Low-altitude flight detection device and control system thereof

Abstract

The utility model relates to the technical field of radio detection, in particular to a low-altitude flight detection device and a control system thereof, the low-altitude flight detection device comprises a first device and a plurality of second devices, and the first device is in communication connection with the plurality of second devices; the second device comprises a first shell, a first cavity is formed in the first shell, an antenna assembly is arranged on one side of the first cavity, a data processing assembly is arranged in the first cavity, the data processing assembly is used for obtaining baseband echo data, and first heat dissipation assemblies are further arranged on the periphery of the first shell. The utility model aims to solve the technical problems of complex structure and difficulty in heat dissipation of the existing integrated low-altitude flight detection device.

Description

Technical Field

[0001] This utility model relates to the field of radio detection technology, and more specifically, to a low-altitude flight detection device and its control system. Background Technology

[0002] Currently, the widespread use of low-altitude aircraft poses a serious challenge to public safety and aviation safety. Low-altitude flight safety monitoring systems need to accurately monitor the position, altitude, speed, and other flight status information of low-altitude aircraft in real time, and based on this, formulate sound emergency response procedures and measures for low-altitude flight. Among numerous detection methods, radar detection equipment is considered a core component of low-altitude flight safety monitoring systems due to its significant advantages such as wide detection range, strong real-time performance, high accuracy, and strong weather adaptability.

[0003] Traditional mechanically scanned radars achieve scanning in different directions by mechanically rotating the antenna to change its orientation. This method results in a slow scanning speed, making it difficult to meet the real-time tracking requirements of fast-moving targets in low-altitude economic activities. Its complex mechanical structure leads to a large workload and high cost of maintenance, as well as low reliability, posing potential risks to low-altitude economic activities. While phased array electronically scanned radar overcomes some of the shortcomings of mechanically scanned radar, it still faces numerous challenges. It contains a large number of antenna elements, phase shifters, amplifiers, signal processors, and other hardware, requiring real-time processing of massive amounts of radar echo data. The complex signal processing algorithms and extremely high heat dissipation make air-cooling or liquid-cooling methods problematic. Air cooling is susceptible to dust and debris, leading to reduced heat dissipation or even fan failure, and it also generates significant noise, impacting the environment and user experience. In high-humidity environments, it can easily cause electrical short circuits. Liquid cooling, on the other hand, requires complex piping, water pumps, and radiators, increasing system complexity and cost. Its piping installation and maintenance are demanding, and there is a risk of leakage at pipes and joints. In low-temperature environments, the coolant may freeze, causing pipe ruptures and pump damage. Therefore, neither air-cooled nor liquid-cooled phased array electronically scanned radar can meet the reliability requirements for continuous, long-term operation in outdoor environments. Utility Model Content

[0004] The purpose of this invention is to provide a low-altitude flight detection device and its control system to solve the technical problems of complex structure and difficult heat dissipation in existing integrated low-altitude flight detection devices in the background art.

[0005] To achieve the above objectives, the first aspect of the present invention provides a low-altitude flight detection device, including a first device and several second devices, wherein the first device and several second devices are communicatively connected; the second devices include a first housing, a first cavity is provided inside the first housing, an antenna assembly is provided on one side of the first cavity, a data processing assembly is provided inside the first cavity, the data processing assembly is used to acquire baseband echo data, and a first heat dissipation assembly is also provided around the first housing.

[0006] Furthermore, the antenna assembly includes a second housing and an antenna. The second housing is disposed on one side of the first housing and is fixedly connected to the first housing. The second housing has a second cavity for mounting the antenna inside.

[0007] Furthermore, the antenna assembly also includes a first cover plate, which is disposed on the side of the antenna away from the first housing, and the first cover plate is sealed to the second housing.

[0008] Furthermore, a second heat dissipation component is provided around the second housing.

[0009] Furthermore, an external connector is provided at the bottom of the first cavity, and the external connector is electrically connected to the data processing component.

[0010] Furthermore, the data processing component includes a first control module and a frequency conversion module, and the first control module and the frequency conversion module are fixedly connected.

