Claims:1. A system (100) for rescuing a plurality of aircraft, the system comprising:
a rescue engine (102) operatively coupled to a memory (104), the memory storing instructions executable by the rescue engine configured to:
receive a set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters;
compute, from the received set of input data, a matrix of feasibility to rescue the plurality of aircraft on the available airbases; and
compute optimal route for each of the plurality of aircraft by generation of rescue points for each of the plurality of aircraft such that the rescue mission for the plurality of aircraft is performed simultaneously,
wherein, upon reaching the rescue points, the alignment of the plurality of aircraft with the runway of the airbase is performed, and wherein critical commands are being generated at a time interval to ensure safe landing of the plurality of aircraft on the desired airbase.
2. The system as claimed in claim 1, wherein the matrix of feasibility is computed based on fuel sufficiency, weather conditions, visibility at the airbase, and runway availability of the received set of input data.
3. The system as claimed in claim 2, wherein the rescue engine (102) computes the weather condition based on crosswind component and headwind component.
4. The system as claimed in claim 1, wherein the optimal path is computed by calculating any or a combination of the desired heading, bearing, turn direction, speed, clock code and range of the plurality of aircraft.
5. The system as claimed in claim 4, wherein the rescue engine (102) is configured to, on detection of deviation from the path, activate corresponding feedback to counter the deviation.
6. The system as claimed in claim 5, wherein the rescue engine (102) configured to maintain continuous alignment of the deviated aircraft with the path.
7. The system as claimed in claim 1, wherein the rescue points are computed based on the aircraft performance parameters that comprise any or a combination of aircraft height, fast rate of descent, slow rate of descent, speed of aircraft, fuel consumed, minimum crosswind speed, pilot rating and fuel left.
8. The system as claimed in claim 1, wherein the rescue engine (102) configured to alert an operator when the fuel level of the plurality of aircraft drops below a critical level, wherein at least one aircraft of the plurality of aircraft with a minimum fuel level is rescued at first stage followed by the other plurality of aircraft.
9. The system as claimed in claim 8, wherein at least one aircraft of the plurality of aircraft with the minimum fuel level reach the rescue points to align with the runway of the airbase.
10. A method (300) for rescuing a plurality of aircraft, the method comprising:
receiving (302), at a rescue engine, a set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters, the rescue engine operatively coupled to a memory;
computing (304), at the rescue engine, from the received set of input data, a matrix of feasibility to rescue the plurality of aircraft on the available airbases; and
computing (306), at the rescue engine, optimal route for each of the plurality of aircraft by generation of rescue points for each of the plurality of aircraft such that the rescue mission for the plurality of aircraft is performed simultaneously,
wherein upon reaching the rescue points, the alignment of the plurality of aircraft with the runway of the airbase is performed (308), wherein critical commands are being generated at a time interval to ensure safe landing of the plurality of aircraft on the desired airbase.
, Description:TECHNICAL FIELD
[0001] The present disclosure relates, in general, to air command and control system, and more specifically, relates to a system and method for the rescue of aircraft in an air command and control system.

BACKGROUND
[0002] Critical mission accomplishment has a high priority, but safe rescue of airplane is also crucial. Rescuing mission-critical aircraft involves, retrieving the aircraft from distress situation and land it safely at an airbase. The aircraft rescue process is quite complex and requires airport operator to work diligently with aircraft operator to recover aircraft. There are a lot of challenges in this process.
[0003] In a scenario, it is not feasible to rescue an aircraft with the available amount of fuel or it is not feasible to land on a particular airbase due to weather hazards. So, it becomes very challenging to re-route aircraft during rescue operations when encountered with critical situations such as runway unavailable or blocked, weather hazards such as high crosswind component at the airbase, low visibility at the airbase, insufficient fuel to land on the particular airbase.
[0004] Sometimes a situation arises when there are multiple aircraft in formation, which needs to be rescued. The challenge arises to bring all aircraft in a particular sequence by maintaining a certain distance and the aircraft with minimum fuel left has to be rescued first. It is generally seen that after completing a mission, the military aircraft request for safe recovery on the airbase. The challenge arises to find an optimum route that aircraft must take among the available n routes (AA1, AA2…. AAn) to align with the direction of the runway of the airbase.
[0005] Few existing technologies in the field of air control system can include a Simulink model for an aircraft landing system using energy functions, however, this method does not provide a solution for the critical situations of low fuel left with the aircraft. Another existing methodology of real-time ionosphere threat adaptation adjusts the ionosphere threat model in real-time. The mechanism improves the performance of the aircraft landing system. However, this method does not consider weather parameters such as crosswind component, wind speed and visibility which are crucial during rescue operations.
