out diversified interference to low-altitude aircraft by interference device after low-altitude aircraft gets into the second region, make low-altitude aircraft unable location, communication, thereby force low-altitude aircraft to descend or return voyage.
An embodiment of an aspect of the present application provides a defense system for a low-altitude aircraft, including:
the system comprises a detection radar, a first processing unit and a second processing unit, wherein the detection radar is used for scanning a first area to detect a low-altitude aircraft appearing in the first area and acquiring position information of the low-altitude aircraft, and the first area comprises at least one second area;
the video monitoring device is used for tracking the low-altitude aircraft according to the position information of the low-altitude aircraft and displaying a video image of the low-altitude aircraft through a display;
the interference device is used for sending interference signals of a plurality of working frequency bands to the second area through the transmitting antenna array when the position information of the low-altitude aircraft is in the second area, and the interference signals are used for interfering the communication link of the low-altitude aircraft;
the monitoring center platform, the monitoring center platform with survey the radar, the video monitoring device with interference device intercommunication, the monitoring center platform is used for being in the position information of low-altitude aircraft generates alarm information when being in the second region, and according to alarm information generates first control command, and will first control command send to the interference device, wherein, first control command is used for controlling opening and closing of interference device.
The defense system for the low-altitude aircraft comprises a detection radar, a video monitoring device, a display, an interference device, a monitoring center platform, a communication link and a communication link, wherein the communication link, the communication link and the communication link are connected in sequence, the monitoring center platform is used for generating alarm information when the position information of the low-altitude aircraft is in a second area, the monitoring center platform is used for generating a first control instruction according to the alarm information, and the first control instruction is sent to the interference device, the first control instruction is used for controlling the interference device to be turned on and off. Therefore, after the low-altitude aircraft enters the second area, the interference device carries out multi-directional interference on the low-altitude aircraft, so that the low-altitude aircraft cannot be positioned and communicated, and the low-altitude aircraft is forced to land or return.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of a defense system of a low-altitude aircraft according to an embodiment of the present application;
FIG. 2 is a schematic diagram illustrating the arrangement of the regions in the embodiment of the present application;
fig. 3 is a schematic structural diagram of a defense system of a low-altitude aircraft according to a second embodiment of the present application.
Detailed Description
Reference will now be made in detail to embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application.
The following describes a low-altitude aircraft defense system according to an embodiment of the present application with reference to the drawings.
Fig. 1 is a schematic structural diagram of a defense system of a low-altitude aircraft according to an embodiment of the present application.
As shown in fig. 1, the low-altitude aircraft defense system may include: a detection radar 110, a video surveillance unit 120, a jamming unit 130, and a surveillance center platform 140.
The detection radar 110 is configured to scan a first area to detect a low-altitude aircraft appearing in the first area, and acquire position information of the low-altitude aircraft, where the first area includes at least one second area.
In this application embodiment, low-altitude aircraft can be for the flight target of small-size fixed rotor aircraft, helicopter, unmanned aerial vehicle, hovercar, flight packing box etc. below 3000 meters true height, and wherein, unmanned aerial vehicle can be for small-size fixed wing unmanned aerial vehicle, many rotor unmanned aerial vehicle, "bee colony" unmanned aerial vehicle etc. does not do the restriction to this.
In the embodiment of the present application, the first area is preset, and may be set according to the actual demand of the user and a specific application scenario, for example, the first area may be an office area, a residential activity area, a people flow dense area, and the like, which is not limited thereto. For example, when the defense system for a low-altitude aircraft is applied to a station with dense crowds, the first area may be an area including the entire station and a predetermined range around the station.
In the embodiment of the present application, the number of the detection radars 110 is at least one, and when the number of the detection radars 110 is one, the detection radar 110 may be located in the center of the first area, the azimuth coverage range is 360 degrees, and the scanning area covers the first area, for example, the detection range may be 500 meters to 10 kilometers, that is, the detection distance may be 500 meters to 10 kilometers. When the number of the detection radars 110 is plural, the positions where the plural detection radars 110 are disposed are not limited, but the scanning areas of the plural detection radars 110 need to cover the first area.
In the embodiment of the present application, the detection radar 110 is configured to detect a low-altitude aircraft in a first area, so as to obtain position information of the low-altitude aircraft. It should be noted that, the detection radar 110 may also obtain flight state information of the low-altitude aircraft, where the flight state information includes a distance between the low-altitude aircraft and the detection radar 110, and an azimuth angle and a pitch angle of the low-altitude aircraft.
