Short-range air defense radar ultra-low-altitude test route optimization method, device and terminal

Abstract

The invention discloses a short-range air defense radar ultra-low-altitude test route optimization method and device and a terminal, and belongs to the field of radar data processing, and the method comprises the steps: obtaining DEM data with the resolution of 30M in a test region, the DEM data with the resolution of 30M in the test region comprising a radar position, a radar elevation, a radar power coverage range and a target aircraft flight height; and establishing radar rectangular coordinate system data with a test area resolution of 30M by taking the radar position as an original point, carrying out modeling and calculation by adopting a radar elevation comparison method in a Python programming environment, carrying out intervisibility analysis on topographic conditions in an air route area to form a flight detection data set, and completing air route planning. According to the method, the terrain shielding model is established through high-precision terrain DEM data in the geographic information technology, the propagation path and shielding condition of radar beams are analyzed and calculated, the influence range and degree of terrain shielding on radar detection are predicted and evaluated, and the limit boundary characteristics of radar equipment are assessed to the maximum extent.

Description

Technical Field

[0001] The invention discloses a method, a device and a terminal for optimizing a short-range air defense radar ultra-low altitude test route, and belongs to the field of radar data processing. Background Art

[0002] Ultra-low-altitude penetration is an aircraft's attempt to avoid effective detection by enemy radar and ground-based air defense equipment. It makes full use of geographical advantages and radar detection shortcomings, including the natural obstruction of the earth's curvature and the detection blind spots formed by complex terrain, to quickly penetrate into the enemy's defense zone for a sudden and rapid strike, and quickly evacuate before the enemy's air defense equipment can react, greatly reducing the probability of the aircraft being detected, tracked, and shot down by the enemy, and performing combat missions in a covert and efficient manner. With the rapid iterative development of various types of small RCS, high-speed, and micro-unmanned aerial vehicles, ultra-low-altitude penetration will inevitably pose a major threat to short-range air defense radar equipment. Therefore, in the identification test and assessment of new short-range air defense equipment, ultra-low-altitude performance is the top priority among all indicators, and the precise planning of ultra-low-altitude test routes determines the scientificity, effectiveness, and adequacy of the test. Summary of the invention

[0003] In view of the defects in the ultra-low altitude route design in the short-range air defense radar test, the present invention proposes a short-range air defense radar ultra-low altitude test route optimization method, device and terminal, and applies high-precision digital geographic information technology to the design of radar flight test plan. The ultra-low altitude route can be designed efficiently, accurately and close to the limit, which effectively improves the scientificity and safety of the boundary condition assessment of radar equipment and provides strategic support for the actual combat application of the equipment.

[0004] The technical solution of the present invention is as follows:

[0005] According to a first aspect of an embodiment of the present invention, there is provided a method for optimizing a short-range air defense radar ultra-low altitude test route, comprising:

[0006] Acquire DEM data with a resolution of 30M in the test area, wherein the DEM data with a resolution of 30M in the test area includes: radar position, radar elevation, radar power coverage and target aircraft flight altitude;

[0007] Taking the radar position as the origin, a radar rectangular coordinate system data with a resolution of 30M in the test area is established. In the Python programming environment, the radar elevation angle comparison method is used for modeling and calculation, and the visibility analysis of the terrain conditions in the route area is performed to form a flight inspection data set to complete the route planning.

[0008] Preferably, the radar elevation angle comparison method is used for modeling and calculation, and the terrain conditions in the route area are analyzed for visibility to form a flight inspection data set to complete the route planning, including:

[0009] Taking the radar position as the origin and the radar power coverage as the detection pole diameter, traverse the elevation values ​​of each point in the DEM data, and determine whether the straightness of the radar power ray direction under the flight inspection requirements is met under the premise of being lower than the radar position height:

[0010] If yes, enter the corresponding points into the flight inspection route data set;

[0011] If no, proceed to the next step;

[0012] The radar power coverage is the detection radius, and the azimuth is the step length. The polar diameter is sampled in sequence at intervals of a step length ΔL, and the elevation values ​​corresponding to each point P1, P2, ... Pn in the digital DEM database of the area are traversed. The pitch angle of the target aircraft relative to the radar is determined according to the flight altitude of the target aircraft. The pitch angle of the corresponding point relative to the radar is obtained according to the elevation value corresponding to each point, and it is determined whether it is less than the pitch angle of the target aircraft relative to the radar. If so, the corresponding point is entered into the flight inspection route data set. If not, the judgment is repeated until all points are judged and the route planning is completed.