[0006] Another aircraft rerouting decision-making model under severe weather is known in the art, the model is based on aircraft flight regulations considering severe weather, flight forbidden area (FFAs), self-situation of aircraft and aircraft flight coordination. The mechanism presents a simplified model to determine effectively whether the aircraft can change its speed to avoid severe weather. However, this method does not provide the solution for rerouting in case the runway of the airbase is blocked or visibility is low at that airbase. Another known method includes planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, however, this method does not provide a path based on fuel left on aircraft and the type of tactic to be used to rescue an aircraft on an appropriate airbase. The method and system for simultaneous recovery of multiple aircraft talk about rescuing multiple aircraft, however, no approach or technique has been provided by which it can be achieved. The method and system for tactics and feasibility solutions to rescue aircraft in air command and control systems mentions feasibility solutions, however, this system does not provide any solution in terms of multiple airbases, fuel feasibility or weather feasibility.
[0007] All the above-described known art provides solutions for rescuing aircraft but none of the methods provides tactic-based solutions. Also, none of the approaches has provided holistic solution considering critical scenarios of weather hazards, airbase not approachable, low fuel or solution for rescuing of multiple aircraft. Therefore, there is a need in the art to provide a simple and efficient method which can provide the matrix of feasibility of rescuing an aircraft on available airbases prior to the commencement of rescue operations so that timely action can be taken and provide the tactical solution for optimum path an aircraft must take.

OBJECTS OF THE PRESENT DISCLOSURE
[0008] An object of the present disclosure relates, in general, to air command and control system, and more specifically, relates to a system and method for the rescue of aircraft in an air command and control system.
[0009] Another object of the present disclosure provides a system that provides matrix of feasibility of rescuing an aircraft on available airbases.
[0010] Another object of the present disclosure provides a system that eliminates the problem of rerouting of aircraft during rescue operations.
[0011] Another object of the present disclosure provides a system that provides tactical solution for optimum path an aircraft must take.
[0012] Another object of the present disclosure provides a system that provides tactical solution based route by generation of rescue points for rescuing multiple aircraft simultaneously.
[0013] Another object of the present disclosure provides a system that takes into consideration weather conditions, hazards, runway availability, current fuel status and current position of aircraft at various checkpoints.
[0014] Another object of the present disclosure provides a system that automates the rescue procedure which provides guidance to aircraft throughout the rescue operation.
[0015] Another object of the present disclosure provides a system that generates commands for accelerate, ascend, descend, deaccelerate, desired course, range, turn commands and clock code by the system for manoeuvring of aircraft.
[0016] Another object of the present disclosure provides a system that is capable to handle 1000 tracks and can execute maximum 64 rescue operations for 100 airbases simultaneously.
[0017] Yet another object of the present disclosure provides a system that involves usage of various aircraft parameters, weather parameters, airbase information and target kinematics to perform rescue operation.

SUMMARY
[0018] The present disclosure relates, in general, to air command and control system, and more specifically, relates to a system and method for the rescue of aircraft in an air command and control system.
[0019] The present disclosure provides a feasibility solution on available airbases prior to the commencement of rescue operations. Track kinematics, fuel consumption and weather conditions are taken into consideration. It also provides a tactical approach for rescuing multiple aircraft simultaneously. The system has been designed taking into consideration weather elements such as wind speed, wind direction, visibility. Commands are being generated every 4 seconds by the system to provide guidance to keep aircraft aligned with the route. Any deviation from the route is being monitored by the system. The system is capable to handle 1000 tracks and can handle 64 rescue operations simultaneously. The present disclosure can be described in enabling detail in the following examples, which may represent more than one embodiment of the present disclosure.
[0020] In an aspect, the present disclosure provides a system for rescuing a plurality of aircraft, the system including a rescue engine operatively coupled to a memory, the memory storing instructions executable by the rescue engine configured to receive a set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters, compute, from the received set of input data, matrix of feasibility to rescue the plurality of aircraft on the available airbases and compute optimal route for each of the plurality of aircraft by generation of rescue points for each of the plurality of aircraft such that the rescue mission for the plurality of aircraft is performed simultaneously, wherein upon reaching the rescue points, the alignment of the plurality of aircraft with the runway of the airbase is performed, and wherein critical commands are being generated at a time interval to ensure safe landing of the plurality of aircraft on the desired airbase.