As a possible implementation manner, since the ground interference of the Ku band is very small, and the Ku band has a high frequency, generally between 12.5 GHz and 18GHz, and is not easily interfered by microwave radiation, the requirement of the detection radar 110 on the receiving environment is greatly reduced, in this application, the operating frequency band of the detection radar 110 may be the Ku band, or the operating frequency band of the detection radar 110 may also be an X band, where the X band is a radio wave band having a frequency of 8GHz to 12 GHz.
And the video monitoring device 120 is used for tracking the low-altitude aircraft according to the position information of the low-altitude aircraft and displaying the video image of the low-altitude aircraft through the display.
In this embodiment, after the detection radar 110 obtains the position information of the low-altitude aircraft, the video monitoring device 120 may track the low-altitude aircraft in real time according to the position information of the low-altitude aircraft, and display a video image of the low-altitude aircraft through the display, so that a relevant worker may observe the low-altitude aircraft in real time through the video image.
As a possible implementation manner, the video monitoring apparatus 120 may be a photoelectric tracker, which includes a camera, a laser lighting assembly, a universal variable-speed outdoor console, a multifunctional decoder, and a display, and tracks the low-altitude aircraft according to the position information of the low-altitude aircraft, and displays a video image of the low-altitude aircraft through the display. Namely, in the application, the low-altitude aircraft can be captured, tracked and locked by the photoelectric tracker.
The range of the azimuth rotation angle of the photoelectric tracker is 0-360 degrees, the working frequency band of the photoelectric tracker can be an infrared frequency band, and the search range of the photoelectric tracker can be 50 meters to 3 kilometers.
And the interference device 130 is configured to send, through the transmit antenna array, interference signals of multiple operating frequency bands to the second area when the position information of the low-altitude aircraft is in the second area, where the interference signals are used to interfere with a communication link of the low-altitude aircraft.
In the embodiment of the present application, the at least one second region is also preset, for example, the at least one second region may be arranged inside the periphery of the first region.
In the embodiment of the present application, the interference device 130 refers to a device that emits or forwards an electronic interference signal, and the interference device 100 may be a fixed interference device, or may also be a handheld interference device, such as a handheld interference gun, which is not limited in the present application. Wherein, the interference distance of the interference device 130 is not less than 2 kilometers.
In this embodiment of the application, when the position information of the low-altitude aircraft is in the second area, the interference device 130 may interfere with the low-altitude aircraft, and transmit interference signals of a plurality of working frequency bands to the second area through the transmit antenna array, where the interference signals are used to interfere with a communication link of the low-altitude aircraft, so that the low-altitude aircraft cannot be positioned, communicate, and lose control, thereby driving the low-altitude aircraft to exit the second area or forcing the low-altitude aircraft to forcibly land.
In the embodiment of the present application, in order to implement multi-directional interference and directional interference on the low-altitude aircraft, the interference device 130 may generate electronic interference signals with different frequencies. Specifically, the interference device 130 may send interference signals of multiple operating frequency bands to the second area through the transmit antenna array to interfere with the communication link of the low-altitude aircraft, so that the low-altitude aircraft cannot be positioned and communicate, and the low-altitude aircraft is forced to land or return.
The plurality of working frequency bands can be set according to requirements, for example, the working frequency bands can be a Beidou satellite navigation System B1 frequency band, a Global Positioning System (GPS for short) frequency band (for example, a civil GPS frequency band, such as a working frequency band of a vehicle-mounted navigator and a working frequency band of a driving recorder), and a Wireless Fidelity (WiFi for short).
As a possible implementation manner, in order to implement omnidirectional interference and directional interference on the low-altitude aircraft, the multiple operating frequency bands may cover the full frequency band, for example, the multiple frequency bands may include: 1300MHz 810-.
And the monitoring center platform 140 is in mutual communication with the detection radar 110, the video monitoring device 120 and the interference device 130, and the monitoring center platform 140 is configured to generate alarm information when the position information of the low-altitude aircraft is in the second area, generate a first control instruction according to the alarm information, and send the first control instruction to the interference device 130, where the first control instruction is used to control the interference device 130 to be turned on and turned off.
In the embodiment of the application, when the monitoring platform 140 determines that the low-altitude aircraft is located in the second area according to the position information of the low-altitude aircraft acquired by the detection radar 110, alarm information may be generated to remind relevant workers, wherein the alarm information may be in the form of sound, light, characters, and the like. Meanwhile, a first control instruction may be generated according to the alarm information, and the first control instruction may be sent to the interference device 130. Correspondingly, after the interference device 130 receives the first control instruction, the device may be turned on according to the first control instruction to perform multi-directional interference on the low-altitude aircraft.
