KR102620468B1 - Apparatus for analyzing trajectory of air vehicle and method thereof - Google Patents

Abstract

The present invention discloses an aircraft trajectory analysis device and method. In other words, the present invention generates the flight trajectory of the aircraft based on the aircraft information collected from the detection system, confirms the coordinates of the point where the pitch of the aircraft changes based on the generated flight trajectory, and changes the pitch of the confirmed aircraft. Set the expected section of the launch origin using a one-way linear regression analysis model created based on the coordinates of the point, and create another one-way linear regression analysis model based on the coordinates of the point where the pitch of the confirmed aircraft changes. , by estimating the launch origin based on other generated one-way linear regression analysis models and the previously set launch origin expected section, the flight trajectory of the aircraft is estimated without a 3D Kalman filter, and the type of ammunition, maximum altitude, flight trajectory, etc. of the aircraft are estimated. The launch origin of the aircraft can be estimated without prior database information.

Description

Apparatus for analyzing trajectory of air vehicle and method thereof}

The present invention relates to an aircraft trajectory analysis device and method. In particular, the flight trajectory of an aircraft is generated based on aircraft information collected from a detection system, and the coordinates of the point where the pitch of the aircraft changes are determined based on the generated flight trajectory. Confirm, set the expected launch origin section using a one-way linear regression analysis model created based on the coordinates of the point where the pitch of the confirmed aircraft changes, and set the expected section for the launch origin based on the coordinates of the point where the pitch of the confirmed aircraft changes. The purpose is to provide an aircraft trajectory analysis device and method for generating another one-way linear regression analysis model and estimating the launch origin based on the other generated one-way linear regression analysis model and the previously set launch origin expected section.

After being launched, a ballistic missile is accelerated by the rocket's propulsion and flies, and when the propellant is completely burned, it refers to a guided missile that flies along a trajectory similar to the ballistic curve of a cannon.

To estimate the trajectory of such a ballistic missile (or missile), launch angle, projectile type, speed, weather (including, for example, wind direction, wind speed, etc.), and a three-dimensional trajectory considering the effects of the Earth's rotation are required. It is difficult to confirm information such as this, and it is difficult to track the origin of a ballistic missile launched from an opponent.

In addition, in the case of existing methods of origin estimation, such as photo verification using satellites and triangulation measurement using radio signals, there are difficulties in establishing a detection system, purchasing software, and requiring analysis time.

Korean Patent No. 10-1426290 [Title: Radar system and target tracking method using the same]

The purpose of the present invention is to generate a flight trajectory of an aircraft based on the aircraft information collected from the detection system, confirm the coordinates of the point where the pitch of the aircraft changes based on the generated flight trajectory, and change the pitch of the confirmed aircraft. Set the expected section of the launch origin using a one-way linear regression analysis model created based on the coordinates of the point, and create another one-way linear regression analysis model based on the coordinates of the point where the pitch of the confirmed aircraft changes. The purpose is to provide an aircraft trajectory analysis device and method for estimating the launch origin based on other generated one-way linear regression analysis models and the previously set launch origin expected section.

An aircraft trajectory analysis device according to an embodiment of the present invention includes a communication unit that receives aircraft information transmitted from a detection system; And performing a preprocessing function on the received aircraft information, extracting basic information, generating at least one of a two-dimensional flight trajectory and a three-dimensional flight trajectory of the aircraft based on the basic information, and generating the generated two-dimensional flight trajectory. Confirm the coordinates of the point where the pitch of the aircraft changes based on information about the trajectory or the information about the generated three-dimensional flight trajectory, and based on the coordinates of the point where the pitch of the confirmed aircraft changes, Extract data before pitch change from the basic information, construct a first one-way linear regression analysis model and a second one-way linear regression analysis model based on the confirmed data before pitch change, respectively, and construct the first one-way linear regression analysis model constructed above. Based on the linear regression analysis model and the second one-way linear regression analysis model, first expected coordinates and second expected coordinates corresponding to the estimated altitude of the launch origin are calculated, respectively, and the calculated first expected coordinates and the calculated first expected coordinates are calculated. 2 Set an expected launch origin section consisting of expected coordinates, construct a third one-way linear regression analysis model based on the data before the pitch change, and calculate the third one-way linear regression analysis model constructed above and the expected launch origin set above. It may include a control unit that estimates the expected launch origin based on the section and estimates the actual launch origin based on the first and second expected launch origin estimated coordinates included in the estimated launch origin. .

As an example related to the present invention, the basic information may include at least one of latitude, longitude, altitude, speed, data set reception time, and detection system name.

An aircraft trajectory analysis method according to an embodiment of the present invention includes the steps of performing a preprocessing function on aircraft information collected from a detection system by a control unit to extract basic information; Generating, by the control unit, at least one of a two-dimensional flight trajectory and a three-dimensional flight trajectory of the aircraft based on the basic information; Confirming, by the control unit, the coordinates of a point where the pitch of the aircraft changes based on information about the generated two-dimensional flight trajectory or information about the generated three-dimensional flight trajectory; extracting, by the control unit, data prior to a pitch change from the basic information based on the coordinates of a point where the pitch of the confirmed aircraft changes; Constructing, by the control unit, a first one-way linear regression analysis model and a second one-way linear regression analysis model based on the confirmed data before the pitch change; calculating, by the control unit, first expected coordinates and second expected coordinates corresponding to the estimated altitude of the launch origin based on the configured first one-way linear regression analysis model and the second one-way linear regression analysis model; Setting, by the control unit, an expected launch origin section consisting of the calculated first expected coordinates and the calculated second expected coordinates; Constructing, by the control unit, a third one-way linear regression analysis model based on the data before the pitch change; estimating, by the control unit, an expected emission origin based on the configured third one-way linear regression analysis model and the set emission origin expected section; And it may include, by the control unit, estimating the actual launch origin based on the first expected launch origin estimated coordinates and the second expected launch origin estimated coordinates included in the estimated expected launch origin.

As an example related to the present invention, the step of generating at least one of a two-dimensional flight trajectory and a three-dimensional flight trajectory of the aircraft includes applying the Loess technique or the Lowess technique to the basic information to generate a two-dimensional flight trajectory of the aircraft. process; And it may include at least one process of generating a three-dimensional flight trajectory of the aircraft by applying the Lowess technique to the basic information.

As an example related to the present invention, the step of confirming the coordinates of the point where the pitch of the aircraft changes includes dividing the x-axis section of the two-dimensional flight trajectory or the three-dimensional flight trajectory into preset intervals to create a plurality of sections. process; A process of calculating a slope for each section for each of the plurality of sections created; A process of confirming a specific section that exceeds a preset reference value among the calculated slopes for each section; And it may include a process of corresponding information about a specific section exceeding the confirmed reference value to the coordinates of a point where the pitch of the aircraft changes.

As an example related to the present invention, the step of extracting data before the pitch change from the basic information is based on information about a specific section exceeding the confirmed reference value corresponding to the coordinates of the point where the pitch of the aircraft changes, Among the basic information, data from the initial data of the basic information to the section immediately preceding the specific section exceeding the confirmed reference value may be extracted as data before the pitch change.

As an example related to the present invention, the step of constructing the first one-way linear regression analysis model and the second one-way linear regression analysis model, respectively, takes the hardness included in the extracted data before the pitch change as the x-axis, and A process of constructing the first one-way linear regression analysis model with the altitude included in the extracted data before the pitch change as the y-axis; And it may include the process of constructing a second one-way linear regression analysis model with the latitude included in the extracted data before the pitch change as the x-axis and the altitude included in the extracted data before the pitch change as the y-axis. there is.

As an example related to the present invention, the step of calculating the first and second expected coordinates respectively corresponding to the estimated altitude of the launch origin corresponds to the longitude origin estimate based on the first one-way linear regression analysis model constructed above. A process of calculating a first x value corresponding to the average sea level altitude of the expected launch point of the aircraft; A process of calculating first expected coordinates consisting of the calculated first x value and a first y value corresponding to the estimated altitude of the launch origin; A process of calculating a second x value corresponding to the average sea level altitude of the expected launch point of the aircraft corresponding to the latitude origin estimate based on the configured second one-way linear regression analysis model; And it may include calculating second expected coordinates consisting of the calculated second x value and a second y value corresponding to the estimated altitude of the launch origin.