[0021] In an embodiment, the matrix of feasibility is computed based on fuel sufficiency, weather conditions, visibility at the airbase, and runway availability of the received set of input data.
[0022] In another embodiment, the rescue engine computes the weather condition based on crosswind component and headwind component.
[0023] In another embodiment, the optimal path is computed by calculating any or a combination of the desired heading, bearing, turn direction, speed, clock code and range of the plurality of aircraft.
[0024] In another embodiment, the rescue engine is configured to, on detection of deviation from the path, activate corresponding feedback to counter the deviation.
[0025] In another embodiment, the rescue engine configured to maintain continuous alignment of the deviated aircraft with the path.
[0026] In another embodiment, the rescue points are computed based on the aircraft performance parameters that comprise any or a combination of aircraft height, fast rate of descent, slow rate of descent, speed of aircraft, fuel consumed, minimum crosswind speed, pilot rating and fuel left.
[0027] In another embodiment, the rescue engine configured to alert an operator when the fuel level of the plurality of aircraft drops below a critical level, wherein at least one aircraft of the plurality of aircraft with a minimum fuel level is rescued at first stage followed by the other plurality of aircraft.
[0028] In another embodiment, at least one aircraft of the plurality of aircraft with the minimum fuel level reach the rescue points to align with the runway of the airbase.
[0029] In an aspect, the present disclosure provides a method for rescuing a plurality of aircraft, the method including receiving, at a rescue engine, a set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters, the rescue engine operatively coupled to a memory, computing, at the rescue engine, from the received set of input data, matrix of feasibility to rescue the plurality of aircraft on the available airbases; and computing, at the rescue engine, optimal route for each of the plurality of aircraft by generation of rescue points for each of the plurality of aircraft such that the rescue mission for the plurality of aircraft is performed simultaneously, wherein upon reaching the rescue points, the alignment of the plurality of aircraft with the runway of the airbase is performed, wherein critical commands are being generated at a time interval to ensure safe landing of the plurality of aircraft on the desired airbase.
[0030] 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
[0031] The following drawings form part of the present specification and 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.
[0032] FIG. 1A illustrates an exemplary representation of a system for rescue of aircraft in tactical scenario, in accordance with an embodiment of the present disclosure.
[0033] FIG. 1B illustrates an exemplary view of the wind components, in accordance with an embodiment of the present disclosure.
[0034] FIG. 2A illustrates an exemplary multiple aircraft landing approach, in accordance with an embodiment of the present disclosure.
[0035] FIG. 2B illustrates a schematic view of aircraft route to airbase, in accordance with an embodiment of the present disclosure.
[0036] FIG. 2C illustrates computation of optimal path and route alignment, in accordance with an embodiment of the present disclosure.
[0037] FIG. 3 illustrates an exemplary flow chart of a method for rescuing aircraft, in accordance with an embodiment of the present disclosure.

DETAILED DESCRIPTION
[0038] 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.
[0039] 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.
[0040] The present disclosure relates, in general, to air command and control system, and more specifically, relates to a system and method for the rescue of aircraft in an air command and control system. Safe landing of aircraft in tactical emergency situations like changing fuel level, airbase availability and weather conditions is a big challenge to safely land an aircraft.
[0041] The present disclosure provides a feasibility solution on available airbases prior to the commencement of rescue operations. Track kinematics, fuel consumption and weather conditions are taken into consideration. It also provides a tactical approach for rescuing multiple aircraft simultaneously. The system has been designed taking into consideration weather elements such as wind speed, wind direction, visibility. Commands are being generated every 4 seconds by the system to provide guidance to keep aircraft aligned with the route. Any deviation from the route is being monitored by the system. The system is capable to handle 1000 tracks and can handle 64 rescue operations simultaneously. The present disclosure can be described in enabling detail in the following examples, which may represent more than one embodiment of the present disclosure.
[0042] FIG. 1A illustrates an exemplary representation of a system for rescue of aircraft in tactical scenario, in accordance with an embodiment of the present disclosure.
[0043] Referring to FIG. 1A, system 100 can be configured to ensure a fail-safe rescue procedure of one or more aircraft. System 100 can include a rescue engine 102 and a database 104 (also interchangeably referred to as a memory 104). The rescue engine 102 coupled to the one or more aircraft, the rescue engine 102 configured to receive a set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters. The real-time aircraft data and airbase data are taken from Jepson maps or local data store. The rescue engine 102 is the core of system 100 and can compute the solutions based on the set of input data received. The present disclosure aims to generate the solution to rescue one or more aircraft by providing manoeuvring commands to guide aircraft to follow an optimum route to land on the desired airbase with the available runway.