Or, the first control instruction may also be used to control the interference device 130 to transmit an interference signal to interfere with the low-altitude aircraft, and after receiving the first control instruction, the interference device 130 may directly send the interference signals of the multiple operating frequency bands to the second area according to the first control instruction.
The defense system for the low-altitude aircraft comprises a detection radar, a video monitoring device, a display, an interference device, a monitoring center platform, a communication link and a communication link, wherein the communication link, the communication link and the communication link are connected in sequence, the monitoring center platform is used for generating alarm information when the position information of the low-altitude aircraft is in a second area, the monitoring center platform is used for generating a first control instruction according to the alarm information, and the first control instruction is sent to the interference device, the first control instruction is used for controlling the interference device to be turned on and off. Therefore, after the low-altitude aircraft enters the second area, the interference device carries out multi-directional interference on the low-altitude aircraft, so that the low-altitude aircraft cannot be positioned and communicated, and the low-altitude aircraft is forced to land or return.
It is understood that, in practical applications, the flying target entering the first area may not be a low-altitude aircraft, for example, a bird, a kite, or other flying object, and at this time, the detection radar 110 can detect the flying target, but it cannot be determined whether the flying target is a low-altitude aircraft, and therefore, in order to improve the defense accuracy of the low-altitude aircraft, the flying target detected by the detection radar 110 needs to be identified to determine whether the flying target is a low-altitude aircraft.
As a possible implementation, the flight target may be identified manually. Specifically, after the detection radar 110 detects and acquires the position information of the flying target, the position information of the flying target may be sent to the monitoring center platform 140, and the monitoring center platform 140 may send the position information of the flying target to the video monitoring device 120, so that the video monitoring device 120 tracks the low-altitude aircraft according to the position information of the low-altitude aircraft. Meanwhile, the video monitoring device 120 may also display a video image of the low-altitude aircraft through a display, and a relevant worker may determine whether the flying target entering the first area is the low-altitude aircraft through the video image displayed by the video monitoring device 120, if so, notify the monitoring center platform 140 that the flying target is the low-altitude aircraft, and when the monitoring center platform 140 determines that the low-altitude aircraft is located in the second area according to the position information of the low-altitude aircraft, may send a first control instruction to the interfering device to interfere with the low-altitude aircraft.
As another possible implementation, whether the flight target is a low-altitude aircraft or not can be determined based on an image recognition technology. Specifically, the monitoring center platform 140 may acquire a video image from the video monitoring apparatus 120, perform image detection on the video image to determine whether the video image includes a low-altitude aircraft, for example, may detect the video image based on an image recognition technology of deep learning, for example, may acquire a training image, label the low-altitude aircraft in the training image, train a recognition model with the labeled training image, recognize the video image according to the trained recognition model, and may determine whether the video image includes the low-altitude aircraft, if so, when it is determined that the low-altitude aircraft is in the second area according to the position information of the low-altitude aircraft, the monitoring center platform 140 may send a first control instruction to the interfering apparatus to interfere with the low-altitude aircraft.
It should be noted that when it is determined that the flying target is not a low-altitude aircraft, the flying target may not be defended, and the flying target present in the first area continues to be detected by the detection radar 110, and whether the flying target is a low-altitude aircraft is identified by the above method, until the flying target is identified as a low-altitude aircraft, the low-altitude aircraft may be defended by the low-altitude aircraft defense system.
As a possible implementation manner, the first area may further include a third area, for example, referring to fig. 2, the third area 21 may be disposed at a central position of the first area 20, at least one second area 22 is disposed along a periphery of the third area 21, and a safety level of the third area 21 is higher than that of the second area 22. For example, the center position of the first region may be set as a dangerous region, that is, the dangerous region is a third region, and four interference regions may be provided on the outer periphery of the third region as the second region.
For example, when the defense system for a low-altitude aircraft is applied to a station with dense crowds, the first area may be an area including the whole station and a peripheral preset range of the station, the third area may be the whole station area, and the second area may be the peripheral area of the station.