As an example related to the present invention, the step of estimating the expected launch origin based on the configured third one-way linear regression analysis model and the set launch origin expected section includes calculating the first x value in the first expected coordinates as the x value. and calculating the first expected launch origin estimated coordinates, which are configured by using the latitude value corresponding to the first x value as the y value in the configured third one-way linear regression analysis model; And a second expected launch configured by taking the second It includes calculating estimated origin coordinates, wherein the expected launch origin may be composed of the first expected launch origin estimated coordinates and the second expected launch origin estimated coordinates.

As an example related to the present invention, the step of estimating the actual emission origin includes: setting a emission origin estimation section consisting of the first expected emission origin estimate coordinates and the second expected emission origin estimate coordinates; Calculating longitude coordinates at a preset altitude using the first one-way linear regression model, and calculating latitude coordinates at the preset altitude using the second one-way linear regression model; A process of displaying the calculated longitude coordinates and latitude coordinates at the preset altitude on the progress path (vector) and confirming the estimated value located on the axis of the estimated launch origin point section; And it may include a process of estimating the confirmed estimated value as the actual launch origin.

The present invention generates a flight trajectory of an aircraft based on aircraft information collected from a detection system, confirms the coordinates of the point where the pitch of the aircraft changes based on the generated flight trajectory, and confirms the point at which the pitch of the confirmed aircraft changes. Set the expected section of the launch origin using a one-way linear regression analysis model created based on the coordinates of , and create another one-way linear regression analysis model based on the coordinates of the point where the pitch of the confirmed aircraft changes. By estimating the launch origin based on other one-way linear regression analysis models and the previously set launch origin expected section, the flight trajectory of the aircraft is estimated without a 3D Kalman filter, and a dictionary database for the aircraft's ammunition type, maximum altitude, flight trajectory, etc. The launch origin of the aircraft is estimated without any detailed information, and it has the effect of making it easier to estimate the flight trajectory in agents with limited memory or low computing power, such as wearable devices.

Figure 1 is a block diagram showing the configuration of an aircraft trajectory analysis device according to an embodiment of the present invention.
Figure 2 is a flowchart showing a method of analyzing an aircraft trajectory according to an embodiment of the present invention.
3 and 4 are diagrams showing examples of flight trajectories according to an embodiment of the present invention.
Figure 5 is a diagram showing an example of data before a pitch change according to an embodiment of the present invention.
Figure 6 is a diagram showing an example of an emission origin estimation section according to an embodiment of the present invention.
Figure 7 is a diagram showing an example of the final emission origin estimate coordinates according to an embodiment of the present invention.

It should be noted that the technical terms used in the present invention are only used to describe specific embodiments and are not intended to limit the present invention. In addition, the technical terms used in the present invention, unless specifically defined in a different sense in the present invention, should be interpreted as meanings generally understood by those skilled in the art in the technical field to which the present invention pertains, and are not overly comprehensive. It should not be interpreted in a literal or excessively reduced sense. Additionally, if the technical terms used in the present invention are incorrect technical terms that do not accurately express the idea of the present invention, they should be replaced with technical terms that can be correctly understood by those skilled in the art. In addition, general terms used in the present invention should be interpreted according to the definition in the dictionary or according to the context, and should not be interpreted in an excessively reduced sense.

Additionally, as used in the present invention, singular expressions include plural expressions unless the context clearly dictates otherwise. In the present invention, terms such as “consists of” or “comprises” should not be construed as necessarily including all of the various components or steps described in the invention, and some of the components or steps may not be included. It may be possible, or it should be interpreted as being able to further include additional components or steps.

Additionally, terms containing ordinal numbers, such as first, second, etc., used in the present invention may be used to describe constituent elements, but the constituent elements should not be limited by the terms. Terms are used only to distinguish one component from another. For example, a first component may be named a second component without departing from the scope of the present invention, and similarly, the second component may also be named a first component.

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the attached drawings. However, identical or similar components will be assigned the same reference numbers regardless of the reference numerals, and duplicate descriptions thereof will be omitted.

Additionally, when describing the present invention, if it is determined that a detailed description of related known technologies may obscure the gist of the present invention, the detailed description will be omitted. In addition, it should be noted that the attached drawings are only intended to facilitate easy understanding of the spirit of the present invention, and should not be construed as limiting the spirit of the present invention by the attached drawings.

Figure 1 is a block diagram showing the configuration of an aircraft trajectory analysis device 100 according to an embodiment of the present invention.

As shown in FIG. 1, the aircraft trajectory analysis device 100 consists of a communication unit 110, a storage unit 120, a display unit 130, an audio output unit 140, and a control unit 150. Not all of the components of the aircraft trajectory analysis device 100 shown in FIG. 1 are essential components, and the aircraft trajectory analysis device 100 may be implemented with more components than those shown in FIG. 1. The aircraft trajectory analysis device 100 may also be implemented with fewer components.

The aircraft trajectory analysis device 100 is applicable to a smart phone, a portable terminal, a mobile terminal, a foldable terminal, a personal digital assistant (PDA), and a PMP. (Portable Multimedia Player) terminal, telematics terminal, navigation terminal, personal computer, laptop computer, Slate PC, Tablet PC, ultrabook, wearable Devices (including wearable devices, e.g. smartwatch, smart glass, head mounted display (HMD), etc.), Wibro terminal, IPTV (Internet Protocol Television) terminal, smart TV , It can be applied to various terminals such as digital broadcasting terminals, AVN (Audio Video Navigation) terminals, A/V (Audio/Video) systems, flexible terminals, digital signage devices, artificial intelligence speakers, etc.

The communication unit 110 communicates with any internal component or at least one external terminal through a wired/wireless communication network. At this time, the external arbitrary terminal may include a server (not shown), another terminal (not shown), etc. Here, wireless Internet technologies include Wireless LAN (WLAN), DLNA (Digital Living Network Alliance), Wibro (Wireless Broadband: Wibro), Wimax (World Interoperability for Microwave Access: Wimax), and HSDPA (High Speed Downlink Packet Access). ), HSUPA (High Speed Uplink Packet Access), IEEE 802.16, Long Term Evolution (LTE), LTE-A (Long Term Evolution-Advanced), Wireless Mobile Broadband Service (WMBS), etc. The communication unit 110 transmits and receives data according to at least one wireless Internet technology, including Internet technologies not listed above. In addition, short-range communication technologies include Bluetooth, RFID (Radio Frequency Identification), Infrared Data Association (IrDA), UWB (Ultra Wideband), ZigBee, and Near Field Communication (NFC). , Ultrasound Communication (USC), Visible Light Communication (VLC), Wi-Fi, Wi-Fi Direct, etc. may be included. Additionally, wired communication technologies may include Power Line Communication (PLC), USB communication, Ethernet, serial communication, optical/coaxial cables, etc.

Additionally, the communication unit 110 can transmit information to and from any terminal through a universal serial bus (USB).

In addition, the communication unit 110 supports technical standards or communication methods for mobile communication (e.g., Global System for Mobile communication (GSM), Code Division Multi Access (CDMA), Code Division Multi Access 2000 (CDMA2000), EV -DO (Enhanced Voice-Data Optimized or Enhanced Voice-Data Only), WCDMA (Wideband CDMA), HSDPA (High Speed Downlink Packet Access), HSUPA (High Speed Uplink Packet Access), LTE (Long Term Evolution), LTE-A (Long Term Evolution-Advanced, etc.), wireless signals are transmitted and received with a base station, the server, and the other terminals on a mobile communication network constructed according to (Long Term Evolution-Advanced), etc.).

In addition, the communication unit 110 receives (or collects) aircraft information transmitted from a detection system (not shown) under the control of the control unit 150.

The storage unit 120 stores various user interfaces (UIs), graphic user interfaces (GUIs), etc.