[0013] Preferably, determining the pitch angle of the target aircraft relative to the radar according to the flight altitude of the target aircraft includes:

[0014] The target aircraft's flight altitude is calculated by formula (1) to obtain the pitch angle of the target aircraft relative to the radar:

[0015]

[0016] Where: E 0 is the pitch angle of the target aircraft relative to the radar, h f is the target aircraft flight altitude, h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0017] Preferably, obtaining the pitch angle of the corresponding point relative to the radar according to the elevation value corresponding to each point includes:

[0018] The target aircraft's flight altitude is calculated by formula (2) to obtain the pitch angle of the target aircraft relative to the radar:

[0019]

[0020] Where: E p is the pitch angle of the target aircraft relative to the radar, For the direction The elevation of point P at time h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0021] According to a second aspect of an embodiment of the present invention, there is provided a short-range air defense radar ultra-low altitude test route optimization device, comprising:

[0022] An acquisition module is used to acquire DEM data with a resolution of 30M in the test area, and the DEM data with a resolution of 30M in the test area includes: radar position, radar elevation, radar power coverage and target aircraft flight altitude;

[0023] The analysis module is used to establish radar rectangular coordinate system data with a resolution of 30M in the test area with the radar position as the origin. In the Python programming environment, the radar elevation angle comparison method is used for modeling and calculation, and the visibility analysis of the terrain conditions in the route area is performed to form a flight inspection data set to complete the route planning.

[0024] Preferably, the analysis module is used to:

[0025] Taking the radar position as the origin and the radar power coverage as the detection pole diameter, traverse the elevation values ​​of each point in the DEM data, and determine whether the straightness of the radar power ray direction under the flight inspection requirements is met under the premise of being lower than the radar position height:

[0026] If yes, enter the corresponding points into the flight inspection route data set;

[0027] If no, proceed to the next step;

[0028] The radar power coverage is the detection radius, and the azimuth is the step length. The polar diameter is sampled in sequence at intervals of step length ΔL, and the elevation values ​​corresponding to each point P1, P2, ... Pn in the digital DEM database of the area are traversed. The pitch angle of the target aircraft relative to the radar is determined according to the flight altitude of the target aircraft. The pitch angle of the corresponding point relative to the radar is obtained according to the elevation value corresponding to each point, and it is judged whether it is less than the pitch angle of the target aircraft relative to the radar. If so, the corresponding point is entered into the flight inspection route data set. If not, the judgment is repeated until all points are judged and the route planning is completed.

[0029] Preferably, the analysis module is used to:

[0030] The target aircraft's flight altitude is calculated by formula (1) to obtain the pitch angle of the target aircraft relative to the radar:

[0031]

[0032] Where: E 0 is the pitch angle of the target aircraft relative to the radar, h fis the target aircraft flight altitude, h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0033] Preferably, the analysis module is used to:

[0034] The target aircraft's flight altitude is calculated by formula (2) to obtain the pitch angle of the target aircraft relative to the radar:

[0035]

[0036] Where: E p is the pitch angle of the target aircraft relative to the radar, For the direction The elevation of point P at time h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0037] According to a third aspect of an embodiment of the present invention, a terminal is provided, including:

[0038] one or more processors;

[0039] a memory for storing the one or more processor-executable instructions;

[0040] Wherein, the one or more processors are configured to:

[0041] Execute the method described in the first aspect of the embodiment of the present invention.

[0042] According to a fourth aspect of an embodiment of the present invention, a non-temporary computer-readable storage medium is provided. When instructions in the storage medium are executed by a processor of a terminal, the terminal is enabled to execute the method described in the first aspect of the embodiment of the present invention.

[0043] According to a fifth aspect of an embodiment of the present invention, an application product is provided. When the application product is running on a terminal, the terminal executes the method described in the first aspect of the embodiment of the present invention.