[0044] In an embodiment, the present disclosure aims at providing a tactical solution for rescuing a friendly military aircraft on mission. System 100 is developed to be used in command, control, communications, computers, and intelligence (C4I) systems for defence purposes in air operations. In another embodiment, the track kinematics parameters can include speed, course position and the likes of one or more aircraft. The aircraft performance parameters can include fuel consumed, slow rate of descent (SROD), fast rate of descent (FROD), minimum crosswind speed, pilot rating, fuel left, and aircraft height. The airbase parameters can include airbase position and runway heading. The weather parameters can include wind speed, wind direction and visibility.
[0045] In another embodiment, prior to the commencement of rescue operations, it is imperative to compute the feasibility of rescuing one or more aircraft on available airbases. The rescue engine 102 can compute the rescue operations based on the received set of input data as described below:
[0046] Computation of feasibility Matrix: The rescue engine 102 can compute a matrix of feasibility for rescuing one or more aircraft on available airbases based on the track kinematics, fuel consumption and weather conditions of the received set of input data. The feasibility matrix provides the solution for the feasibility of rescuing one or more aircraft on all available airbases. It includes computation based on fuel sufficiency and weather feasibility considering weather elements such as crosswind component and visibility at the airbase.
[0047] Computation of optimal route: In this step, the optimal route is calculated for one or more aircraft to follow. It includes computation of route kinematics such as turn direction, heading, clock code, and alignment of one or more aircraft with route by providing all the calculated kinematics, where in case of aircraft deviates from its route, feedback is provided to correct the route.
[0048] Computation of rescue solution: After one or more aircraft is aligned to the route, rescuing of one or more aircraft begins. In this, rescuing multiple aircraft is done by the leader-follower concept. Aircraft with the least fuel left is made the leader and has to be rescued first and other aircraft are made the followers. Using aircraft performance parameters such as aircraft height, fast rate of descent, slow rate of descent and speed of aircraft, points are computed from where critical commands are generated for rescuing one or more aircraft. It generates the rescue solution in terms of the desired course, turn (left, right), bank angle, bearing, range and clock code.
[0049] In an embodiment, the rescue engine 102 configured to receive the set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters. The rescue engine 102 can compute, from the received set of input data, the matrix of feasibility to rescue the one or more aircraft on the available airbases and compute optimal route for each of the one or more aircraft by generation of rescue points for each of the one or more aircraft such that the rescue mission for the one or more aircraft is performed simultaneously. Upon reaching the rescue points, the alignment of the one or more aircrafts with the runway of the airbase is performed, where critical commands are being generated at a time interval to ensure safe landing of the one or more aircraft on the desired airbase.
[0050] The matrix of feasibility is computed based on fuel sufficiency, weather conditions, visibility at the airbase, and runway availability of the received set of input data. The rescue engine 102 can compute the weather condition based on crosswind component and headwind component. The optimal path is computed by calculating any or a combination of the desired heading, bearing, turn direction, speed, clock code and range of one or more aircraft. The rescue engine 102 is configured to, on detection of deviation from the path, activate corresponding feedback to counter the deviation. The rescue engine 102 configured to maintain continuous alignment of the deviated aircraft with the path.
[0051] The rescue points are computed based on the aircraft performance parameters that include any or a combination of aircraft height, fast rate of descent, slow rate of descent, speed of aircraft, fuel consumed, minimum crosswind speed, pilot rating and fuel left. The rescue engine 102 configured to alert an operator when the fuel level of the one or more aircraft drops below a critical level, where at least one aircraft of the one or more aircraft with a minimum fuel level is rescued at first stage followed by the other follower aircraft, where at least one aircraft of the one or more aircraft with the minimum fuel level reach the rescue points to align with the runway of the airbase.
[0052] In another embodiment, the present disclosure aims to generate the solution to rescue one or more aircraft by providing manoeuvring commands to guide aircraft to follow the optimum route to land on the airbase with an available runway. The feasibility matrix represents the feasible scenarios of rescuing one or more aircraft on available airbases, where one or more aircraft based on fuel sufficiency and weather conditions such as visibility, wind, cloud at that airbase are considered. The proposed method checks the feasibility of aircraft landing on the airbase. The first step is to filter the contender airbases for landing based on the proximity of the airbases and one or more aircraft.
