Claims:1. A system (100) for detecting real-time manoeuvres of one or more aircrafts, the system comprising:
an array of radars (110) adapted to receive a surveillance data collected for one or more aircrafts (102);
a multi-sensor tracker (212) coupled to the array of radars, the multi-sensor tracker adapted to identify, from the collected surveillance data, track data indicative of maneuvers of the one or more aircraft, the track data comprising a set of parameters pertaining to kinematic, non-kinematic and model probabilities;
an analytical engine (216) coupled to the multi-sensor tracker, the analytical engine adapted to receive the track data from the multi-sensor tracker, the analytical engine 216 comprising:
a contender track generator (218) adapted to generate contender track data that is stored in a database (222) for calculating release point of a launch object (104); and
a launch object release point generator (220) adapted to compare consecutive track data with the stored data fetched from the database by applying weight to each of the set of parameters, wherein, when course difference of the stored data with the consecutive track data breaches a threshold value, the probable release point of the launch object is determined.
2. The system as claimed in claim 1, wherein the contender track data is the list of eligible tracks for turn detection of the one or more aircrafts.
3. The system as claimed in claim 1, wherein the probable release point of the launch object is being transferred to a track monitoring unit (224) for display of the release point.
4. The system as claimed in claim 1, wherein the system comprises a system settings manager (214) adapted to filter upper and lower bound of the one or more aircrafts based on the kinematic parameters.
5. The system as claimed in claim 1, wherein the kinematic parameters comprise position, altitude and velocity components.
6. The system as claimed in claim 1, wherein the model probabilities of linear and nonlinear motion of the one or more aircraft (102) are calculated using straight and turn estimation of the track data to assign probability value, wherein target error matrix remove error from the estimation.
7. The system as claimed in claim 1, wherein the system (100) configured to receive surveillance data from the array of radars (110) with different revolutions per minute (RPM) and calculate the release point of the launch object (104) from the one or more aircraft (102) based on updated track data at variable update rates.
8. The system as claimed in claim 1, wherein the consecutive track data is received at the analytical engine (216) in out of sync manner with respect to timeframe, wherein interpolation and extrapolation techniques are used to estimate the correct state of the track data for weighted average calculation.
9. A method (500) for detecting real-time manoeuvre of one or more aircrafts, the method comprising:
receiving (502), at an array of radars, a surveillance data collected for one or more aircrafts;
identifying (504), at a multi sensor tracker, from the collected surveillance data, track data indicative of maneuvers of the one or more aircraft, the track data comprising set of parameters pertaining to kinematic, non-kinematic and model probabilities;
receiving (506), at an analytical engine, the track data, from the multi sensor tracker coupled to the the analytical engine;
generating (508), at a contender track generator, contender track data that is stored in a database for calculating release point of a launch object, the contender track data coupled to the analytical engine; and
comparing (510), at a launch object release point generator 220, the consecutive track data with the stored data fetched from the database by applying weight to each of the set of parameters, wherein, when course difference of the stored data with the consecutive track data breaches a threshold value, the probable release point of the launch object is determined.
, Description:TECHNICAL FIELD
[0001] The present disclosure relates, in general, to command-and-control systems, and more specifically, relates to a system and method for real-time manoeuvre detection of aircraft for release of daughter object and estimation of release point.

BACKGROUND
[0002] In the era of electronic warfare, there are a lot of aircrafts present in airspace that are detected by different sensors like radars and associated systems. Generally, all the detection, as well as data processing modules are part of command and control (C2) systems. The capacity of the C2 system has become stronger and more robust with new-age sensors that provide optimal and precise information about targets.