[0044] The beneficial effects of the present invention are:

[0045] The present invention provides a method, device and terminal for optimizing the ultra-low altitude test route of a short-range air defense radar. The method establishes a terrain shielding model through high-precision terrain DEM data in geographic information technology, analyzes and calculates the propagation path and shielding of the radar beam, predicts and evaluates the scope and degree of influence of terrain shielding on radar detection, comprehensively and quickly optimizes the design of the ultra-low altitude test route of the radar, and maximizes the assessment of the limit boundary characteristics of the radar equipment.

[0046] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 It is a flow chart of a method for optimizing a short-range air defense radar ultra-low altitude test route according to an exemplary embodiment.

[0048] Figure 2 It is a schematic block diagram of the structure of a short-range air defense radar ultra-low altitude test route optimization device according to an exemplary embodiment.

[0049] Figure 3 The present invention is a schematic block diagram of a terminal structure according to an exemplary embodiment. DETAILED DESCRIPTION

[0050] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0052] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] An embodiment of the present invention provides a method for optimizing a short-range air defense radar ultra-low altitude test route. The method is implemented by a terminal. The terminal may be a desktop computer or a laptop computer, etc. The terminal at least includes a CPU, etc.

[0054] Embodiment 1

[0055] Figure 1 The present invention is a flow chart of a method for optimizing a short-range air defense radar ultra-low altitude test route according to an exemplary embodiment. The method is used in a terminal and includes the following steps:

[0056] Step 101, obtain DEM data with a resolution of 30M in the test area, where:

[0057] The SRTM high-resolution digital DEM model includes radar image data with a total area of ​​more than 119 million square kilometers between 60° north latitude and 56° south latitude, covering more than 80% of the earth's land surface. SRTM has two common resolutions: 30m and 90m. Data with a resolution of 30m is usually better in quality and accuracy. This embodiment uses a mountain area with an area of ​​100km×100km, an elevation of less than 1000m, and a resolution of 30m for analysis and calculation. The DEM data with a resolution of 30M in the DEM data test area includes: radar position, radar elevation, radar power coverage, and target aircraft flight altitude.

[0058] Step 102, using the radar position as the origin to establish radar rectangular coordinate system data with a resolution of 30M in the test area, using the radar elevation angle comparison method to perform modeling and calculation in the Python programming environment, performing visibility analysis on the terrain conditions in the route area to form a flight inspection data set, and completing route planning, wherein:

[0059] Taking the radar position as the origin, the coordinate transformation of the area data to be calculated near the radar station is performed to convert it into the radar local rectangular coordinates, thereby establishing the radar rectangular coordinate system data with a test area resolution of 30M.

[0060] The premise of the test route design is that there is no terrain obstruction throughout the flight route to meet the requirements for qualified judgment of power and accuracy. Therefore, the visibility analysis of the terrain conditions in the route area is the key.

[0061] Taking the radar position as the origin and the radar power coverage as the detection pole diameter, traverse the elevation values ​​of each point in the DEM data, and determine whether the straightness of the radar power ray direction meets the flight inspection requirements under the premise of being lower than the radar position height:

[0062] If yes, enter the corresponding points into the flight inspection route data set;

[0063] If no, proceed to the next step;

[0064] The radar power coverage is the detection radius, and the azimuth is the step length. The polar diameter is sampled in sequence at intervals of a step length ΔL, and the elevation values ​​corresponding to each point P1, P2, ... Pn in the digital DEM database of the area are traversed. The pitch angle of the target aircraft relative to the radar is determined according to the flight altitude of the target aircraft. The pitch angle of the corresponding point relative to the radar is obtained according to the elevation value corresponding to each point, and it is determined whether it is less than the pitch angle of the target aircraft relative to the radar. If so, the corresponding point is entered into the flight inspection route data set. If not, the judgment is repeated until all points are judged and the route planning is completed.