Additionally, the storage unit 120 stores data and programs necessary for the aircraft trajectory analysis device 100 to operate.

That is, the storage unit 120 stores a plurality of application programs (application programs or applications) running on the aircraft trajectory analysis device 100, data for the operation of the aircraft trajectory analysis device 100, and commands. You can save it. At least some of these applications may be downloaded from an external server via wireless communication. In addition, at least some of these applications may exist on the aircraft trajectory analysis device 100 from the time of shipment for the basic functions of the aircraft trajectory analysis device 100. Meanwhile, the application program is stored in the storage unit 120, installed on the aircraft trajectory analysis device 100, and driven by the control unit 150 to perform the operation (or function) of the aircraft trajectory analysis device 100. It can be.

In addition, the storage unit 120 is a flash memory type, hard disk type, multimedia card micro type, and card type memory (for example, SD or XD). memory, etc.), magnetic memory, magnetic disk, optical disk, RAM (Random Access Memory), SRAM (Static Random Access Memory), ROM (Read-Only Memory: ROM), EEPROM (Electrically Erasable Programmable Read-Only Memory), It may include at least one storage medium of PROM (Programmable Read-Only Memory). Additionally, the aircraft trajectory analysis device 100 may operate web storage that performs the storage function of the storage unit 120 on the Internet, or may operate in relation to the web storage.

In addition, the storage unit 120 stores the received (or collected) aircraft information, etc. under the control of the control unit 150.

The display unit (or display unit) 130 can display various contents, such as various menu screens, using the user interface and/or graphic user interface stored in the storage unit 120 under the control of the control unit 150. there is. Here, the content displayed on the display unit 130 includes various text or image data (including various information data) and a menu screen including data such as icons, list menus, and combo boxes. Additionally, the display unit 130 may be a touch screen.

In addition, the display unit 130 may be a liquid crystal display (LCD), a thin film transistor-liquid crystal display (TFT LCD), an organic light-emitting diode (OLED), or a flexible display. It may include at least one of a flexible display, a 3D display, an e-ink display, and a light emitting diode (LED).

In addition, the display unit 130 displays the received (or collected) aircraft information, etc. under the control of the control unit 150.

The audio output unit 140 outputs audio information included in a signal processed by the control unit 150. Here, the audio output unit 140 may include a receiver, speaker, buzzer, etc.

Additionally, the voice output unit 140 outputs a guidance voice generated by the control unit 150.

In addition, the audio output unit 140 outputs audio information (or sound information) corresponding to the received (or collected) aircraft information, etc. under the control of the control unit 150.

The controller (or microcontroller unit (MCU)) 150 executes the overall control function of the aircraft trajectory analysis device 100.

In addition, the control unit 150 executes the overall control function of the aircraft trajectory analysis device 100 using the program and data stored in the storage unit 120. The control unit 150 may include RAM, ROM, CPU, GPU, and a bus, and the RAM, ROM, CPU, GPU, etc. may be connected to each other through a bus. The CPU can access the storage unit 120, perform booting using the O/S stored in the storage unit 120, and use various programs, content, data, etc. stored in the storage unit 120. This allows you to perform various operations.

In addition, the control unit 150 uses previously collected aircraft information (or basic information extracted from the aircraft information) as data for continuous machine learning (or deep learning). Here, the input dataset for machine learning includes aircraft information for each of the plurality of components (or basic information extracted from the aircraft information) at a preset ratio (including, for example, 7:3, 8:2, etc.) By dividing it into a training set and a test set, training and testing functions can be performed. In addition, the input dataset for the machine learning includes aircraft information for each component (or basic information extracted from the aircraft information) that is collected later. In addition, the output dataset for the machine learning is the part that is desired to be predicted, and is learned according to the received aircraft information (or basic information extracted from the aircraft information), and later predicts the average of the expected launch point of the aircraft. A first It includes estimated coordinates of the first expected launch origin, estimated coordinates of the second expected launch origin, etc.

That is, the control unit 150 extracts specific aircraft information (or from the specific aircraft information) in relation to specific raw data for an altitude-corresponding longitude prediction model, an altitude-corresponding latitude prediction model, an expected launch origin estimation model, etc., through preset learning data. specific basic information), etc., the first x value (e.g. longitude) corresponding to the average sea level altitude of the expected launch point of the aircraft, the second For example, latitude), first expected coordinates, second expected coordinates, first expected launch origin estimated coordinates, second expected launch origin estimated coordinates, etc. perform a learning function to predict (or estimate/calculate/calculate). At this time, the control unit 150 stores raw data (or specific aircraft information of a component/specific basic information extracted from the specific aircraft information, etc.) in parallel and distributed, and stores the stored raw data (or including learning data, etc.) Unstructured data, structured data, and semi-structured data contained within are refined, preprocessed including classification into metadata, and preprocessed data is subjected to data mining. You can build big data by conducting analysis and conducting learning, training, and testing based on at least one type of machine learning. At this time, at least one type of machine learning is Supervised Learning, Semi-Supervised Learning, Unsupervised Learning, Reinforcement Learning, and Deep Reinforcement Learning. It may be any one or a combination of at least one of them.

In this way, the control unit 150 performs a learning function on the altitude-corresponding longitude prediction model, the altitude-corresponding latitude prediction model, and the expected launch origin estimation model in the form of neural networks through the learning data, etc. .

Additionally, the control unit 150 collects (or receives) aircraft information from a detection system (not shown). Here, the detection system includes aircraft, radar, etc.

In addition, the control unit 150 performs a preprocessing (or reclassification) function on the collected (or received) aircraft information (or radar information/data) to extract (or configure/generate) basic information. Here, the basic information includes latitude, longitude, altitude, speed, reception time of the data set, detection system name (or unique identification information of the detection system), etc. Additionally, the reception time of the data set corresponds to the time of collecting (or measuring) the corresponding latitude, longitude, altitude, etc. At this time, the extracted basic information is managed (or converted) into a preset format (or format) (for example, including extension csv format, etc.).

Additionally, the control unit 150 performs a sorting function on the extracted basic information according to a preset method. Here, the preset method (or sorting method) includes sorting in descending/ascending order according to latitude/longitude, sorting according to reception time of the data set, sorting by detection system, etc.

In addition, the control unit 150 controls the aircraft including a section (or section not included) in which aircraft information (or aircraft information/basic information) is not captured based on the preprocessed (or reclassified/extracted) basic information. Generate a two-dimensional flight trajectory and/or three-dimensional flight trajectory of the aircraft for the entire flight section. Here, the aircraft (or projectile) includes ballistic missiles, missiles, etc.

That is, the control unit 150 generates (or configures) a two-dimensional flight trajectory of the aircraft based on the preprocessed (or reclassified/extracted) basic information. At this time, in the two-dimensional flight trajectory of the aircraft, the x-axis represents the flight distance and the y-axis represents the altitude. In addition, the flight distance is generated by calculating the distance between each aircraft information (including, for example, latitude, longitude, etc.) from the first capture point (including, for example, latitude, longitude, etc.) of the corresponding aircraft.

Here, the control unit 150 generates (or configures) a two-dimensional flight trajectory of the aircraft by applying the Loess technique or the Lowess technique to the preprocessed (or reclassified/extracted) basic information, and applies the Loess technique. At this time, the f value (or luminance value) can be any one of 0.28 to 0.32. At this time, when applying a two-dimensional flight trajectory, it may be advantageous to apply the Loess technique. In addition, the control unit 150 generates flight trajectories for two-stage propulsion aircraft (including, for example, Iskandar missiles, etc.), and the level can be used when compared with the actually collected aircraft information (or missile capture data/information). You can create a two-dimensional flight trajectory of the aircraft.

Additionally, the control unit 150 generates (or configures) a 3D flight trajectory of the aircraft based on the preprocessed (or reclassified/extracted) basic information. At this time, in the case of the 3D flight trajectory of the aircraft, only the Lowess method can be applied, and the f value (or luminance value) can be any one of 0.28 to 0.32. Here, in the three-dimensional flight trajectory of the aircraft, the x-axis represents latitude, the y-axis represents longitude, and the z-axis represents altitude.