[0003] In tactical airspace, it is very difficult to distinguish the activity of an aircraft whether it is hostile or not, as the hostile aircraft carries out tactical movements to launch a gliding object with some patterns. The launch object will be named as daughter object. It means accurately identifying the target following a fixed pattern and is going to manoeuvre and release a gliding daughter object. Also, there is a big challenge to estimate the behaviour of a target at the start of the trajectory i.e., the number of inputs per target required to provide optimal results for daughter object release point calculation, from the turning point of aircraft and the detection of probable released daughter object. The track kinematic and non-kinematic information makes a better situation awareness of the daughter object prediction area by combining the inputs from various sensors and systems.
[0004] This situation awareness is then provided to different decision support sub-systems running in the C2 system. Detection of parent aircraft and calculation of daughter object release point should be across different geographical locations. Parent aircraft is referred here for the aircraft from which the daughter object is released. The operational efficiency of the system should not be hampered with this functionality; as such kind of daughter object release may not happen very frequently.
[0005] The introduction of systems like Laser-based ranging and modern radars have improved the error probability of daughter object delivery from aircraft. Advancements in technology have resulted in the invention of airborne electronics leading to significant improvements in daughter object controlling from aircraft. The speed of the daughter object depends on the speed of the parent aircraft and the altitude of the parent aircraft from which the daughter object is released. Modern systems have the capability to provide real-time information of parent aircraft and the release daughter object kinematics. However, it is very difficult to detect a target in the low altitude in hilly areas by single radar as the probability of detection is very low but in the multi-sensor scenario in C2 systems, it is able to detect and identify the aircraft and daughter object in low altitude and high clutter environment.
[0006] On the basis of information provided by multiple sources, the fused multi sensor contributed output is consistent in C2 systems and it improves the overall probability of detection as compare to single sensor/system. For real-time, manoeuvring targets, the trajectory of the aircraft is not having a fix pattern and can occur anytime/anywhere. Hence a method is needed for identifying such patterns. An example of such system and method is recited in a paper by Jerome H.Travert, the paper proposes solution for manoeuvre detection using quantitative evaluation of the flight data. However, fixed kinds of patterns (with fixed/constant turn angles) have been considered for manoeuvre identification in this paper. Another example recited in a paper Wang Yongjun et al, proposes the study of historical flight data from various sorties and creation of manoeuvre data library for manoeuvre detection. Various possible types of manoeuvre characteristics are studied for detecting manoeuvre of the same type by analysing the flight altitude of aircraft. The scope of this approach is limited to manoeuvre types that are stored in historical flight manoeuvre data library.
[0007] Another example recited in a paper by S.P. Puranik and J.K. Tugnait proposes multiple scan joint probabilistic data association (MSCAN-JPDA) technique was enhanced for large number of manoeuvring aircrafts where a filtering methodology was generated by utilizing MSCAN-JPDA technique and basic interacting multiple model (IMM) approach. However, the algorithm in this paper is applicable only to single sensor tracking. Yet another example recited in a paper by Bogler, P. L. provides methodology based on hypothesis testing of multiple models with different turn rate may increase the computation time of estimation process and the method needs a big detection window for the accurate estimation of aircraft turns, which makes the methodology computationally inefficient.
[0008] Although multiple system and methods exist today, these systems and methods suffer from significant drawbacks. Hence, it is desired to develop a means to detect real-time manoeuvre of aircraft in a way to determine probable impact point of released daughter object.

OBJECTS OF THE PRESENT DISCLOSURE
[0009] An object of the present disclosure relates, in general, to command-and-control systems, and more specifically, relates to a system and method for real-time manoeuvre detection of aircraft for release of daughter object and estimation of release point.
[0010] Another object of the present disclosure is to provide a system that operates on real-time target kinematics.
[0011] Another object of the present disclosure is to provide a system that validates the expected manoeuvre detection as per threshold.
[0012] Another object of the present disclosure is to provide a system that does not cater for any historical flight manoeuvre data library.
[0013] Another object of the present disclosure is to provide a system that provides real-time and reliable turn detection mechanism specific for daughter object releasing aircraft along with probable daughter object release point calculation in World Geodetic System (WGS-84) coordinates.