It can be understood that, when the low-altitude aircraft is in the second region, a plurality of device 130 that disturb carry out all-round interference to the low-altitude aircraft, fail to force the low-altitude aircraft to descend or return to the journey, at this moment, the low-altitude aircraft probably flies to the third region, because the security level in third region is higher, consequently, can carry out the laser to the low-altitude aircraft and strike, damage low-altitude aircraft organism or key position by laser, thereby make the low-altitude aircraft crash or lose flight ability, in order to prevent that the low-altitude aircraft from carrying out illegal detection, terrorism etc. to the third region, can effectively improve the factor of safety in third region, ensure the safety of third region orderly.
Specifically, referring to fig. 3, on the basis of the embodiment shown in fig. 1, the low-altitude aircraft defense system may further include: a laser transmitter 150.
Wherein, the laser transmitter 150 is used for transmitting a laser beam to hit down the low-altitude aircraft when the position information of the low-altitude aircraft is in the third area.
In this application embodiment, when the positional information of low-altitude aircraft is in the third region, can be through laser emitter 150 transmission laser beam to hit down this low-altitude aircraft, can carry out the laser through laser emitter 150 and strike low-altitude aircraft, damage low-altitude aircraft organism or key part by laser, thereby make the low-altitude aircraft crash or lose flight ability, in order to hit down this low-altitude aircraft.
The working waveband of the laser transmitter 150 can be 1 micrometer, the interference distance is not less than 2 kilometers, and the damage distance is not less than 500 meters. For example, when the flying height of the low-altitude aircraft is greater than 2 kilometers, the laser beam emitted by the laser emitter 150 can interfere with the flight of the low-altitude aircraft, and when the flying height of the low-altitude aircraft is less than 500 kilometers, the laser beam emitted by the laser emitter 150 can damage the body or key parts of the low-altitude aircraft, so that the low-altitude aircraft crashes or loses flight ability to knock down the low-altitude aircraft.
The monitoring center platform 140 is further configured to communicate with the laser transmitter 150, generate a second control instruction when the position information of the low-altitude aircraft is in the third area, and send the second control instruction to the laser transmitter 150, where the second control instruction is used to control the laser transmitter 150 to be turned on and turned off.
In this embodiment of the application, when the monitoring platform 140 determines that the low-altitude aircraft is located in the third area according to the position information of the low-altitude aircraft acquired by the detection radar 110, a second control instruction may be generated, and the second control instruction is sent to the laser emitter 150, and correspondingly, after the laser emitter 150 receives the second control instruction, the device may be started according to the second control instruction, and laser shock is performed on the low-altitude aircraft.
Or, the second control instruction may also be used to control the laser emitter 150 to emit a laser beam to the low-altitude aircraft, and after the laser emitter 150 receives the second control instruction, the laser shock may be performed on the low-altitude aircraft according to the second control instruction.
As a possible implementation manner, the laser transmitter 150 may further include an automatic focusing device, after the laser transmitter 150 receives a second control instruction transmitted by the monitoring center platform 140, and after the device is turned on, the dynamic focusing mode may be entered to focus and lock the low-altitude aircraft, and then the laser transmitter may transmit a high-power laser beam to damage the body or key parts of the low-altitude aircraft, so that the low-altitude aircraft crashes or loses flight capability to knock down the low-altitude aircraft, thereby preventing the low-altitude aircraft from performing illegal detection, attack and the like on a third area, effectively improving the safety factor of the third area, and ensuring the safety and order of the third area.
As an example, under typical atmospheric conditions with atmospheric visibility greater than 5 km, temperature of 25 ℃ and humidity of 80%, the warning capability of the low-altitude aircraft defense system of the embodiment of the present application is as follows: the working frequency band of the detection radar is an X wave band, and the detection range is 500 meters to 10 kilometers; the working frequency band of the photoelectric tracker is an infrared frequency band and is 1 micron, and the search range is 50 meters to 3 kilometers; the integrated probing frequency is greater than or equal to 96%.
Tracking ability: the tracking distance is not less than 2.5 kilometers; the tracking distance is not less than 2.5 kilometers; the coarse tracking precision is less than or equal to 0.3 mrad (3 sigma); the fine tracking accuracy is less than or equal to 10 μ rad (3 σ).
Interference capability: the electronic interference working frequency band of the interference device is a Beidou satellite navigation system B1 frequency band, a GPS frequency band and a WiFi frequency band, the electronic interference distance is not less than 2 kilometers, and the electronic interference range is as follows: satellite navigation interference is less than or equal to 15 degrees multiplied by 15 degrees (3dB range); remote link interference is less than or equal to 10 degrees by 10 degrees (3dB range).