In addition, the control unit 150 extracts a preset number of samples (for example, 1,000) from the z-axis (or altitude) trajectory and creates symmetrical x-axis (or latitude) and y-axis (or longitude) coordinate values. Obtain and generate a 3-dimensional flight trajectory (for example, x2, y2, z2) of the aircraft consisting of three variables. At this time, the data reconstructing the 3D flight trajectory in a preset format (including, for example, "*.csv" format, etc.) can be used as basic statistical analysis data for various pictures or tracks.

That is, the control unit 150 generates a two-dimensional flight trajectory of the aircraft based on the preprocessed (or reclassified/extracted) basic information, and the preset flight trajectory is determined from the generated two-dimensional flight trajectory of the aircraft. A number of samples (for example, 1,000) are extracted, and the extracted preset number of samples are combined with the altitude on the actual data to generate a three-dimensional flight trajectory of the aircraft.

In addition, the control unit 150 displays the generated two-dimensional flight trajectory of the aircraft, the three-dimensional flight trajectory of the aircraft, etc. on the display unit 130.

In this way, the control unit 150 controls the flight of the aircraft including a section (or section not included) in which the aircraft information (or basic information) is not captured based on the preprocessed (or reclassified/extracted) basic information. A 2D flight trajectory and/or a 3D flight trajectory of the aircraft can be generated for the entire section.

In addition, the control unit 150 controls the point at which the pitch (or elevation angle) of the aircraft changes based on the information about the generated two-dimensional flight trajectory and/or the information about the generated three-dimensional flight trajectory. Check the coordinates (including latitude, longitude, etc.).

In addition, the control unit 150 extracts data before the pitch change from the basic information based on the coordinates of the point where the confirmed pitch (or elevation angle) of the corresponding aircraft changes. At this time, the control unit 150 confirms the coordinates of the point where the pitch of the aircraft changes according to the administrator input (or administrator/user selection/touch/control) that confirmed the two-dimensional flight trajectory or the three-dimensional flight trajectory ( or select).

In other words, the control unit 150 accurately uses data before the pitch of the aircraft changes in order to estimate the launch origin of the aircraft, so the coordinates before the pitch of the aircraft changes (or the coordinates before the pitch of the aircraft changes) In order to check the section coordinates, the x-axis sections of the two-dimensional flight trajectory and/or the three-dimensional flight trajectory are classified (or divided/divided) into preset intervals to create a plurality of sections.

Additionally, the control unit 150 calculates (or calculates) the slope for each section for each of the plurality of sections created. At this time, the control unit 150 may calculate the slope for each of the plurality of created sections through differentiation. Here, the slope may be an angle with the ground (or an angle formed with the ground).

Additionally, the control unit 150 identifies a specific section that exceeds (or deviates from/is above) a preset reference value (or reference range) among the calculated slopes for each section. At this time, the control unit 150 can check the first section that exceeds the reference value among the calculated slopes for each section.

In addition, the control unit 150 selects the basic information based on information about a specific section (including, for example, coordinate information, etc.) exceeding the confirmed reference value corresponding to the coordinates of the point where the pitch of the aircraft changes. , data from the initial data of the basic information (or coordinates of the first capture point) to the section immediately preceding the specific section exceeding the confirmed reference value are extracted as the data before the pitch change. Here, the data before the pitch change includes latitude, longitude, altitude, etc.

At this time, in order to facilitate data extraction section setting (or data extraction setting before the pitch change), the control unit 150 assigns an index number to the data of the 2D/3D flight trajectory, and displays the corresponding flight trajectory. The index number is displayed together on the screen, and a specific index number is selected by the administrator input, or a specific index number corresponding to a specific section exceeding the confirmed standard value is selected, and the first index number among the basic information is selected. Data (or coordinates) corresponding to to data corresponding to the index number before the specific index number selected may be extracted as data before the pitch change.

In this way, in order to estimate the flight trajectory of a normal missile (or aircraft), 3D information (longitude, latitude, altitude) considering the launch angle, projectile type, speed, weather (including, for example, wind direction, wind speed, etc.), and the effects of the Earth's rotation are required. Trajectory creation is necessary, but when detecting an aircraft in a real situation, it is difficult to check the launch angle, type of ammunition, speed, weather, etc. of the aircraft, so limited detection data such as latitude, longitude, altitude, and detection time are used to detect the aircraft. You can check the flight trajectory.

In addition, when estimating the origin using a 3D aircraft trajectory, there is an interaction between longitude (x-axis) and latitude (y-axis) due to the influence of the Earth's rotation, and in order to accurately generate a 3D aircraft trajectory and estimate the origin, the explanatory variables must be There are limitations to maintaining independence. Here, the interaction refers to a phenomenon of mutual influence between explanatory variables during statistical regression analysis.

In addition, the control unit 150 must calculate the estimated latitude origin and the estimated longitude origin, respectively, considering the fact that the flight trajectory of the aircraft is curved due to the influence of the Earth's rotation, so that the pitch of the confirmed aircraft changes. Based on the coordinates of the point (or data before the pitch change), the first simple linear regression model (or first one-way linear regression equation) and the second one-way linear regression model (or Construct (or create) a second one-way linear regression equation, respectively.

That is, the control unit 150 uses the longitude included in the previously extracted data before the pitch change as the x-axis (or x-coordinate), and the altitude included in the previously extracted data before the pitch change as the y-axis (or y-coordinate). Construct (or create) the first one-way linear regression analysis model.

In addition, the control unit 150 generates a first x value ( For example, calculate (or calculate) hardness. Here, the mean sea level (MSL) of the expected launch point of the aircraft refers to the characteristics of the terrain from which an aircraft (including, for example, missiles, etc.) can be launched, which is flat, and the sea level altitude of the flat is 110 m in most cases. The average sea level altitude of the expected launch point described in the embodiment of the present invention may be 110 m by default, and may be set differently depending on the designer's design.

At this time, the control unit 150 performs artificial intelligence-based machine learning based on the average sea level altitude of the expected launch point of the aircraft, and based on the machine learning results, creates a machine learning method corresponding to the average sea level altitude of the expected launch point of the aircraft. Calculate (or calculate/generate) a first x value (e.g. longitude).

That is, the control unit 150 performs machine learning (or artificial intelligence/deep learning) by using the average sea level altitude of the expected launch point of the aircraft as an input value of a preset altitude-corresponding hardness prediction model, and provides machine learning results (or Based on the artificial intelligence results/deep learning results), the first x value (e.g., longitude) corresponding to the average sea level altitude of the expected launch point of the aircraft is calculated (or calculated/generated).

In addition, the control unit 150 uses the calculated (or calculated) first x value (e.g., longitude) and first y value (e.g., estimated altitude of launch origin/average sea level altitude of expected launch point). Calculate (or calculate/generate) the configured first expected coordinates.

In addition, the control unit 150 uses the latitude included in the previously extracted data before the pitch change as the x-axis (or x-coordinate), and the altitude included in the previously extracted data before the pitch change as the y-axis (or y-coordinate). Construct (or create) a second one-way linear regression analysis model.

In addition, the control unit 150 generates a second x value ( For example, calculate (or calculate) latitude.

At this time, the control unit 150 performs another artificial intelligence-based machine learning based on the average sea level altitude of the expected launch point of the aircraft, and determines the average sea level altitude of the expected launch point of the aircraft based on other machine learning results. Calculate (or calculate/generate) a corresponding second x value (e.g. latitude).

That is, the control unit 150 performs other machine learning (or other artificial intelligence/other deep learning) by using the average sea level altitude of the expected launch point of the aircraft as an input value of a preset altitude-corresponding latitude prediction model, and other machines Based on the learning results (or other artificial intelligence results/other deep learning results), a second x value (e.g., latitude) corresponding to the average sea level altitude of the expected launch point of the aircraft is calculated (or calculated/generated).

In addition, the control unit 150 uses the calculated (or calculated) second x value (e.g., latitude) and second y value (e.g., estimated altitude of launch origin/average sea level altitude of expected launch point). Calculate (or calculate/generate) the constructed second expected coordinates.