[0011] Furthermore, the data processing component also includes a second cover plate, which is fixedly connected to the side of the first housing away from the antenna assembly. The side of the second cover plate near the first cavity is fixedly connected to the first control module. A third heat dissipation component is also provided on the side of the second cover plate away from the first control module.

[0012] Furthermore, the frequency conversion module is communicatively connected to the first control module and the antenna assembly. The frequency conversion module includes a transmitting channel and four receiving channels. The transmitting channel is electrically connected to the four receiving channels, and the four receiving channels are connected in parallel.

[0013] Furthermore, the first cavity has an annular sealing groove on the side near the second cover plate, and a sealing strip is provided in the annular sealing groove.

[0014] The second aspect of this utility model provides a control system for a low-altitude flight detection device, including the low-altitude flight detection device described in the first aspect of this utility model, comprising a second control module and a third control module disposed within a first device, wherein the second control module, the third control module, and the data processing component are communicatively connected.

[0015] The beneficial effects of this utility model include:

[0016] 1. The low-altitude flight detection device provided by this utility model, from the perspective of heat dissipation, abandons the complex structure of air cooling and water cooling in traditional phased array electronically scanned radar. Through a split architecture, the low-altitude flight device is designed as a first device and a second device. The second device can work stably by simply air cooling through the first heat dissipation component, avoiding the trouble of frequent maintenance of vulnerable parts such as fans and water pipes, and reducing maintenance costs and difficulties. On the other hand, several second devices can work together to enhance target resolution, positioning and identification accuracy. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments of this utility model will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A side view of the low-altitude flight detection device provided in this embodiment of the utility model;

[0019] Figure 2 A side front view structural diagram of the low-altitude flight detection device provided in this embodiment of the utility model;

[0020] Figure 3 A schematic diagram of the antenna assembly of the low-altitude flight detection device provided in this embodiment of the utility model;

[0021] Figure 4 This is a schematic diagram of the structure of the data processing component provided in an embodiment of the present utility model;

[0022] Figure 5 A schematic diagram of the structure of the first housing provided in an embodiment of this utility model;

[0023] Figure 6 A schematic diagram illustrating the composition of the low-altitude flight detection device provided in this embodiment of the utility model;

[0024] Figure 7 This is a schematic diagram of the internal components of the second device provided in an embodiment of the present utility model;

[0025] Figure 8 This is a schematic diagram of the structure of the frequency converter module provided in an embodiment of the present utility model;

[0026] Figure 9A schematic diagram of the control system of the low-altitude flight detection device provided in this embodiment of the utility model;

[0027] Icons: 100-First housing, 110-First cavity, 120-First heat dissipation assembly, 130-First control module, 140-Frequency conversion module, 141-Transmit channel, 142-Receive channel, 150-Second cover plate, 160-Sealing strip, 170-External connector, 180-Third heat dissipation assembly, 200-Second housing, 210-Antenna, 220-Second cavity, 230-First cover plate, 240-Second heat dissipation assembly. Detailed Implementation

[0028] The technical solutions of the present invention will now be described with reference to the accompanying drawings in the embodiments of the present invention.