[0065] Preferably, determining the pitch angle of the target aircraft relative to the radar according to the flight altitude of the target aircraft includes:

[0066] The target aircraft's flight altitude is calculated by formula (1) to obtain the pitch angle of the target aircraft relative to the radar:

[0067]

[0068] Where: E 0 is the pitch angle of the target aircraft relative to the radar, h f is the target aircraft flight altitude, h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0069] Preferably, obtaining the pitch angle of the corresponding point relative to the radar according to the elevation value corresponding to each point includes:

[0070] The target aircraft's flight altitude is calculated by formula (2) to obtain the pitch angle of the target aircraft relative to the radar:

[0071]

[0072] Where: E p is the pitch angle of the target aircraft relative to the radar, For the direction The elevation of point P at time h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0073] Taking the power coverage range of 0 to 90° as an example, the azimuth angles are 67°, 69°, 44°, 11°, 13°, 75°, 15°, and 77°. P <E 0.

[0074] In the above Python program implementation, the azimuth step angle of 0.1° and the distance step length of 30m are measures that comprehensively consider computing resources and efficiency. The calculation plan can also be reasonably carried out according to the urgency of the task.

[0075] Embodiment 2

[0076] Figure 2 The present invention is a schematic block diagram of a short-range air defense radar ultra-low altitude test route optimization device according to an exemplary embodiment, the device comprising:

[0077] The acquisition module 210 is used to acquire DEM data with a resolution of 30M in the test area, and the DEM data with a resolution of 30M in the test area includes: radar position, radar elevation, radar power coverage and target aircraft flight altitude;

[0078] The analysis module 220 is used to establish radar rectangular coordinate system data with a resolution of 30M in the test area with the radar position as the origin. In the Python programming environment, the radar elevation angle comparison method is used for modeling and calculation, and the terrain conditions in the route area are analyzed for visibility to form a flight inspection data set to complete the route planning.

[0079] Preferably, the analysis module 220 is used to:

[0080] Taking the radar position as the origin and the radar power coverage as the detection pole diameter, traverse the elevation values ​​of each point in the DEM data, and determine whether the straightness of the radar power ray direction under the flight inspection requirements is met under the premise of being lower than the radar position height:

[0081] If yes, enter the corresponding points into the flight inspection route data set;

[0082] If no, proceed to the next step;

[0083] The radar power coverage is the detection radius, and the azimuth is the step length. The polar diameter is sampled in sequence at intervals of step length ΔL, and the elevation values ​​corresponding to each point P1, P2, ... Pn in the digital DEM database of the area are traversed. The pitch angle of the target aircraft relative to the radar is determined according to the flight altitude of the target aircraft. The pitch angle of the corresponding point relative to the radar is obtained according to the elevation value corresponding to each point, and it is judged whether it is less than the pitch angle of the target aircraft relative to the radar. If so, the corresponding point is entered into the flight inspection route data set. If not, the judgment is repeated until all points are judged and the route planning is completed.

[0084] Preferably, the analysis module 220 is used to:

[0085] The target aircraft's flight altitude is calculated by formula (1) to obtain the pitch angle of the target aircraft relative to the radar:

[0086]

[0087] Where: E 0 is the pitch angle of the target aircraft relative to the radar, h f is the target aircraft flight altitude, h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0088] Preferably, the analysis module 220 is used to:

[0089] The target aircraft's flight altitude is calculated by formula (2) to obtain the pitch angle of the target aircraft relative to the radar:

[0090]

[0091] Where: E p is the pitch angle of the target aircraft relative to the radar, For the direction The elevation of point P at time h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

[0092] This application establishes a terrain shielding model through high-precision terrain DEM data in geographic information technology, analyzes and calculates the propagation path and shielding of the radar beam, predicts and evaluates the scope and degree of influence of terrain shielding on radar detection, comprehensively and quickly optimizes the radar ultra-low altitude test route design, and maximizes the assessment of the extreme boundary characteristics of radar equipment.

[0093] Embodiment 3

[0094] Figure 3 300 is a block diagram of a terminal provided in an embodiment of the present application, and the terminal may be a terminal in the above embodiment. The terminal 300 may be a portable mobile terminal, such as a smart phone or a tablet computer. The terminal 300 may also be referred to as a user equipment, a portable terminal, or other names.

[0095] Typically, the terminal 300 includes a processor 301 and a memory 302 .