Additionally, the control unit 150 sets (or configures/generates) an expected launch origin section (or expected launch origin range) consisting of the calculated first expected coordinates and the calculated second expected coordinates.

That is, the control unit 150 creates an expected launch origin section (or launch origin point) of a preset geometric shape (including, for example, square, circle, oval, diamond, etc.) based on the calculated first expected coordinates and second expected coordinates. Set the expected area.

In this way, the control unit 150 uses a one-way linear regression analysis model consisting of longitude-altitude and latitude-altitude to determine the origin of the launch in order to limit detection data, influence the Earth's rotation, and simplify programs for building embedded systems. You can set the expected section.

At this time, the control unit 150 estimates the 3D flight trajectory by taking into account the fact that when estimating a 3D flight trajectory, an interaction between latitude and longitude occurs, which creates limitations when estimating the origin (or estimating the origin of launch). Three models can be used.

In addition, the control unit 150 creates a third one-way linear regression analysis model (or a third one-way linear regression equation) based on the coordinates of the point at which the confirmed pitch of the aircraft changes (or data before the pitch change). Construct (or create).

That is, the control unit 150 creates a two-dimensional plot diagram in which the x-axis is longitude and the y-axis is latitude based on the coordinates of the point at which the pitch of the confirmed aircraft changes (or data before the pitch change). Create (or write/configure).

In addition, the control unit 150 sets the longitude included in the previously extracted data before the pitch change as the x-axis (or x-coordinate), and the latitude included in the previously extracted data before the pitch change as the y-axis (or y-coordinate). Construct (or create) the third one-way linear regression analysis model.

In addition, the control unit 150 estimates the expected launch origin based on the configured (or generated) third one-way linear regression analysis model and the previously set launch origin expected section.

That is, the control unit 150 sets the first x value (for example, longitude) in the previously calculated first expected coordinate as the x value (or x coordinate), and calculates the Calculate (or calculate/generate/construct) the first expected launch origin estimated coordinates, which are configured by using the latitude value corresponding to the x value (or the first x value) as the y value (or y coordinate).

In addition, the control unit 150 sets the second x value (for example, latitude) in the previously calculated second expected coordinates as the y value (or y coordinate), and uses the Calculate (or calculate/generate/construct) the second expected emission origin estimated coordinates, which are configured by using the longitude value corresponding to the y value (or the second x value) as the x value (or x coordinate).

At this time, the control unit 150 performs another artificial intelligence-based machine learning based on the coordinates of the point where the pitch of the aircraft changes (or data before the pitch change), etc., based on another machine learning result. First expected coordinates, second expected coordinates, first expected launch origin estimated coordinates according to the first expected coordinates, second expected launch origin estimated coordinates according to the second expected coordinates, etc. are calculated (or calculated/generated).

That is, the control unit 150 uses the coordinates of the point at which the pitch of the aircraft changes (or data before the pitch change) as an input value of a preset expected launch origin estimation model to perform another machine learning (or another artificial intelligence) /another deep learning), and based on another machine learning result (or another artificial intelligence result/another deep learning result), a first expected coordinate, a second expected coordinate, and a first expected coordinate according to the first expected coordinate. Calculate (or calculate/generate) the estimated coordinates of the expected launch origin, the estimated coordinates of the second expected launch origin, etc. according to the second expected coordinates.

Additionally, the control unit 150 estimates the actual launch origin based on the calculated first and second expected launch origin coordinates.

That is, the control unit 150 sets (or creates/configures) a launch origin estimation section (or launch origin estimation range/area) consisting of the calculated first expected launch origin estimate coordinates and the second expected launch origin estimate coordinates. do.

At this time, the control unit 150 launches the preset geometric shape (including, for example, a square, a circle, an oval, a diamond, etc.) based on the calculated first expected launch origin estimate coordinates and the second expected launch origin estimate coordinates. Set the origin estimation section (or origin estimation area/range).

In addition, the control unit 150 considers the launch angle change in a vertical launch (cold launch) type vehicle (including, for example, a missile, etc.) and uses the first one-way linear regression analysis model to set the preset altitude. Calculate (or calculate) the longitude coordinate at (for example, 3,000 m), and calculate (or calculate) the latitude coordinate at the preset altitude using the second one-way linear regression analysis model. Here, the preset altitude takes into account the situation in which the aircraft is first captured by the detection system, and can be set (or selected) according to the designer's design from 2,700m to 3,300m, and can generally be set to 3,000m. In addition, the coordinates (longitude, degree) estimated at the point corresponding to the altitude of 3,000 m are similar to the actual launch origin. Here, the altitude estimated in the previous process is the actual altitude of the ground surface, but errors occur due to the vertical launch (cold launch) method, and the origin estimation error that occurs in the current weapon system is the error that occurs due to this vertical launch method. You can.

That is, the control unit 150 inputs the preset altitude (e.g., 3,000 m) as an input value of the first one-way linear regression analysis model, and generates an altitude corresponding to the preset altitude (e.g., 3,000 m). Calculate longitude coordinates, input the preset altitude (e.g., 3,000m) as an input value of the second one-way linear regression model, and obtain latitude coordinates corresponding to the preset altitude (e.g., 3,000m). Calculate .

In addition, the control unit 150 displays (or applies/projects) the longitude coordinates and latitude coordinates at the calculated preset altitude on the progress path (vector) to provide an estimated value located on the axis of the launch origin estimation section. Check (or calculate/create/construct). Here, the confirmed estimated value may be the actual launch origin coordinates (or the final launch origin estimated coordinates/actual launch origin/final launch origin). At this time, the progress path may be generated (or calculated/configured) based on the calculated first expected launch origin coordinates and the second expected launch origin estimate coordinates.

That is, the control unit 150 calculates another latitude coordinate by using the calculated longitude coordinate at the preset altitude as an input value of the third one-way linear regression analysis model, and calculates the latitude coordinate at the calculated preset altitude. is calculated as an input value of the third one-way linear regression analysis model, and the estimated value (or the actual launch origin coordinate/final launch coordinate) consisting of the calculated other longitude coordinate and the calculated other latitude coordinate is calculated. Check the estimated origin coordinates).

Additionally, the control unit 150 displays the confirmed estimated value on the display unit 130.

In addition, in actual use, the control unit 150 may use the calculated first estimated launch origin coordinates (or entry point coordinates), the calculated second expected launch origin coordinates (or final point coordinates), progress path, etc. is provided to an actual unmanned aerial vehicle (not shown), a reconnaissance aircraft (not shown), an artificial satellite (not shown), etc., and in the unmanned aerial vehicle, a reconnaissance aircraft, and an artificial satellite, from the first estimated launch origin coordinates to the second expected launch origin estimated coordinates. By intensively searching the path according to the progress path, the final estimated value (or final point) can be confirmed.

In the embodiment of the present invention, the case where the aircraft is a missile is mainly described, but it is not limited thereto, and the aircraft trajectory analysis device 100 detects/tracks anti-aircraft missiles (including, for example, Patriot missiles, etc.) during operation. When the radar is disabled, the technical features of the present invention can be applied to launch an anti-aircraft missile to an expected point, and then turn on the anti-aircraft missile's own radar at the entry point to enable shooting down an enemy aircraft.

In this way, the flight trajectory of the aircraft is generated based on the aircraft information collected from the detection system, the coordinates of the point where the pitch of the aircraft changes are confirmed based on the generated flight trajectory, and the identified point where the pitch of the aircraft changes is confirmed. Set the expected section of the launch origin using a one-way linear regression analysis model created based on the coordinates of , and create another one-way linear regression analysis model based on the coordinates of the point where the pitch of the confirmed aircraft changes. The launch origin can be estimated based on other one-way linear regression analysis models and the previously set launch origin expected section.

Hereinafter, the aircraft trajectory analysis method according to the present invention will be described in detail with reference to FIGS. 1 to 7.

Figure 2 is a flowchart showing a method of analyzing an aircraft trajectory according to an embodiment of the present invention.

First, the control unit 150 collects (or receives) aircraft information from a detection system (not shown). Here, the detection system includes aircraft, radar, etc.