[0053] For example, in a scenario, there can be n number of airbases (b1, b2…bn), where aircraft A1 can be rescued. Airbase position (bx, by) and aircraft position (ax, ay) may be taken from Jepson maps and local data store. Sorting algorithms are applied to filter the probable airbases based on the complexity O(n*n). The second step is to compute the feasibility of rescuing one or more aircraft based on the visibility of the pilot on the airbase. The visibility factor is associated with the airbase which can be measured by visibility sensors deployed at the airbase. Similarly, the pilot has also associated visibility which is the range over which the pilot of an aircraft can sight and identify objects. Let v1 is the visibility of the airbase and v2 is the visibility of the pilot. If v1< v2, then rescue at airbase b1 is not feasible.
[0054] FIG. 1B illustrates an exemplary view of the wind components, in accordance with an embodiment of the present disclosure. Another step is to compute the feasibility of rescuing one or more aircraft based on the wind speed and its direction, which plays an important role while rescuing one or more aircraft. The wind is decomposed into vector form (wx, wy). The horizontal component of wind is the crosswind component and the vertical component is the headwind component as shown in FIG. 1B. Angle A is the angle between the nose of the aircraft and the wind direction called the relative wind angle. Angle B is the angle between the beam of the aircraft and the wind direction. Crosswind component (Cw) of the weather can be calculated as
Cw = Ws* sin (Wd),
where Ws is the wind speed and
Wd is the wind direction.
[0055] If crosswind speed (s) of an aircraft (A1) is greater than the crosswind component (Cw) of the weather at the airbase (b1), then rescue is not feasible at airbase b1. After computing the weather feasibility, runway availability is monitored. If left runway (L) is blocked, right runway(R) is considered. If both the runways are blocked, then parallel taxi track (PTT) is to be opted.
[0056] Last step is to compute the fuel required for the rescue operation of one or more aircrafts and compute the feasibility of landing the aircraft A1 on the airbase b1 with available amount of fuel at height bands h1, h2….hn. In this method, fuel required can be calculated as
FR=(FC/60) * t,
where FC is fuel consumption per minute at a certain height band,
FR is fuel required and
t is the time required computed by system.
If FR <=FL, where FL is fuel left in aircraft, it indicates that no fuel in reserve is required and aircraft can be landed safely with the given amount of fuel and vice versa. In case, reserve fuel is required, can be calculated as FRS = FR-FL, where FRS is reserved fuel required, FR is fuel required and FL is fuel left in aircraft.
[0057] A consolidated feasibility matrix for n bases is presented in terms of following table:
Airbase Fuel Available Fuel required Runaway status PTT Cross wind Visibility
b1 f1 fr1 blocked Available Low High
b2 f2 fr2 blocked Not available High Low
bn fn frn Not blocked NA Low Low
Table 1: Feasibility Matrix Table
[0058] The embodiments of the present disclosure described above provide several advantages. The one or more of the embodiments provide tactical solution-based route by the generation of rescue points for rescuing multiple aircraft simultaneously and eliminate the problem of rerouting of aircraft during rescue operations. System 100 takes into consideration weather conditions, hazards, runway availability, current fuel status and current position of aircraft at various checkpoints to automate the rescue procedure to guide one or more aircraft throughout the rescue operation. System 100 generates commands for accelerate, ascend, descend, deaccelerate, desired course, range, turn commands and clock code by the system for manoeuvring of aircraft. Further, system 100 is capable to handle 1000 tracks and can execute maximum of 64 rescue operations for 100 airbases simultaneously
[0059] FIG. 2A illustrates exemplary multiple aircraft landing approach 200, in accordance with an embodiment of the present disclosure.
[0060] Referring to FIG. 2A, when one or more aircraft in formations are to be rescued, multiple aircraft landing approaches can be implemented. In this type of approach, at least one aircraft of one or more aircraft, which has minimum fuel is made the leader aircraft and others are made the follower aircraft. Minimum separation distance has to be maintained between one or more aircraft. No separate turn and descend commands are issued for the follower tracks. At least one aircraft which has minimum fuel can be rescued first.
[0061] For example, A1, A2, A3…An are aircraft, which needs to be rescued to an airbase B1. P1, P2 and P3 …Pn are the respective points to be computed by system 100, where leader aircraft can be brought to P1 and others at P2…Pn respectively. To bring the leader aircraft A1 to point P1, system 100 can first order the formation to arrive some distance farther from the point P1.