[0096] The processor 301 may include one or more processing cores, such as a 4-core processor, an 8-core processor, etc. The processor 301 may be implemented in at least one hardware form of DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 301 may also include a main processor and a coprocessor. The main processor is a processor for processing data in the awake state, also known as a CPU (Central Processing Unit); the coprocessor is a low-power processor for processing data in the standby state. In some embodiments, the processor 301 may be integrated with a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the display screen. In some embodiments, the processor 301 may also include an AI (Artificial Intelligence) processor, which is used to process computing operations related to machine learning.

[0097] The memory 302 may include one or more computer-readable storage media, which may be tangible and non-transitory. The memory 302 may also include a high-speed random access memory, and a non-volatile memory, such as one or more disk storage devices, flash memory storage devices. In some embodiments, the non-transitory computer-readable storage medium in the memory 302 is used to store at least one instruction, which is used to be executed by the processor 301 to implement a short-range air defense radar ultra-low altitude test route optimization method provided in the present application.

[0098] In some embodiments, the terminal 300 may further include: a peripheral device interface 303 and at least one peripheral device. Specifically, the peripheral device includes: at least one of a radio frequency circuit 304 , a touch screen 305 , a camera 306 , an audio circuit 307 , a positioning component 308 and a power supply 309 .

[0099] The peripheral device interface 303 may be used to connect at least one peripheral device related to I / O (Input / Output) to the processor 301 and the memory 302. In some embodiments, the processor 301, the memory 302, and the peripheral device interface 303 are integrated on the same chip or circuit board; in some other embodiments, any one or two of the processor 301, the memory 302, and the peripheral device interface 303 may be implemented on a separate chip or circuit board, which is not limited in this embodiment.

[0100] The radio frequency circuit 304 is used to receive and transmit RF (Radio Frequency) signals, also known as electromagnetic signals. The radio frequency circuit 304 communicates with the communication network and other communication devices through electromagnetic signals. The radio frequency circuit 304 converts electrical signals into electromagnetic signals for transmission, or converts received electromagnetic signals into electrical signals. Optionally, the radio frequency circuit 304 includes: an antenna system, an RF transceiver, one or more amplifiers, a tuner, an oscillator, a digital signal processor, a codec chipset, a user identity module card, and the like. The radio frequency circuit 304 can communicate with other terminals through at least one wireless communication protocol. The wireless communication protocol includes but is not limited to: the World Wide Web, a metropolitan area network, an intranet, various generations of mobile communication networks (2G, 3G, 4G and 5G), a wireless local area network and / or a WiFi (Wireless Fidelity) network. In some embodiments, the radio frequency circuit 304 may also include circuits related to NFC (Near Field Communication), which is not limited in this application.

[0101] The touch display screen 305 is used to display the UI (User Interface). The UI may include graphics, text, icons, videos and any combination thereof. The touch display screen 305 also has the ability to collect touch signals on the surface or above the surface of the touch display screen 305. The touch signal can be input to the processor 301 as a control signal for processing. The touch display screen 305 is used to provide virtual buttons and / or virtual keyboards, also known as soft buttons and / or soft keyboards. In some embodiments, the touch display screen 305 can be one, and the front panel of the terminal 300 is set; in other embodiments, the touch display screen 305 can be at least two, which are respectively set on different surfaces of the terminal 300 or are folded; in some other embodiments, the touch display screen 305 can be a flexible display screen, which is set on the curved surface or folded surface of the terminal 300. Even, the touch display screen 305 can also be set to a non-rectangular irregular shape, that is, a special-shaped screen. The touch display screen 305 can be made of materials such as LCD (Liquid Crystal Display) and OLED (Organic Light-Emitting Diode).

[0102] The camera assembly 306 is used to capture images or videos. Optionally, the camera assembly 306 includes a front camera and a rear camera. Typically, the front camera is used to realize video calls or selfies, and the rear camera is used to realize the shooting of photos or videos. In some embodiments, there are at least two rear cameras, which are any one of a main camera, a depth of field camera, and a wide-angle camera, so as to realize the fusion of the main camera and the depth of field camera to realize the background blur function, and the fusion of the main camera and the wide-angle camera to realize panoramic shooting and VR (Virtual Reality) shooting functions. In some embodiments, the camera assembly 306 may also include a flash. The flash can be a monochrome temperature flash or a dual-color temperature flash. A dual-color temperature flash refers to a combination of a warm light flash and a cold light flash, which can be used for light compensation at different color temperatures.