In addition, the control unit 150 performs a preprocessing (or reclassification) function on the collected (or received) aircraft information (or radar information/data) to extract (or configure/generate) basic information. Here, the basic information includes latitude, longitude, altitude, speed, reception time of the data set, detection system name (or unique identification information of the detection system), etc. Additionally, the reception time of the data set corresponds to the time of collecting (or measuring) the corresponding latitude, longitude, altitude, etc. At this time, the extracted basic information is managed (or converted) into a preset format (or format) (for example, including extension csv format, etc.).

Additionally, the control unit 150 performs a sorting function on the extracted basic information according to a preset method. Here, the preset method (or sorting method) includes sorting in descending/ascending order according to latitude/longitude, sorting according to reception time of the data set, sorting by detection system, etc.

As an example, the first control unit 150 receives first aircraft information transmitted from the first detection system.

In addition, the first control unit performs a preprocessing function on the received first aircraft information, and selects first basic information (e.g., latitude, longitude, altitude, speed, reception time of the data set, (including the name of the first detection system, etc.) is extracted.

Additionally, the first control unit sorts the extracted first basic information according to the reception time of the data set (S210).

Thereafter, the control unit 150 determines the aircraft information (or aircraft information/basic information) based on the preprocessed (or reclassified/extracted) basic information, including the section (or section not included) in which the aircraft information (or aircraft information/basic information) is not captured. Generate a two-dimensional flight trajectory and/or three-dimensional flight trajectory of the aircraft for the entire flight section. Here, the aircraft (or projectile) includes ballistic missiles, missiles, etc.

That is, the control unit 150 generates (or configures) a two-dimensional flight trajectory of the aircraft based on the preprocessed (or reclassified/extracted) basic information. At this time, in the two-dimensional flight trajectory of the aircraft, the x-axis represents the flight distance and the y-axis represents the altitude. In addition, the flight distance is generated by calculating the distance between each aircraft information (including, for example, latitude, longitude, etc.) from the first capture point (including, for example, latitude, longitude, etc.) of the corresponding aircraft.

Here, the control unit 150 generates (or configures) a two-dimensional flight trajectory of the aircraft by applying the Loess technique or the Lowess technique to the preprocessed (or reclassified/extracted) basic information, and applies the Loess technique. At this time, the f value (or luminance value) can be any one of 0.28 to 0.32. At this time, when applying a two-dimensional flight trajectory, it may be advantageous to apply the Loess technique. In addition, the control unit 150 generates flight trajectories for two-stage propulsion aircraft (including, for example, Iskandar missiles, etc.), and the level can be used when compared with the actually collected aircraft information (or missile capture data/information). You can create a two-dimensional flight trajectory of the aircraft.

Additionally, the control unit 150 generates (or configures) a 3D flight trajectory of the aircraft based on the preprocessed (or reclassified/extracted) basic information. At this time, in the case of the 3D flight trajectory of the aircraft, only the Lowess method can be applied, and the f value (or luminance value) can be any one of 0.28 to 0.32. Here, in the three-dimensional flight trajectory of the aircraft, the x-axis represents latitude, the y-axis represents longitude, and the z-axis represents altitude.

In addition, the control unit 150 extracts a preset number of samples (for example, 1,000) from the z-axis (or altitude) trajectory and creates symmetrical x-axis (or latitude) and y-axis (or longitude) coordinate values. Obtain and generate a 3-dimensional flight trajectory (for example, x2, y2, z2) of the aircraft consisting of three variables. At this time, the data reconstructing the 3D flight trajectory in a preset format (including, for example, "*.csv" format, etc.) can be used as basic statistical analysis data for various pictures or tracks.

That is, the control unit 150 generates a two-dimensional flight trajectory of the aircraft based on the preprocessed (or reclassified/extracted) basic information, and the preset flight trajectory is determined from the generated two-dimensional flight trajectory of the aircraft. A number of samples (for example, 1,000) are extracted, and the extracted preset number of samples are combined with the altitude on the actual data to generate a three-dimensional flight trajectory of the aircraft.

In addition, the control unit 150 displays the generated two-dimensional flight trajectory of the aircraft, the three-dimensional flight trajectory of the aircraft, etc. on the display unit 130.

In this way, the control unit 150 controls the flight of the aircraft including a section (or section not included) in which the aircraft information (or basic information) is not captured based on the preprocessed (or reclassified/extracted) basic information. A 2D flight trajectory and/or a 3D flight trajectory of the aircraft can be generated for the entire section.

As an example, the first control unit generates a two-dimensional flight trajectory of the first aircraft corresponding to the first aircraft information based on the sorted first basic information.

Additionally, the first control unit generates a three-dimensional flight trajectory of the first aircraft corresponding to the first aircraft information based on the aligned first basic information.

In addition, as shown in FIGS. 3 and 4, the first control unit displays the generated two-dimensional flight trajectory of the first aircraft, the three-dimensional flight trajectory of the first aircraft, etc. on the first display unit 130. Do it (S220).

Thereafter, the control unit 150 sets a point at which the pitch (or elevation angle) of the aircraft changes based on the information about the generated two-dimensional flight trajectory and/or the information about the generated three-dimensional flight trajectory. Check the coordinates (including latitude, longitude, etc.).

In addition, the control unit 150 extracts data before the pitch change from the basic information based on the coordinates of the point where the confirmed pitch (or elevation angle) of the corresponding aircraft changes. At this time, the control unit 150 confirms the coordinates of the point where the pitch of the aircraft changes according to the administrator input (or administrator/user selection/touch/control) that confirmed the two-dimensional flight trajectory or the three-dimensional flight trajectory ( or select).

In other words, the control unit 150 accurately uses data before the pitch of the aircraft changes in order to estimate the launch origin of the aircraft, so the coordinates before the pitch of the aircraft changes (or the coordinates before the pitch of the aircraft changes) In order to check the section coordinates, the x-axis sections of the two-dimensional flight trajectory and/or the three-dimensional flight trajectory are classified (or divided/divided) into preset intervals to create a plurality of sections.

Additionally, the control unit 150 calculates (or calculates) the slope for each section for each of the plurality of sections created. At this time, the control unit 150 may calculate the slope for each of the plurality of created sections through differentiation. Here, the slope may be an angle with the ground (or an angle formed with the ground).

Additionally, the control unit 150 identifies a specific section that exceeds (or deviates from/is above) a preset reference value (or reference range) among the calculated slopes for each section. At this time, the control unit 150 can check the first section that exceeds the reference value among the calculated slopes for each section.

In addition, the control unit 150 selects the basic information based on information about a specific section (including, for example, coordinate information, etc.) exceeding the confirmed reference value corresponding to the coordinates of the point where the pitch of the aircraft changes. , data from the initial data of the basic information (or coordinates of the first capture point) to the section immediately preceding the specific section exceeding the confirmed reference value are extracted as the data before the pitch change. Here, the data before the pitch change includes latitude, longitude, altitude, etc.

For example, the first control unit classifies the Create.

Additionally, the first control unit calculates the first to 100th slopes for each section for the generated first to 100th sections.

Additionally, the first control unit determines a 31st section that exceeds the reference value among the calculated first slope corresponding to the first section to the 100th slope corresponding to the 100th section.

In addition, as shown in FIG. 5, the first control unit controls information from 1-1 information, which is the first data of the first basic information, to the 30th section before the confirmed 31st section among the first basic information. The 1-30th information, which is the data, is extracted, and data before the first pitch change including the extracted 1-1st to 1-30th information is generated (S230).

Afterwards, the control unit 150 must calculate the estimated latitude origin and the estimated longitude origin, respectively, considering the fact that the flight trajectory of the aircraft is curved due to the influence of the Earth's rotation, so that the pitch of the confirmed aircraft changes. Based on the coordinates of the point (or data before the pitch change), the first one-way linear regression analysis model (or first one-way linear regression equation) and the second one-way linear regression analysis model (or second one-way linear regression) Construct (or create) each equation.