[0029] It should be noted that similar reference numerals and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. It should be noted that the terms "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the figures, or the orientation or positional relationship commonly used when the utility model product is in use. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0030] Please see Figures 1 to 6As shown, the first aspect of the present invention provides a low-altitude flight detection device, including a first device and several second devices, wherein the first device and several second devices are communicatively connected; the second devices include a first housing 100, a first cavity 110 is provided inside the first housing 100, an antenna assembly is provided on one side of the first cavity 110, a data processing assembly is provided inside the first cavity 110, the data processing assembly is used to acquire baseband echo data, and a first heat dissipation assembly 120 is also provided around the first housing 100. Specifically, the low-altitude aircraft detection device consists of two parts: a first device and a second device. One set of the first device can simultaneously connect to and adapt to multiple sets of the second device. Optical fiber is preferred for communication commands and baseband echo data transmission between the first and second devices. An antenna assembly on one side of the first cavity 110 is used to receive and transmit electromagnetic signals to capture various characteristic information of low-altitude aircraft, such as position and speed-related echo signals. The data processing component is used to quickly process the received signals and obtain baseband echo data. The first heat dissipation assembly 120 around the first housing 100 uses equidistant toothed heat dissipation plates. This design utilizes natural wind flow to increase the heat dissipation area and effectively dissipate the heat generated by the data processing component. Simultaneously, the second device adopts a streamlined or smooth low-drag shape design to avoid turbulence and excessive drag caused by sharp corners under strong winds. Its frame structure uses high-strength steel, aluminum alloy, and other materials to ensure stable operation in complex outdoor environments. In practical applications, such as... Figure 6 As shown, the first device is installed indoors in a computer room, while several second devices are distributed outdoors. These second devices work together to detect targets over a wide area. The detection arrays of the second devices at different locations focus on the target from multiple angles, each collecting data and transmitting it back to the first device. The first device integrates the multi-source information, achieving data fusion and significantly improving target resolution, thus enabling accurate target location and identification. Even if one of the second devices malfunctions, the remaining nodes continue to operate, ensuring seamless low-altitude monitoring thanks to the system's robust fault-tolerance mechanism.

[0031] The low-altitude flight detection device provided in this embodiment is an improvement on the traditional phased array electronically scanned radar, designed to meet the application requirements of low-altitude flight safety monitoring systems. On one hand, the signal processing hardware unit, which generates significant heat dissipation in traditional phased array electronically scanned radar, is separated from the antenna and other radio frequency components. This separated unit operates as a first device in a computer room, powered by an air conditioner for cooling. On the other hand, the data processing components are integrated into a single design and installed outdoors as a second device. This separate design avoids the significant heat dissipation generated during installation, allowing the second device to operate normally under natural air cooling conditions. This avoids the problems of poor heat dissipation and insufficient stability during continuous outdoor operation associated with traditional air or water cooling systems, and eliminates the need for frequent maintenance and repair of easily damaged components such as fans, water pipes, and water pumps.

[0032] Preferably, the antenna assembly includes a second housing 200 and an antenna 210. The second housing 200 is disposed on one side of the first housing 100 and fixedly connected to the first housing 100. The second housing 200 has a second cavity 220 for mounting the antenna 210. The antenna assembly also includes a first cover plate 230, which is disposed on the side of the antenna 210 away from the first housing 100. The first cover plate 230 is sealed to the second housing 200. A second heat dissipation assembly 240 is also provided around the second housing 200. Specifically, for the antenna assembly, the second housing 200 serves as a load-bearing component and is stably disposed on one side of the first housing 100. Bolts or welding can be used to ensure a tight connection between the two. The first cover plate 230 uses a sealing material, such as a rubber sealing strip or sealant, to achieve a sealed connection with the second housing 200, preventing dust, moisture, etc. from entering and protecting the antenna 210 and its internal components from harsh outdoor environments. The second heat dissipation component 240 around the second housing 200 adopts a heat dissipation principle adapted to the first heat dissipation component 120, which diffuses the heat generated by the antenna component to the outside of the device, and then carries away the heat with the help of natural wind. The second heat dissipation component 240 and the first heat dissipation component 120 work together to further optimize the overall heat dissipation efficiency of the device.

[0033] Preferably, the bottom of the first cavity 110 is also provided with an external connector 170, which is electrically connected to the data processing component. Specifically, the external connector 170 can be electrically connected to the data processing component by welding or crimping. From a power supply perspective, the external connector 170 preferably uses a DC+12V standard power supply. An appropriate power conversion module is provided outside the device to accurately convert the mains power or other input power into a stable +12V DC power, which is then connected to the external connector 170 via a power cable to stably power the data processing component and ensure its continuous operation. In terms of communication, an optical fiber LC interface is preferably used as the external communication interface. Inside the first cavity 110, the communication port of the data processing component is connected to the LC interface end of the external connector 170 through an optical fiber patch cord, and then connected to an external optical fiber network to achieve high-speed, low-loss data transmission, meeting the needs of low-altitude flight detection devices for transmitting large amounts of baseband echo data.