The hitting ability: the laser interference and damage working wave band of the laser transmitter is 1 micron, the laser interference distance is not less than 2 kilometers, the laser damage distance is not less than 500 meters, the maximum continuous hitting time of a single laser damage is 60 seconds, the hitting response time is less than or equal to 6 seconds, and the comprehensive hitting success probability is greater than or equal to 96%.
System air condition processing capacity: not less than 30 low-altitude aircrafts.
The multi-target protection capability of the system is as follows: not less than 3 low-altitude aircrafts.
The system target information updating period is as follows: a radar detection update period is less than or equal to 6 seconds; the photoelectric detection updating period is less than or equal to 6 seconds; the video surveillance update period is less than or equal to 5 seconds.
The system communication capability: the communication distance between the 4G base station and the gateway is more than or equal to 3 kilometers (urban area); the working frequency range of the trunking communication is 350-370 MHz; the cluster communication distance is greater than or equal to 3 kilometers (urban area).
The system positioning, orientation and timing capabilities are as follows: positioning accuracy (relative base station): the plane is less than or equal to 5 cm (1 sigma), and the height is less than or equal to 10 cm (1 sigma); the orientation precision (base length 6 m) is less than or equal to 0.03 ° (1 σ); the stabilization time is less than or equal to 1 hour; the time service precision is less than or equal to 50 nanoseconds; the horizontal two-dimensional attitude precision is less than or equal to 0.003 degrees; the positioning accuracy of the intelligent terminal is as follows: the plane is less than or equal to 10m (1 sigma) and the height is less than or equal to 10m (1 sigma).
Mobility (vehicle-mounted); the vehicle carrying vehicle has no leakage under the condition of rainstorm; the equipment outside the cabin is provided with a rain cover and cloth; under the conditions of medium rain, medium snow and the like (including medium rain and medium snow), system power guarantee equipment, finger control equipment, fire control equipment and communication equipment can work; the unfolding time is not more than 4 hours after the membrane is in place; the time for entering a working state after the expansion is not more than 4 hours; the withdrawal time is not more than 4 hours; the maximum speed of the transport capacity on the second level road is 80 km/h.
As an example, a small-sized fixed wing drone (a typical target: Radar Cross Section (RCS) ═ 0.1m2) and a multi-rotor drone (a typical target: RCS ═ 0.01m2) are defended, the protection area of the system is greater than or equal to 4 square kilometers, and the protection height of the system is greater than 500 meters; the number of the system vehicle carriers is 50; the warning means is X wave band, infrared and visible light; the tracking means is infrared and visible light; the electronic interference effect comprises driving away and forced landing; the laser interference effect comprises suppression and blindness; the laser damage effect comprises candle burning and crash; the tracking distance is 50 meters to 2.5 kilometers; the comprehensive detection probability is greater than or equal to 96%; the power consumption of the command control vehicle equipment is less than or equal to 12 kilowatts (including air conditioning, lighting and the like); the power consumption of the single comprehensive protection vehicle device is less than or equal to 75 kilowatts (including air conditioning, illumination and the like); the Mean Time Between Failures (MTBF) of the system is larger than or equal to 168 hours, and the Mean Time To Repair (MTTR) of the system is smaller than or equal to 2 hours; working temperature: the temperature of the working equipment outside the cabin is-30 ℃ to +50 ℃, and the temperature of the working equipment inside the cabin is 5 ℃ to +35 ℃; the storage temperature of the system is-30 ℃ to +55 ℃.
When the detection radar works, electromagnetic radiation has no influence on civil mobile communication and navigation, and is harmless to workers in vehicle-carrying equipment; when the communication equipment works, the electromagnetic radiation has no influence on civil communication and navigation, and is harmless to workers in the vehicle-carrying equipment; the detection laser and the ranging laser are safe to the eyes outside the distance of 200 m; the damage laser has no influence on civil aviation airspace above 600 m; when the electronic interference works, the electromagnetic radiation does no harm to workers in the vehicle; the working noise of the system is less than or equal to 86dB (1 meter away from a power station and oil engine equipment).
In the description herein, reference to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
Any process or method descriptions in link diagrams or otherwise described herein may be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing steps of a custom logic function or process, and the scope of the preferred embodiments of the present application includes additional implementations in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the embodiments of the present application.