That is, the control unit 150 uses the longitude included in the previously extracted data before the pitch change as the x-axis (or x-coordinate), and the altitude included in the previously extracted data before the pitch change as the y-axis (or y-coordinate). Construct (or create) the first one-way linear regression analysis model.

In addition, the control unit 150 generates a first x value ( For example, calculate (or calculate) hardness. Here, the mean sea level (MSL) of the expected launch point of the aircraft refers to the characteristics of the terrain from which an aircraft (including, for example, missiles, etc.) can be launched, which is flat, and the sea level altitude of the flat is 110 m in most cases. The average sea level altitude of the expected launch point described in the embodiment of the present invention may be 110 m by default, and may be set differently depending on the designer's design.

In addition, the control unit 150 uses the calculated (or calculated) first x value (e.g., longitude) and first y value (e.g., estimated altitude of launch origin/average sea level altitude of expected launch point). Calculate (or calculate/generate) the configured first expected coordinates.

In addition, the control unit 150 uses the latitude included in the previously extracted data before the pitch change as the x-axis (or x-coordinate), and the altitude included in the previously extracted data before the pitch change as the y-axis (or y-coordinate). Construct (or create) a second one-way linear regression analysis model.

In addition, the control unit 150 generates a second x value ( For example, calculate (or calculate) latitude.

In addition, the control unit 150 uses the calculated (or calculated) second x value (e.g., latitude) and second y value (e.g., estimated altitude of launch origin/average sea level altitude of expected launch point). Calculate (or calculate/generate) the constructed second expected coordinates.

Additionally, the control unit 150 sets (or configures/generates) an expected launch origin section (or expected launch origin range) consisting of the calculated first expected coordinates and the calculated second expected coordinates.

That is, the control unit 150 creates an expected launch origin section (or launch origin point) of a preset geometric shape (including, for example, square, circle, oval, diamond, etc.) based on the calculated first expected coordinates and second expected coordinates. Set the expected area.

As an example, the first control unit uses a first one-way linear regression analysis model with the longitude included in the data before the first pitch change as the x-axis and the altitude included in the data before the first pitch change as the y-axis. Compose.

In addition, the first control unit determines a first ) is calculated.

Additionally, the first control unit calculates first expected coordinates consisting of the calculated first x value (e.g., longitude) and first y value (e.g., estimated altitude of launch origin/110 m).

In addition, the first control unit configures a second one-way linear regression analysis model with the latitude included in the data before the first pitch change as the x-axis and the altitude included in the data before the first pitch change as the y-axis. do.

In addition, the first control unit determines a second ) is calculated.

Additionally, the first control unit calculates second expected coordinates consisting of the calculated second x value (e.g., latitude) and the second y value (e.g., estimated altitude of launch origin/110 m).

Additionally, the first control unit sets a first expected launch origin section in a preset square shape based on the calculated first expected coordinates and the calculated second expected coordinates (S240).

Thereafter, the control unit 150 creates a third one-way linear regression analysis model (or a third one-way linear regression equation) based on the coordinates of the point at which the confirmed pitch of the aircraft changes (or data before the pitch change). Construct (or create).

That is, the control unit 150 creates a two-dimensional plot diagram in which the x-axis is longitude and the y-axis is latitude based on the coordinates of the point at which the pitch of the confirmed aircraft changes (or data before the pitch change). Create (or write/configure).

In addition, the control unit 150 sets the longitude included in the previously extracted data before the pitch change as the x-axis (or x-coordinate), and the latitude included in the previously extracted data before the pitch change as the y-axis (or y-coordinate). Construct (or create) the third one-way linear regression analysis model.

In addition, the control unit 150 estimates the expected launch origin based on the configured (or generated) third one-way linear regression analysis model and the previously set launch origin expected section.

That is, the control unit 150 sets the first x value (for example, longitude) in the previously calculated first expected coordinate as the x value (or x coordinate), and calculates the Calculate (or calculate/generate/construct) the first expected launch origin estimated coordinates, which are configured by using the latitude value corresponding to the x value (or the first x value) as the y value (or y coordinate).

In addition, the control unit 150 sets the second x value (for example, latitude) in the previously calculated second expected coordinates as the y value (or y coordinate), and uses the Calculate (or calculate/generate/construct) the second expected emission origin estimated coordinates, which are configured by using the longitude value corresponding to the y value (or the second x value) as the x value (or x coordinate).

As an example, the first control unit generates a two-dimensional plot diagram in which the x-axis is longitude and the y-axis is latitude based on data before the first pitch change corresponding to the point at which the pitch of the confirmed first aircraft changes. .

In addition, the first control unit configures a third one-way linear regression analysis model with the longitude included in the data before the first pitch change as the x-axis and the latitude included in the data before the first pitch change as the y-axis. do.

In addition, the first control unit sets the first x value (for example, longitude) in the calculated first expected coordinates as an x value, and sets the first x value in the calculated first expected coordinates as the configured third Calculate the estimated coordinates of the first expected launch origin, using the output value (for example, latitude) calculated as an input value to the one-way linear regression model as the y value.

In addition, the first control unit sets the second x value (for example, latitude) in the calculated second expected coordinates as a y value, and sets the second The estimated coordinates of the second expected launch origin are calculated using the output value (e.g., longitude) calculated as the input value to the one-way linear regression model as the x value (S250).

Thereafter, the control unit 150 estimates the actual launch origin based on the calculated first and second expected launch origin coordinates.

That is, the control unit 150 sets (or creates/configures) a launch origin estimation section (or launch origin estimation range/area) consisting of the calculated first expected launch origin estimate coordinates and the second expected launch origin estimate coordinates. do.

At this time, the control unit 150 launches the preset geometric shape (including, for example, a square, a circle, an oval, a diamond, etc.) based on the calculated first expected launch origin estimate coordinates and the second expected launch origin estimate coordinates. Set the origin estimation section (or origin estimation area/range).

In addition, the control unit 150 considers the launch angle change in a vertical launch (cold launch) type vehicle (including, for example, a missile, etc.) and uses the first one-way linear regression analysis model to set the preset altitude. Calculate (or calculate) the longitude coordinate at (for example, 3,000 m), and calculate (or calculate) the latitude coordinate at the preset altitude using the second one-way linear regression analysis model.

That is, the control unit 150 inputs the preset altitude (e.g., 3,000 m) as an input value of the first one-way linear regression analysis model, and generates an altitude corresponding to the preset altitude (e.g., 3,000 m). Calculate longitude coordinates, input the preset altitude (e.g., 3,000m) as an input value of the second one-way linear regression model, and obtain latitude coordinates corresponding to the preset altitude (e.g., 3,000m). Calculate .

In addition, the control unit 150 displays (or applies/projects) the longitude coordinates and latitude coordinates at the calculated preset altitude on the progress path (vector) to provide an estimated value located on the axis of the launch origin estimation section. Check (or calculate/create/construct). Here, the confirmed estimated value may be the actual launch origin coordinates (or the final launch origin estimate coordinates). At this time, the progress path may be generated (or calculated/configured) based on the calculated first expected launch origin coordinates and the second expected launch origin estimate coordinates.

That is, the control unit 150 calculates another latitude coordinate by using the calculated longitude coordinate at the preset altitude as an input value of the third one-way linear regression analysis model, and calculates the latitude coordinate at the calculated preset altitude. is calculated as an input value of the third one-way linear regression analysis model, and the estimated value (or the actual launch origin coordinate/final launch coordinate) consisting of the calculated other longitude coordinate and the calculated other latitude coordinate is calculated. Check the estimated origin coordinates.

Additionally, the control unit 150 displays the confirmed estimated value on the display unit 130.

For example, as shown in FIG. 6, the first control unit sets a first emission origin estimation section consisting of the calculated first and second expected emission origin coordinates.

Additionally, the first control unit inputs the preset altitude as 3,000 m into the first one-way linear regression analysis model and calculates the first longitude coordinate at the corresponding altitude of 3,000 m.

Additionally, the first control unit inputs the preset altitude as 3,000 m into the second first-way linear regression model and calculates the first latitude coordinate at the corresponding altitude of 3,000 m.