[0103] The audio circuit 307 is used to provide an audio interface between the user and the terminal 300. The audio circuit 307 may include a microphone and a speaker. The microphone is used to collect sound waves from the user and the environment, and convert the sound waves into electrical signals and input them into the processor 301 for processing, or input them into the radio frequency circuit 304 to achieve voice communication. For the purpose of stereo acquisition or noise reduction, there may be multiple microphones, which are respectively arranged at different parts of the terminal 300. The microphone may also be an array microphone or an omnidirectional acquisition microphone. The speaker is used to convert the electrical signal from the processor 301 or the radio frequency circuit 304 into sound waves. The speaker may be a traditional film speaker or a piezoelectric ceramic speaker. When the speaker is a piezoelectric ceramic speaker, it can not only convert the electrical signal into sound waves audible to humans, but also convert the electrical signal into sound waves inaudible to humans for purposes such as ranging. In some embodiments, the audio circuit 307 may also include a headphone jack.

[0104] The positioning component 308 is used to locate the current geographical location of the terminal 300 to implement navigation or LBS (Location Based Service). The positioning component 308 can be a positioning component based on the US GPS (Global Positioning System), China's Beidou system or Russia's Galileo system.

[0105] The power supply 309 is used to power various components in the terminal 300. The power supply 309 can be an alternating current, a direct current, a disposable battery, or a rechargeable battery. When the power supply 309 includes a rechargeable battery, the rechargeable battery can be a wired rechargeable battery or a wireless rechargeable battery. A wired rechargeable battery is a battery charged through a wired line, and a wireless rechargeable battery is a battery charged through a wireless coil. The rechargeable battery can also be used to support fast charging technology.

[0106] In some embodiments, the terminal 300 further includes one or more sensors 310 , including but not limited to: an acceleration sensor 311 , a gyroscope sensor 312 , a pressure sensor 313 , a fingerprint sensor 314 , an optical sensor 315 , and a proximity sensor 316 .

[0107] The acceleration sensor 311 can detect the magnitude of acceleration on the three coordinate axes of the coordinate system established by the terminal 300. For example, the acceleration sensor 311 can be used to detect the components of gravity acceleration on the three coordinate axes. The processor 301 can control the touch display screen 305 to display the user interface in a horizontal view or a vertical view according to the gravity acceleration signal collected by the acceleration sensor 311. The acceleration sensor 311 can also be used for collecting game or user motion data.

[0108] The gyro sensor 312 can detect the body direction and rotation angle of the terminal 300. The gyro sensor 312 can cooperate with the acceleration sensor 311 to collect the user's 3D (3 Dimensions) action on the terminal 300. The processor 301 can implement the following functions based on the data collected by the gyro sensor 312: motion sensing (such as changing the UI according to the user's tilt operation), image stabilization during shooting, game control, and inertial navigation.

[0109] The pressure sensor 313 can be set on the side frame of the terminal 300 and / or the lower layer of the touch display screen 305. When the pressure sensor 313 is set on the side frame of the terminal 300, it can detect the user's holding signal of the terminal 300, and perform left and right hand recognition or shortcut operation according to the holding signal. When the pressure sensor 313 is set on the lower layer of the touch display screen 305, it can control the operability control on the UI interface according to the user's pressure operation on the touch display screen 305. The operability control includes at least one of a button control, a scroll bar control, an icon control, and a menu control.

[0110] The fingerprint sensor 314 is used to collect the user's fingerprint to identify the user's identity based on the collected fingerprint. When the user's identity is identified as a trusted identity, the processor 301 authorizes the user to perform relevant sensitive operations, including unlocking the screen, viewing encrypted information, downloading software, paying, and changing settings. The fingerprint sensor 314 can be set on the front, back, or side of the terminal 300. When a physical button or a manufacturer logo is set on the terminal 300, the fingerprint sensor 314 can be integrated with the physical button or the manufacturer logo.