[0062] FIG. 2B illustrates a schematic view of aircraft route to airbase, in accordance with an embodiment of the present disclosure. Firstly, leader aircraft is brought to point Pa from point P1 and is commanded to align with the safety lane of the runway. Similarly, other aircraft are also brought from points P2 and P3 …Pn to Pa. As shown in FIG. 2B, Pa, Pb, Pc are the points (also interchangeably referred to as rescue points) on which critical commands are generated. Pa is computed using the aircraft height at point Pa, fast rate of descent, slow rate of descent, speed of aircraft. Similarly, other points are computed. Distances can be computed as: Length from runway to Pa = Lbb + Lbc+ Lab,
where Lbb is configurable.
Lbc= speed_SROD * (Hc-Hb) / SROD and Lab = speed_FROD * (Ha-Hb) / FROD.
[0063] The main object is to bring the pilot to point Pa, at least one aircraft i.e., leader aircraft of one or more aircraft is brought from point Pa to point Pb at the fast rate of descent and from point Pb to point Pc at the slow rate of descent. At height Hc, the aircraft levels off and the pilot is expected to visually acquire the runway. Course correction commands can be issued with clock codes, where clock code is a clock position or clock bearing which is the direction of an object observed from an aircraft and range.
[0064] FIG. 2C illustrates computation of optimal path and route alignment, in accordance with an embodiment of the present disclosure. To land one or more aircraft to airbase, aircraft needs to be brought to the point from where one or more aircraft can land on airbase. Once an aircraft reaches the computed point, aircraft needs to get aligned with the runway of the airbase. As shown in FIG. 2C, Aircraft (A) on mission is to be rescued and needs to be landed on airbase, where (AA1, AA2…. AAn) are the available routes.
[0065] Optimal path is computed by computing the desired heading, speed, clock code and range. First step is to calculate the radius of turn, where it is the radius with which an aircraft can turn with a given bank angle. Radius of turn for an aircraft can be calculated as

Where,
Rt turning radius of the aircraft,
is the current true speed of the aircraft,
is the bank angle used by aircraft to turn, and
is 11.2.
[0066] The desired bearing is computed from aircraft to airbase. Turn direction (left, right), clock code is computed. To align aircraft with the route, feed of all these kinematics can be provided at a time interval e.g., every 4 second which aids in manoeuvring one or more aircraft to its airbase. In case the aircraft deviates from its path, course correction commands are provided by system 100 to reroute the aircraft to its route.
[0067] FIG. 3 illustrates an exemplary flow chart of a method 300 for rescuing aircraft, in accordance with an embodiment of the present disclosure.
[0068] Referring to FIG. 3, at block 302, the rescue engine can receive a set of input data pertaining to track kinematic parameters, aircraft performance parameters, airbase parameters and weather parameters, the rescue engine operatively coupled to a memory. At block 304, the rescue engine can compute from the received set of input data, matrix of feasibility to rescue the plurality of aircraft on the available airbases.
[0069] At block 306, the rescue engine can compute optimal route for each of the plurality of aircraft by generation of rescue points for each of the plurality of aircraft such that the rescue mission for the plurality of aircraft is performed simultaneously. At block 308, upon reaching the rescue points, the alignment of the plurality of aircraft with the runway of the airbase is performed, wherein critical commands are being generated at a time interval to ensure safe landing of the plurality of aircraft on the desired airbase.
[0070] 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 scope of the disclosure, as described in the claims.

ADVANTAGES OF THE PRESENT DISCLOSURE
[0071] The present disclosure provides a system that eliminates the problem of rerouting of aircraft during rescue operations.
[0072] The present disclosure provides a system that provides feasibility of rescuing an aircraft on available airbases.
[0073] The present disclosure provides a system that provides tactical solution for optimum path an aircraft must take.
[0074] The present disclosure provides a system that provides tactical solution based route by generation of rescue points for rescuing multiple aircraft simultaneously.
[0075] The present disclosure provides a system that takes into consideration weather conditions, hazards, runway availability, current fuel status and current position of aircraft at various checkpoints.
[0076] The present disclosure provides a system that automates the rescue procedure which provides guidance to aircraft throughout the rescue operation.
[0077] The present disclosure provides a system that generates commands for accelerate, ascend, descend, deaccelerate, desired course, range, turn commands and clock code by the system for manoeuvring of aircraft.
[0078] The present disclosure provides a system that is capable to handle 1000 tracks and can execute maximum 64 rescue operations for 100 airbases simultaneously.
[0079] The present disclosure provides a system that involves usage of various aircraft parameters, weather parameters, airbase information and target kinematics to perform rescue operation.