The logic and/or steps represented in the block diagrams or otherwise described herein, such as an ordered listing of executable instructions that can be considered to implement logical functions, can be embodied in any computer-readable medium for use by or in connection with an instruction execution system, apparatus, or device, such as a computer-based system, processor-containing system, or other system that can fetch the instructions from the instruction execution system, apparatus, or device and execute the instructions. For the purposes of this description, a "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of the computer-readable medium would include the following: an electrical connection (electronic device) having one or more wires, a portable computer diskette (magnetic device), a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). Additionally, the computer-readable medium could even be paper or another suitable medium upon which the program is printed, as the program can be electronically captured, via for instance optical scanning of the paper or other medium, then compiled, interpreted or otherwise processed in a suitable manner if necessary, and then stored in a computer memory.
It should be understood that portions of the present application may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. If implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.
It will be understood by those skilled in the art that all or part of the steps carried by the method for implementing the above embodiments may be implemented by hardware related to instructions of a program, which may be stored in a computer readable storage medium, and when the program is executed, the program includes one or a combination of the steps of the method embodiments.
In addition, functional units in the embodiments of the present application may be integrated into one processing module, or each unit may exist alone physically, or two or more units are integrated into one module. The integrated module can be realized in a hardware mode, and can also be realized in a software functional module mode. The integrated module, if implemented in the form of a software functional module and sold or used as a stand-alone product, may also be stored in a computer readable storage medium.
The storage medium mentioned above may be a read-only memory, a magnetic or optical disk, etc. Although embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application, and that variations, modifications, substitutions and alterations may be made to the above embodiments by those of ordinary skill in the art within the scope of the present application.
Claims (10)
1. A low-altitude aircraft defense system, comprising:
the system comprises a detection radar, a first processing unit and a second processing unit, wherein the detection radar is used for scanning a first area to detect a low-altitude aircraft appearing in the first area and acquiring position information of the low-altitude aircraft, and the first area comprises at least one second area;
the video monitoring device is used for tracking the low-altitude aircraft according to the position information of the low-altitude aircraft and displaying a video image of the low-altitude aircraft through a display;
the interference device is used for sending interference signals of a plurality of working frequency bands to the second area through the transmitting antenna array when the position information of the low-altitude aircraft is in the second area, and the interference signals are used for interfering the communication link of the low-altitude aircraft;
the monitoring center platform, the monitoring center platform with survey the radar, the video monitoring device with interference device intercommunication, the monitoring center platform is used for being in the position information of low-altitude aircraft generates alarm information when being in the second region, and according to alarm information generates first control command, and will first control command send to the interference device, wherein, first control command is used for controlling opening and closing of interference device.
2. The low-altitude aircraft defense system of claim 1, wherein the first zone further comprises a third zone, the low-altitude aircraft defense system further comprising: the laser transmitter is used for transmitting a laser beam to knock down the low-altitude aircraft when the position information of the low-altitude aircraft is in the third area;
the monitoring center platform is further used for communicating with the laser emitter, generating a second control instruction when the position information of the low-altitude aircraft processes the third area, and sending the second control instruction to the laser emitter, wherein the second control instruction is used for controlling the laser emitter to be turned on and turned off.
3. The low-altitude aircraft defense system according to claim 2, characterized in that the third zone is arranged in a central position of the first zone, the at least one second zone is arranged along the periphery of the third zone, and the third zone has a higher safety level than the second zone.
4. The low-altitude aircraft defense system according to any one of claims 1 to 3, characterized in that the operating frequency band of the detection radar is Ku band or X band.
5. The low-altitude aircraft defense system according to any one of claims 1 to 3, characterized in that the detection range of the detection radar is 500 meters to 10 kilometers.
6. The low-altitude aircraft defense system of claims 1-3, the plurality of operating frequency bands comprising a Beidou satellite navigation System B1 frequency band, a satellite positioning System GPS frequency band, a Wireless Fidelity (WiFi) frequency band.
7. The low-altitude aircraft defense system of claims 1-3, wherein the interfering device has an interference distance of no less than 2 kilometers.
8. The low-altitude aircraft defense system of claim 2, wherein the laser transmitter has an operating band of 1 micron.
9. The low-altitude aircraft defense system of claim 2, wherein the laser transmitter has a jamming distance of no less than 2 kilometers.
10. The low-altitude aircraft defense system of claim 2, wherein the laser transmitter has a damage distance of not less than 500 meters.
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| CN113030978A (en) * | 2021-02-07 | 2021-06-25 | 中国民用航空总局第二研究所 | Airport ultra-low altitude bird detection and intelligent warning system and method |
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| CN113030978A (en) * | 2021-02-07 | 2021-06-25 | 中国民用航空总局第二研究所 | Airport ultra-low altitude bird detection and intelligent warning system and method |
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