[0014] Another object of the present disclosure is to provide a system that is robust to decide whether the track is taking a specific turn for daughter object release.
[0015] Another object of the present disclosure is to provide a system that filters the irrelevant track data and declare the probable track for daughter object release point calculation.
[0016] Another object of the present disclosure is to provide a system that operate in real time with live sensor/system data and generates the output asynchronously.
[0017] Yet another object of the present disclosure is to provide a system that enables dynamic gating.

SUMMARY
[0018] The main objective of the present disclosure is to solve the technical problem as recited above by detecting real-time manoeuvre of aircraft in a way to determine probable impact point of released daughter object. The present disclosure does not store any fixed patterns but works on real-time target kinematics and uses an analytical engine to validate the expected manoeuvre detection as per threshold. The present disclosure does not cater for any historical flight manoeuvre data library and is designed for the turn detection by aircraft using some target history points and the model probabilities generated in the tracking part in a multi-sensor tracker. In the proposed solution, the target is the outcome of multi-sensor data fusion which is the fused output of multiple sensors. In the proposed method the gating is dynamic and resolve the issues of the technical problem as recited above.
[0019] The present disclosure aims at providing a real-time and reliable turn detection mechanism specific for daughter object releasing aircraft along with calculation of probable daughter object release point in World Geodetic System (WGS-84) coordinates. The combination of model probabilities for linear and nonlinear motion along with system configuration settings makes it robust to decide whether the track is taking a specific turn for daughter object release. Track error matrix based on the state estimate and measurements is also taken into consideration for the finalization of tracks for daughter object release point calculation. The system also stores the data of history trails in terms of all relevant kinematic and non-kinematic parameters of the targets. Stored history trails give the confidence to filter out the irrelevant track data and declare the probable track for daughter object release point calculation. The system is designed to work in real-time with live sensor/system data and generates the output asynchronously.
[0020] In an aspect, the present disclosure relates to a system for detecting real-time manoeuvre of one or more aircrafts, the system includes an array of radars adapted to receive a surveillance data collected for one or more aircrafts. A multi sensor tracker coupled to the array of radars, the multi sensor tracker adapted to identify, from the collected surveillance data, track data indicative of manoeuvres of the one or more aircraft, the track data comprising set of parameters pertaining to kinematic, non-kinematic and model probabilities. An analytical engine coupled to the multi sensor tracker, the analytical engine adapted to receive the track data from the multi sensor tracker, the analytical engine comprising a contender track generator adapted to generate contender track data and stored in a database for calculating release point of a launch object; and a launch object release point generator 220 adapted to compare consecutive track data with the stored data fetched from the database by applying weight to each of the set of parameters, wherein, when course difference of the stored data with the consecutive track data breaches a threshold value, the probable release point of the launch object is determined.
[0021] According to an embodiment, the contender track data is the list of eligible tracks for turn detection of the one or more aircrafts.
[0022] According to an embodiment, the system can include a system settings manager adapted to filter upper and lower bound of the one or more aircrafts based on the kinematic parameters.
[0023] According to an embodiment, the kinematic parameters can include position, altitude and velocity components.
[0024] According to an embodiment, the system configured to receive surveillance data from the array of radars with different revolutions per minute (RPM) and calculate the release point of the launch object from the one or more aircraft based on updated track data at variable update rates.
[0025] According to an embodiment, the consecutive track data is received at the analytical engine in out of sync manner with respect to timeframe, wherein interpolation and extrapolation techniques are used to estimate the correct state of the track data for weighted average calculation.
[0026] According to an embodiment, the model probabilities of linear and nonlinear motion of the one or more aircraft are calculated using straight and turn estimation of the track data to assign probability value, wherein target error matrix remove error from the estimation.
[0027] According to an embodiment, the probable release point of the launch object is being transferred to the track monitoring unit for display of the release point.