[0034] For preferred options, please refer to [link / reference]. Figure 7 and Figure 8 As shown, the data processing component includes a first control module 130 and a frequency conversion module 140, which are fixedly connected. The data processing component also includes a second cover plate 150, which is fixedly connected to the side of the first housing 100 away from the antenna assembly. The side of the second cover plate 150 near the first cavity 110 is fixedly connected to the first control module 130. A third heat dissipation component 180 is also provided on the side of the second cover plate 150 away from the first control module 130. The frequency conversion module 140 is communicatively connected to the first control module 130 and the antenna assembly. The frequency conversion module 140 includes a transmitting channel 141 and four receiving channels 142. The transmitting channel 141 and the four receiving channels 142 are connected... The four receiving channels 142 are electrically connected and connected in parallel. Specifically, the first control module 130 and the frequency conversion module 140 in the data processing component are closely arranged and can be fixedly connected by bolts or other means. The first control module 130 is configured to coordinate the operation of each part, receive external instructions, parse and distribute tasks, and perform preliminary processing and integration of the collected data. The transmitting channel 141 of the frequency conversion module 140 is used to accurately upconvert the intermediate frequency excitation signal to a high frequency signal suitable for space radiation, which is then radiated outward by the antenna array. The four receiving channels 142 are connected in parallel, which can simultaneously capture weak echo signals from low-altitude aircraft in different directions, and then downconvert these high-frequency echo signals to intermediate frequency. In addition, the data processing component also includes, for example, Figure 7The components shown include the TR assembly, beam control board, feed network, and sum / differentializer. The TR assembly, following instructions from the beam control board, quickly and accurately switches between transmit and receive signal channels, ensuring timely and accurate signal transmission. The beam control board calculates beam control angles, directs the antenna beam towards the target, and implements amplitude and phase control for each TR channel to optimize signal reception. The feed network distributes the excitation signal, ensuring each element of the antenna array receives appropriate energy, and efficiently synthesizes echo signal subarrays to enhance signal strength. The sum / differentializer synthesizes elevation and azimuth difference signals, providing crucial data for target localization and tracking, and can also work with antenna 210 to generate sidelobes. The stealth reference signal effectively suppresses sidelobe interference. In this embodiment, the second cover plate 150 is fixed to the side of the first housing 100 away from the antenna assembly and is closely connected to the first control module 130, providing protection for internal components and acting as a heat dissipation carrier. The third heat dissipation component 180 adopts the same configuration as the first heat dissipation component 120 and the second heat dissipation component 240, which will not be described again. The multi-channel frequency conversion module 140 in this embodiment, combined with precise beam control and signal synthesis, can effectively improve the detection accuracy, range and sensitivity of low-altitude aircraft and accurately capture fast-moving targets. The third heat dissipation component 180 further optimizes the heat dissipation performance of the device.

[0035] Preferably, the first cavity 110 has an annular sealing groove on the side near the second cover plate 150, and a sealing strip 160 is provided in the annular sealing groove. Specifically, the annular sealing groove is milled using precision machining on the side of the first cavity 110 of the second device near the second cover plate 150. The size and depth of the groove match the specifications of the sealing strip 160, ensuring that the sealing strip 160 is both securely embedded and fully exerts its sealing effect. The sealing strip 160 is preferably made of rubber. The combination of the annular sealing groove and the sealing strip 160 provides protection for the precision data processing components and control modules inside the first cavity 110, effectively preventing the intrusion of dust, moisture, and external impurities, and extending the service life of the equipment.