In addition, the first control unit displays the calculated first longitude coordinate and the first latitude coordinate on the progress path, and displays the first final launch origin, which is the first estimated value located on the axis of the first launch origin estimation section. Check the estimated coordinates.

Additionally, as shown in FIG. 7, the first control unit displays the confirmed first final emission origin estimated coordinates on the first display unit (S260).

As described above, an embodiment of the present invention generates a flight trajectory of an aircraft based on aircraft information collected from a detection system, confirms the coordinates of the point where the pitch of the aircraft changes based on the generated flight trajectory, and Using a one-way linear regression analysis model created based on the coordinates of the point where the pitch of the confirmed aircraft changes, the expected launch origin section is set, and another one-way point is set based on the coordinates of the point where the pitch of the confirmed aircraft changes. Create a linear regression analysis model, estimate the launch origin based on the other generated one-way linear regression analysis model and the previously set launch origin expected section, estimate the flight trajectory of the aircraft without a 3D Kalman filter, type of ammunition for the aircraft, The launch origin of the aircraft can be estimated without prior database information on maximum altitude, flight trajectory, etc.

The above-described content can be modified and modified by anyone skilled in the art without departing from the essential characteristics of the present invention. Accordingly, the embodiments disclosed in the present invention are not intended to limit the technical idea of the present invention, but are for illustrative purposes, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be interpreted in accordance with the claims below, and all technical ideas within the equivalent scope should be construed as being included in the scope of rights of the present invention.

100: Aircraft trajectory analysis device
110: communication unit 120: storage unit
130: display unit 140: audio output unit
150: control unit

Claims (10)

A communication unit that receives aircraft information transmitted from the detection system; and
Performing a preprocessing function on the received aircraft information to extract basic information, generating at least one of a two-dimensional flight trajectory and a three-dimensional flight trajectory of the aircraft based on the basic information, and the generated two-dimensional flight trajectory Confirm the coordinates of the point where the pitch of the aircraft changes based on the information about or the information about the generated three-dimensional flight trajectory, and based on the coordinates of the point where the pitch of the confirmed aircraft changes, Extract the data before the pitch change from the basic information, construct the first one-way linear regression analysis model and the second one-way linear regression analysis model based on the confirmed data before the pitch change, respectively, and construct the first one-way linear regression analysis model constructed above. Based on the regression analysis model and the second one-way linear regression analysis model, first expected coordinates and second expected coordinates corresponding to the estimated altitude of the launch origin are calculated, respectively, and the calculated first expected coordinates and the calculated second expected coordinates are calculated. Set the launch origin expected section consisting of expected coordinates, configure a third one-way linear regression analysis model based on the data before the pitch change, and configure the third one-way linear regression analysis model and the set launch origin expected section. Air vehicle trajectory analysis including a control unit that estimates the expected launch origin based on and estimates the actual launch origin based on the first expected launch origin estimated coordinates and the second expected launch origin estimated coordinates included in the estimated expected launch origin. Device. According to claim 1,
The above basic information is,
An aircraft trajectory analysis device comprising at least one of latitude, longitude, altitude, speed, data set reception time, and detection system name. Extracting basic information by performing a preprocessing function on the aircraft information collected from the detection system by the control unit;
Generating, by the control unit, at least one of a two-dimensional flight trajectory and a three-dimensional flight trajectory of the aircraft based on the basic information;
Confirming, by the control unit, the coordinates of a point where the pitch of the aircraft changes based on information about the generated two-dimensional flight trajectory or information about the generated three-dimensional flight trajectory;
extracting, by the control unit, data prior to a pitch change from the basic information based on the coordinates of a point where the pitch of the confirmed aircraft changes;
Constructing, by the control unit, a first one-way linear regression analysis model and a second one-way linear regression analysis model based on the confirmed data before the pitch change;
calculating, by the control unit, first expected coordinates and second expected coordinates corresponding to the estimated altitude of the launch origin based on the configured first one-way linear regression analysis model and the second one-way linear regression analysis model;
Setting, by the control unit, an expected launch origin section consisting of the calculated first expected coordinates and the calculated second expected coordinates;
Constructing, by the control unit, a third one-way linear regression analysis model based on the data before the pitch change;
estimating, by the control unit, an expected emission origin based on the configured third one-way linear regression analysis model and the set emission origin expected section; and
An aircraft trajectory analysis method comprising the step of estimating, by the control unit, an actual launch origin based on the first expected launch origin estimated coordinates and the second expected launch origin estimated coordinates included in the estimated expected launch origin. According to claim 3,
The step of generating at least one of a two-dimensional flight trajectory and a three-dimensional flight trajectory of the aircraft,
A process of generating a two-dimensional flight trajectory of the aircraft by applying the Loess technique or the Lowess technique to the basic information; and
An aircraft trajectory analysis method comprising at least one process of generating a three-dimensional flight trajectory of the aircraft by applying the Lowess technique to the basic information. According to claim 3,
The step of checking the coordinates of the point where the pitch of the aircraft changes is,
A process of generating a plurality of sections by classifying the x-axis sections of the two-dimensional flight trajectory or the three-dimensional flight trajectory into preset intervals;
A process of calculating a slope for each section for each of the plurality of sections created;
A process of confirming a specific section that exceeds a preset reference value among the calculated slopes for each section; and
An aircraft trajectory analysis method comprising: correlating information about a specific section exceeding the confirmed reference value with coordinates of a point at which the pitch of the aircraft changes. According to claim 5,
The step of extracting data before pitch change from the basic information is,
Based on information about a specific section exceeding the confirmed reference value corresponding to the coordinates of the point where the pitch of the aircraft changes, from the basic information, a specific section exceeding the confirmed reference value from the initial data of the basic information An aircraft trajectory analysis method characterized by extracting data up to the immediately preceding section as data before the pitch change. According to claim 3,
The step of constructing the first one-way linear regression analysis model and the second one-way linear regression analysis model, respectively,
A process of constructing the first one-way linear regression analysis model with the longitude included in the extracted data before the pitch change as the x-axis and the altitude included in the extracted data before the pitch change as the y-axis; and
Characterized by comprising the process of constructing a second one-way linear regression analysis model with the latitude included in the extracted data before the pitch change as the x-axis and the altitude included in the extracted data before the pitch change as the y-axis. Air vehicle trajectory analysis method. According to claim 7,
The step of calculating first expected coordinates and second expected coordinates respectively corresponding to the estimated altitude of the launch origin,
A process of calculating a first x value corresponding to the average sea level altitude of the expected launch point of the aircraft corresponding to the longitude origin estimate based on the configured first one-way linear regression analysis model;
A process of calculating first expected coordinates consisting of the calculated first x value and a first y value corresponding to the estimated altitude of the launch origin;
A process of calculating a second x value corresponding to the average sea level altitude of the expected launch point of the aircraft corresponding to the latitude origin estimate based on the configured second one-way linear regression analysis model; and
An aircraft trajectory analysis method comprising calculating second expected coordinates consisting of the calculated second x value and a second y value corresponding to the estimated altitude of the launch origin. According to claim 3,
The step of estimating the expected launch origin based on the configured third one-way linear regression analysis model and the set launch origin expected section,
A first expected launch origin configured by using the first x value in the first expected coordinates as an x value, and the latitude value corresponding to the first The process of calculating estimated coordinates; and
A second expected launch origin configured by using the second Including the process of calculating estimated coordinates,
The expected launch origin is,
An aircraft trajectory analysis method comprising the first estimated launch origin estimated coordinates and the second expected launch origin estimated coordinates. According to claim 3,
The step of estimating the actual launch origin is,
A process of setting an estimated origin point section consisting of the first estimated origin point estimated coordinates and the second expected origin point estimated coordinates;
Calculating longitude coordinates at a preset altitude using the first one-way linear regression model, and calculating latitude coordinates at the preset altitude using the second one-way linear regression model;
A process of displaying the calculated longitude coordinates and latitude coordinates at the preset altitude on the progress path (vector) and confirming the estimated value located on the axis of the estimated launch origin point section; and
An aircraft trajectory analysis method comprising the step of estimating the confirmed estimated value as the actual launch origin.

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