[0028] Various objects, features, aspects, and advantages of the inventive subject matter will become more apparent from the following detailed description of preferred embodiments, along with the accompanying drawing figures in which like numerals represent like components.

BRIEF DESCRIPTION OF THE DRAWINGS
[0029] The following drawings form part of the present specification are included to further illustrate aspects of the present disclosure. The disclosure may be better understood by reference to the drawings in combination with the detailed description of the specific embodiments presented herein.
[0030] FIG. 1 illustrates an exemplary representation of a system for detection of real-time manoeuvre of one or more aircrafts, in accordance with an embodiment of the present disclosure.
[0031] FIG. 2 illustrates a functional component integrated in the system, in accordance with an embodiment of the present disclosure.
[0032] FIG. 3 illustrates a high-level flow diagram of the target data received after multi sensor tracker application to contender track generator, in accordance with an embodiment of the present disclosure.
[0033] FIG. 4 illustrates a high-level flow diagram of the target data received from contender track generator to release point generator, in accordance with an embodiment of the present disclosure.
[0034] FIG. 5 illustrates a flow diagram of the method for real-time manoeuvre detection of one or more aircrafts, in accordance with an embodiment of the present disclosure.

DETAILED DESCRIPTION
[0035] The following is a detailed description of embodiments of the disclosure depicted in the accompanying drawings. The embodiments are in such detail as to clearly communicate the disclosure. If the specification states a component or feature “may”, “can”, “could”, or “might” be included or have a characteristic, that particular component or feature is not required to be included or have the characteristic.
[0036] As used in the description herein and throughout the claims that follow, the meaning of “a,” “an,” and “the” includes plural reference unless the context clearly dictates otherwise. Also, as used in the description herein, the meaning of “in” includes “in” and “on” unless the context clearly dictates otherwise.
[0037] The present disclosure relates, in general, to command and control systems, and more specifically, relates to a system and method for real-time manoeuvre detection of aircraft for release of daughter object and estimation of release point. The present disclosure is directed to systems and methods for manoeuver detection for daughter object release point detection of an air target, where the target motion is straight followed by manoeuvering pattern of an aircraft. The method comprises multiple model filtering for tracking by calculating the model probabilities of linear and nonlinear motion of the target. Upper and lower bound checking of kinematic parameters like position, height and velocity components are used to detect the target motion. Operations on a set of consecutive track reports make it possible to detect the trajectory of the daughter object releasing aircraft and calculate the release point. Model probabilities are derived from the filtering process of the tracking systems, which makes it more robust, as the filters are used to remove the error from the estimation. The system envisaged here is generic in the sense that it can be utilized in any C4I target tracking system. The description of terms and features related to the present disclosure shall be clear from the embodiments that are illustrated and described; however, the invention is not limited to these embodiments only. Numerous modifications, changes, variations, substitutions, and equivalents of the embodiments are possible within the scope of the present disclosure. Additionally, the invention can include other embodiments that are within the scope of the claims but are not described in detail with respect to the following description.
[0038] FIG. 1 illustrates an exemplary representation of a system for detection real-time manoeuvre of one or more aircrafts, in accordance with an embodiment of the present disclosure.
[0039] Referring to FIG. 1, system 100 for manoeuvre detection for daughter object release point detection of an air target. The system 100 can include aircraft 102 (also interchangeably referred to as parent aircraft 102, herein), daughter object 104 (also interchangeably referred to as launch object 104, herein) and an array of radars 110. The system 100 as shown in FIG. 1, in which there is a single aircraft 102 at an altitude of 25000- 40000 feet in which takes a turn which is supposed to be called release/impact point from where the daughter object 104 is being released.