[0036] Please see Figure 9 As shown, the second aspect of the present invention provides a control system for a low-altitude flight detection device, including the low-altitude flight detection device described in the first aspect of the present invention, comprising a second control module and a third control module disposed within a first device, wherein the second control module, the third control module, and the data processing component are communicatively connected. Figure 9The antenna array, TR components, and other radio frequency components are generally described as the antenna front end. The first device sends control commands such as working mode and parameter configuration to the second device. The second device sends back equipment status monitoring information and baseband echo data, as well as beam pointing and timestamp information corresponding to the echo data to the first device. After receiving the control commands sent by the first device, the second device starts the intermediate frequency excitation signal generation, frequency point selection and beam pointing control, array beam transceiver timing control, and completes echo signal acquisition and digital down-conversion (DDC). The digitally down-converted baseband echo data and corresponding additional information are packaged and transmitted to the optical fiber interface. After receiving the baseband echo data, the first device performs signal and data processing to obtain the flight path information of all aircraft within the monitoring area, and then sends this flight path information to the low-altitude flight safety monitoring system. The second device sends a "heartbeat" frame to the first device every second to provide feedback on the health status and working conditions of each module within the device. In actual use, after the first device reads the baseband echo data at high speed through optical fiber, the second and third control modules work together to remove noise and analyze signal characteristics using existing signal processing algorithms. Then, combined with data processing algorithms, they perform multi-source data fusion analysis to accurately identify the flight path information of all aircraft within the monitoring area, and finally transmit this flight path information to the low-altitude flight safety monitoring system in real time.

[0037] It should be noted that the control programs for data communication, data processing, and data analysis in this utility model are all mature and conventional technologies in the prior art. Those skilled in the art can implement the application of this utility model based on the principles of the same functions in the prior art. This program part is not the innovation point of this utility model.

[0038] In addition to the above description, the following points need to be noted:

[0039] (1) The accompanying drawings of the embodiments of this disclosure only involve the structures involved in the embodiments of this disclosure. Other structures can be referred to the general design.

[0040] (2) Where there is no conflict, the embodiments of this disclosure and the features in the embodiments can be combined with each other to obtain new embodiments.

[0041] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. A low altitude flight detection apparatus, characterized by, The application relates to a low-altitude flight detection device, which comprises a first device and a plurality of second devices, and the first device is in communication connection with the plurality of second devices; the second device comprises a first shell, a first cavity is arranged in the first shell, an antenna assembly is arranged on one side of the first cavity, a data processing assembly is arranged in the first cavity, the data processing assembly is used for acquiring baseband echo data, and a first heat dissipation assembly is further arranged around the first shell.

2. The low altitude flight detection apparatus according to claim 1, wherein The antenna assembly comprises a second shell and an antenna, the second shell is arranged on one side of the first shell and is fixedly connected with the first shell, and a second cavity for mounting the antenna is arranged in the second shell.

3. The low altitude flight detection apparatus according to claim 2, wherein The antenna assembly further comprises a first cover plate, the first cover plate is arranged on the side, away from the first shell, of the antenna, and the first cover plate is sealingly connected with the second shell.

4. The low altitude flight detection apparatus according to claim 2, wherein The second shell is further provided with a second heat dissipation assembly around the second shell.

5. The low altitude flight detection apparatus according to claim 1, wherein The bottom of the first cavity is further provided with an external connector, and the external connector is electrically connected with the data processing assembly.

6. The low altitude flight detection apparatus according to any one of claims 1 to 5, wherein The data processing assembly comprises a first control module and a frequency conversion module, and the first control module is fixedly connected with the frequency conversion module.

7. The low altitude flight detection apparatus according to claim 6, wherein The data processing assembly further comprises a second cover plate, the second cover plate is fixedly connected to the side, away from the antenna assembly, of the first shell, the side, close to the first cavity, of the second cover plate is fixedly connected with the first control module, and the side, away from the first control module, of the second cover plate is further provided with a third heat dissipation assembly.

8. The low altitude flight detection apparatus according to claim 6, wherein The frequency conversion module is in communication connection with the first control module and the antenna assembly, the frequency conversion module comprises a transmitting channel and four receiving channels, the transmitting channel is electrically connected with the four receiving channels, and the four receiving channels are connected in parallel.

9. The low altitude flight detection apparatus according to claim 7, wherein The side, close to the second cover plate, of the first cavity is provided with an annular sealing groove, and a sealing strip is arranged in the annular sealing groove.

10. A control system for a low altitude flight detection apparatus, characterized by, The application further relates to a low-altitude flight detection device, which comprises a second control module and a third control module arranged in the first device, and the second control module, the third control module and the data processing assembly are in communication connection.

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