[0111] The optical sensor 315 is used to collect the ambient light intensity. In one embodiment, the processor 301 can control the display brightness of the touch display screen 305 according to the ambient light intensity collected by the optical sensor 315. Specifically, when the ambient light intensity is high, the display brightness of the touch display screen 305 is increased; when the ambient light intensity is low, the display brightness of the touch display screen 305 is reduced. In another embodiment, the processor 301 can also dynamically adjust the shooting parameters of the camera assembly 306 according to the ambient light intensity collected by the optical sensor 315.

[0112] The proximity sensor 316, also called a distance sensor, is usually arranged on the front of the terminal 300. The proximity sensor 316 is used to collect the distance between the user and the front of the terminal 300. In one embodiment, when the proximity sensor 316 detects that the distance between the user and the front of the terminal 300 is gradually decreasing, the processor 301 controls the touch display screen 305 to switch from the screen-on state to the screen-off state; when the proximity sensor 316 detects that the distance between the user and the front of the terminal 300 is gradually increasing, the processor 301 controls the touch display screen 305 to switch from the screen-off state to the screen-on state.

[0113] Those skilled in the art will understand that Figure 3 The structure shown in the figure does not constitute a limitation on the terminal 300, and the terminal 300 may include more or less components than those shown in the figure, or combine some components, or adopt a different component arrangement.

[0114] Embodiment 4

[0115] In an exemplary embodiment, a computer-readable storage medium is also provided, on which a computer program is stored. When the program is executed by a processor, a method for optimizing the ultra-low altitude test route of a short-range air defense radar is implemented as provided in all the inventive embodiments of the present application.

[0116] Any combination of one or more computer-readable media may be used. A computer-readable medium may be a computer-readable signal medium or a computer-readable storage medium. A computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination thereof. More specific examples (a non-exhaustive list) of computer-readable storage media include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this document, a computer-readable storage medium may be any tangible medium containing or storing a program that may be used by or in conjunction with an instruction execution system, device, or device.

[0117] Computer-readable signal media may include a data signal propagated in baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination of the above. Computer-readable signal media may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0118] Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to wireless, wireline, optical fiber cable, RF, etc., or any suitable combination of the foregoing.

[0119] Computer program code for performing the operations of the present invention may be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0120] Embodiment 5

[0121] In an exemplary embodiment, an application product is also provided, including one or more instructions, which can be executed by the processor 301 of the above-mentioned device to complete the above-mentioned short-range air defense radar ultra-low altitude test route optimization method.

[0122] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily realized. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. A method for optimizing the ultra-low altitude test route of a short-range air defense radar, characterized in that: include: Acquire DEM data with a resolution of 30M in the test area, wherein the DEM data with a resolution of 30M in the test area includes: radar position, radar elevation, radar power coverage and target aircraft flight altitude; Taking the radar position as the origin, a radar rectangular coordinate system data with a resolution of 30M in the test area is established. In the Python programming environment, the radar elevation angle comparison method is used for modeling and calculation, and the visibility analysis of the terrain conditions in the route area is performed to form a flight inspection data set to complete the route planning.

2. The method for optimizing the ultra-low altitude test route of a short-range air defense radar according to claim 1 is characterized in that: The radar elevation angle comparison method is used to perform modeling and calculation, and the terrain conditions in the route area are analyzed for visibility to form a flight inspection data set to complete the route planning, including: Taking the radar position as the origin and the radar power coverage as the detection pole diameter, traverse the elevation values ​​of each point in the DEM data, and determine whether the straightness of the radar power ray direction under the flight inspection requirements is met under the premise of being lower than the radar position height: If yes, enter the corresponding points into the flight inspection route data set; If no, proceed to the next step; The radar power coverage is the detection radius, and the azimuth is the step length. The polar diameter is sampled in sequence at intervals of a step length ΔL, and the elevation values ​​corresponding to each point P1, P2, ... Pn in the digital DEM database of the area are traversed. The pitch angle of the target aircraft relative to the radar is determined according to the flight altitude of the target aircraft. The pitch angle of the corresponding point relative to the radar is obtained according to the elevation value corresponding to each point, and it is determined whether it is less than the pitch angle of the target aircraft relative to the radar. If so, the corresponding point is entered into the flight inspection route data set. If not, the judgment is repeated until all points are judged and the route planning is completed.