[0040] The single air target (also referred to as aircraft 102, herein) is at 25000 feet to 40000 feet, which is detected by the multiple sensors 110 (also interchangeably referred to as an array of radars 110, herein). The aircraft 102 or parent aircraft is manoeuvring as per the pattern followed for releasing the daughter object 104 from a release point or impact point 106 and projected at on the surface 108. The platform is aircraft 102 here, which is detected by the array of the radars 110, which is geographically distributed for the consistent capture of the target. As it can be appreciated, the present disclosure may not be limited to only sensor but may be applicable for systems, which takes input from the multiple subsystems and airborne sensors.
[0041] The array of radars 110 adapted to receive surveillance data collected for one or more aircrafts 102. As shown in FIG. 2, a multi-sensor tracker 212 coupled to the array of radars 110, the multi-sensor tracker 212 adapted to identify, from the collected surveillance data, track data indicative of manoeuvers of the one or more aircraft 102. The track data can include a set of parameters pertaining to kinematic, non-kinematic and model probabilities. An analytical engine 216 coupled to the multi-sensor tracker 212 and adapted to receive the track data from the multi-sensor tracker 212. The analytical engine 216 can include a contender track generator 218 and a launch object release point generator 220.
[0042] In an embodiment, the contender track generator 218 adapted to generate contender track data and stored in a database 222 for calculating the release point of a launch object. The contender track data is the list of eligible tracks for turn detection of one or more aircrafts 102. The launch object release point generator 220 adapted to compare consecutive track data with the stored data fetched from the database 222 by applying weight to each of the set of parameters. The consecutive track data is received at the analytical engine 216 in out of sync manner with respect to timeframe, where interpolation and extrapolation techniques are used to estimate the correct state of the track data for weighted average calculation. When the course difference of the stored data with the consecutive track data breaches a threshold value, the probable release point of the launch object is determined.
[0043] The system 100 can include a system settings manager 214 adapted to filter upper and lower bound of the one or more aircrafts 102 based on the kinematic parameters, where the kinematic parameters can include position, altitude and velocity components. The model probabilities of linear and nonlinear motion of the one or more aircraft are calculated using straight and turn estimation of the track data to assign probability value, wherein target error matrix remove error from the estimation. The system configured to receive surveillance data from the array of radars 110 with different revolutions per minute (RPM) and calculate the release point of the launch object from the one or more aircraft based on updated track data at variable update rates.
[0044] The embodiments of the present disclosure described above provide several advantages. The present disclosure provides the system that operates on a real-time target kinematics. The system validates the expected manoeuvre detection as per threshold and does not cater for any historical flight manoeuvre data library. The system provides real-time and reliable turn detection mechanism specific for daughter object releasing aircraft along with probable daughter object release point calculation in World Geodetic System (WGS-84) coordinates. The system is robust to decide whether the track is taking a specific turn for daughter object release, filters the irrelevant track data and declare the probable track for daughter object release point calculation and enables dynamic gating.
[0045] FIG. 2 illustrates a functional component integrated in the system, in accordance with an embodiment of the present disclosure.
[0046] FIG. 2 conceptually depicts proposed disclosure which includes a high-end machine, processor 202, network manager 204, storage 206 and operating systems 208 and the application 210, which are responsible for tracking, target turn detection for daughter object release point calculation. Complete proposed disclosure is system of subsystems, where each subsystem has its own roles and responsibilities.
[0047] Input data (also referred to as surveillance data) is available from geographically distributed radar, airborne radar and networked systems attached in C4I systems. The input is in standard all-purpose structured Eurocontrol surveillance information exchange (ASTERIX) formats, where the ASTERIX as used herein refers to a standard for the exchange of air traffic services information. This includes target reports from the radars and systems for surveillance-related information. The multiple interfaces have been depicted for the radars and systems.