3. The method for optimizing the ultra-low altitude test route of a short-range air defense radar according to claim 2 is characterized in that: Determining the pitch angle of the target aircraft relative to the radar according to the flight altitude of the target aircraft includes: The target aircraft's flight altitude is calculated by formula (1) to obtain the pitch angle of the target aircraft relative to the radar: Where: E0 is the pitch angle of the target aircraft relative to the radar, h f is the target aircraft flight altitude, h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

4. The method for optimizing the ultra-low altitude test route of a short-range air defense radar according to claim 2 is characterized in that: The step of obtaining the pitch angle of the corresponding point relative to the radar according to the elevation value corresponding to each point includes: The target aircraft's flight altitude is calculated by formula (2) to obtain the pitch angle of the target aircraft relative to the radar: Where: E p is the pitch angle of the target aircraft relative to the radar, For the direction The elevation of point P at time h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

5. A short-range air defense radar ultra-low altitude test route optimization device, characterized in that: include: An acquisition module is used to acquire DEM data with a resolution of 30M in the test area, and the DEM data with a resolution of 30M in the test area includes: radar position, radar elevation, radar power coverage and target aircraft flight altitude; The analysis module is used to establish radar rectangular coordinate system data with a resolution of 30M in the test area with the radar position as the origin. In the Python programming environment, the radar elevation angle comparison method is used for modeling and calculation, and the visibility analysis of the terrain conditions in the route area is performed to form a flight inspection data set to complete the route planning.

6. The short-range air defense radar ultra-low altitude test route optimization device according to claim 5 is characterized in that: The analysis module is used to: Taking the radar position as the origin and the radar power coverage as the detection pole diameter, traverse the elevation values ​​of each point in the DEM data, and determine whether the straightness of the radar power ray direction under the flight inspection requirements is met under the premise of being lower than the radar position height: If yes, enter the corresponding points into the flight inspection route data set; If no, proceed to the next step; The radar power coverage is the detection radius, and the azimuth is the step length. The polar diameter is sampled in sequence at intervals of step length ΔL, and the elevation values ​​corresponding to each point P1, P2, ... Pn in the digital DEM database of the area are traversed. The pitch angle of the target aircraft relative to the radar is determined according to the flight altitude of the target aircraft. The pitch angle of the corresponding point relative to the radar is obtained according to the elevation value corresponding to each point, and it is judged whether it is less than the pitch angle of the target aircraft relative to the radar. If so, the corresponding point is entered into the flight inspection route data set. If not, the judgment is repeated until all points are judged and the route planning is completed.

7. The short-range air defense radar ultra-low altitude test route optimization device according to claim 5 is characterized in that: The analysis module is used to: The target aircraft's flight altitude is calculated by formula (1) to obtain the pitch angle of the target aircraft relative to the radar: Where: E0 is the pitch angle of the target aircraft relative to the radar, h f is the target aircraft flight altitude, h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

8. The short-range air defense radar ultra-low altitude test route optimization device according to claim 5 is characterized in that: The analysis module is used to: The target aircraft's flight altitude is calculated by formula (2) to obtain the pitch angle of the target aircraft relative to the radar: Where: E p is the pitch angle of the target aircraft relative to the radar, For the direction The elevation of point P at time h r is the radar elevation, For the direction P(0) is the horizontal projection distance of point P when the azimuth is 0°.

9. A terminal, characterized in that: include: one or more processors; a memory for storing the one or more processor-executable instructions; Wherein, the one or more processors are configured to: Execute a short-range air defense radar ultra-low altitude test route optimization method as described in any one of claims 1 to 4.

10. A non-transitory computer-readable storage medium, characterized in that: When the instructions in the storage medium are executed by the processor of the terminal, the terminal is enabled to execute a short-range air defense radar ultra-low altitude test route optimization method as described in any one of claims 1 to 4.

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