[0048] The input data is received via the network interface, which is running on the top of the operating system 208. The input data of the sensor system are received from the radar interface and heterogeneous systems’ interface that is sent to the message processors at the multi-sensor tracker 212 in a standard ASTERIX format. The sensor/system data is converted into the native format for further processing. Tracking is the initial step for daughter object release point calculation. The main steps of tracking are coordinate conversion, gating, association, filtering and track maintenance. In coordinate conversion, input data is converted from polar coordinates or latitude, longitude to East North Up (ENU) coordinate system. Gating and association are intermediate steps of multi-sensor tracking, filtering is used to estimate the position and error in the target and track maintenance is responsible for track creation, track update and deletion of the track. The filtering process generates the track kinematic parameters and the model probability.
[0049] Following data elements are generated from tracking process:
[0050] Track kinematic and non-kinematic parameters:
• Targets with latitude, longitude lying in particular geographical area are being considered for turn detection. The list of eligible tracks is called contender track list for turn detection.
• Speed and course in certain direction is being considered.
• If the altitude of a target lies in certain height bands, the target shall be considered for contender target calculation
• Call sign, Identification, friend or foe (IFF), type, subtype, identification of a target is being considered for contender track calculation.
[0051] Model parameters using filters:
• Model probabilities are also derived from the IMM filters which are used to detect the turn of a track contributed by the sensors.
• The filter state contains the track wise internal filter parameters and covariance matrix.
[0052] A system settings manager 214 is responsible for a set of configurable parameters which includes an area of interest in form of polygon to restrict the calculation i.e., tracks inside this area are to be used for daughter object detection. Lower and upper bounds of speed and height of target which is also in system settings manager 214 to scale up and down the system data handling capacity.
[0053] The system settings manager 214 coupled to the analytical engine 216, which is the most important part of the present disclosure, the analytical engine 216 takes the input from multi sensor tracker 212 as a target and system configuration from configuration manager. The analytical engine 216 is divided into two parts, where the two parts are contender track generator 218 and daughter object release point generator 220.
[0054] The contender track generator 218, as per the configuration/system settings available, filtering is applied on the area of interest to generate a solution for tracks taking turn and a contender track list is generated. The contender track data is stored in a local database 222 for daughter object release point calculation. The last ten history points are stored in the contender track data store for trajectory analysis.
[0055] In the daughter object release point generator 220, the set of real time reports from sensor system and the reports fetched from contender track database are computed upon as an initial step for daughter object release point calculation. This mathematical computation involves applying the weight to each kinematic parameter. The weighted average of these reports is then compared with respect to course recorded in the stored reports. If this difference breaches a threshold value, the last updated position in WGS-84 can be the probable point of release of the daughter object. The threshold value is configurable in system settings manager. Based on the behaviour of the data the threshold can be configured. The tracks may be received in out of sync manner, means the order of tracks received at analytical engine 216 may not be in order with respect to time frame. For weighted average calculation, interpolation and extrapolation techniques are used to estimate the correct state of the tracks for daughter object release point calculation.
[0056] FIG. 3 illustrates a high-level flow diagram of the target data received after multi sensor tracker application to contender track generator, in accordance with an embodiment of the present disclosure.
[0057] Referring to FIG. 3, the turn detection and impact point calculation method is described in the form of a flow chart. The target estimation using multi sensor tracker is the initial step for daughter object release point calculation. The estimation process uses the previous output of the time series data of the target and generates the new prediction and estimation of the target with the updated state and covariance matrix. Target data is the output of the multi-sensor tracker 212.
[0058] The method includes block 302, the track data is received by the analytical engine 216. At block 304, the state vector of the aircraft is determined using data from input reports i.e., velocity, altitude, the direction of motion and the like. At block 306, the mathematical quantification i.e., the weighted average is performed to further determine the influence of each of these parameters. At block 308, continuous processing of the tracks is performed, the probability value is assigned as per the straight and turn behaviour of tracks. At block 310, determine if the course difference threshold breaches. At block 312, continuous storage and updating of contender tracks and track history trails is performed.
[0059] FIG. 4 illustrates a high-level flow diagram of the target data received from contender track generator to release point generator, in accordance with an embodiment of the present disclosure.
[0060] The daughter object prediction area contains the points in the form of a polygon. Targets present in this area shall be considered for release point calculation. The model probability is being used to declare the target report is manoeuvring as per the configuration provided by system settings manager 214. At block 402, gating is performed by using velocity component of track from stored track report.
[0061] At block 404, the set of consecutive track reports is used for calculating the course difference of each report with their previously calculated weighted average. At block 406, if the course difference for that set of reports with current report breaches the threshold, the target is considered as contender for release of daughter object. This is a recursive process till the time a threshold is reached. At block 408, in the final step if all criteria are met, the probable impact point is being transferred to track monitoring unit 224 for display of the release point on the system.
[0062] FIG. 5 illustrates a flow diagram of the method 500 for real-time manoeuvre detection of one or more aircrafts, in accordance with an embodiment of the present disclosure.
[0063] Referring to FIG. 5, at block 502, the array of radars can receive the surveillance data from the one or more radar and system interfaces for one or more aircrafts. At block 504, the multi-sensor tracker identifies from the collected surveillance data, track data indicative of maneuvers of the one or more aircraft. The track data comprising set of parameters pertaining to kinematic, non-kinematic and model probabilities. At block 506, the analytical engine coupled to the multi sensor tracker, the analytical engine adapted to receive the track data from the multi sensor tracker. The analytical engine can include contender track generator 218 and launch object release point generator 220.
[0064] At block 508, the contender track generator 218 adapted to generate contender track data and stored in a database for calculating release point of a launch object. At block 510, the launch object release point generator 220 adapted to compare the consecutive track data with the stored data fetched from the database by applying weight to each of the set of parameters, wherein, when course difference of the stored data with the track data breaches a threshold value, the probable release point of the launch object is determined.
[0065] The method of detecting maneuvering aircraft and calculation of daughter object release point, wherein the following sequence of steps carried out asynchronously and recursively for available targets in data storage. The daughter object releasing contender target selection based on speed, altitude and target identity (friend or foe).
[0066] The estimates produced from the daughter object releasing aircraft detection are accurate, where straight and turn model estimates are being used for weighted average of the stored track history trails for considering linear and nonlinear target motion. The usage of target error matrix to determine the best fit targets for daughter object releasing aircraft turn detection. The out of sync data from multiple sensors does not impact the release point calculation results. The out of sync means the incoming target stream is not in order with respect to timeframe. The method is capable to handle out of sync scenario with the help of interpolation and extrapolation techniques.
[0067] The method can be scaled up and down as per the available target machine configuration. The provision of system configuration for daughter object prediction area in WGS-84 for track filtering. Filtering on target upper and lower bound is performed based on height and velocity component.
[0068] It will be apparent to those skilled in the art that the system 100 of the disclosure may be provided using some or all of the mentioned features and components without departing from the scope of the present disclosure. While various embodiments of the present disclosure have been illustrated and described herein, it will be clear that the disclosure is not limited to these embodiments only. Numerous modifications, changes, variations, substitutions, and equivalents will be apparent to those skilled in the art, without departing from the spirit and scope of the disclosure, as described in the claims.

ADVANTAGES OF THE PRESENT DISCLOSURE
[0069] The present disclosure provides a system that operates on real-time target kinematics.
[0070] The present disclosure provides a system that validates the expected manoeuvre detection as per threshold.
[0071] The present disclosure provides a system that does not cater for any historical flight manoeuvre data library.
[0072] The present disclosure provides a system that provides real-time and reliable turn detection mechanism specific for daughter object releasing aircraft along with probable daughter object release point calculation in World Geodetic System (WGS-84) coordinates.
[0073] The present disclosure provides a system that is robust to decide whether the track is taking a specific turn for daughter object release.
[0074] The present disclosure provides a system that filters the irrelevant track data and declare the probable track for daughter object release point calculation.
[0075] The present disclosure provides a system that enables dynamic gating.