System and method for reducing length of runway for aerial vehicle takeoff and landing

Abstract

The present Invention relates to a system for reducing the length of runway for aerial vehicle takeoff and landing and method thereof. The system of the present invention comprises of plurality of configurable solenoids placed on the underlying belly of the aerial vehicle and plurality of configurable solenoids placed on the both sides of runway. In an embodiment, this plurality of configurable solenoids at aerial vehicle and on both sides of runway creates an electro-magnetic force responsible for the overall functioning of the system. In an embodiment, there exits plurality of artificial intelligence units comprising atleast a sending unit in aerial vehicle, atleast a transceiver unit in Air Traffic Control (ATC) and atleast a receiving unit in runway which interact with each other and make sure that the aerial vehicle is correctly and optimally accelerated or decelerated as needed.

Description

Field of the Invention:The present invention relates to the field of runway management system. Particularly, theInvention provides a system for reducing the length of runway for aerial vehicle takeoff and landing and method thereof.Background of the Invention:The air traffic is booming around the world which is expected to soar exponentially in the coming years. Cheap airfares, efficient aircrafts and competition are making flying more accessible to the people. In order to cater the demand of such large number, a tremendous increase was seen in the number of aircrafts flying. The enormous increase in the number of passengers travelling worldwide over the period of time shows both challenges and unprecedented opportunities in the aviation sector. This level of growth in the sector will generate new routes, requires thousands of new airports and large number of new planes, pilots and runways in future which in turn will lead to increase in demand for land and construction of longer runway. To meet the demand for increased air travel, aircraft have become larger with more mass and more engine power and led to requirement of longer and wider runways. Further the aircrafts also requires power during takeoff and landing procedure. Runway plays an important role in the overall landing and takeoff procedure of the aircraft. Currently, available runway doesn't provide adequate power to the aircrafts, as a result of which the aircrafts requires longer runway for takeoff and landing procedure. An increase in the demand for runway involves extra cost, large area and other related requirements. Most populated cities in the world or especially in hilly areas faces land constraints where additional runways or longer runways require land acquisition or extending land into surrounding waters or in hilly areas.This problem can also be present in future space settlements wherein transportation is a costly affair. Space shuttles often require a lot of fuel for acceleration / deceleration during takeoff and landing. This is turn jacks up the operation cost and fuel consumption. This problem can also be present in present / future drone launching and arresting mechanisms where a lot of fuel is wasted when trying to takeoff a drone and sending it to its cruise altitude and descending and decelerating to land.In order to solve the problem in space settlements / stations an efficient system has to designed in such a way that minimal fuel is used in the arrival / departure of space shuttles and operation and maintenance cost is reduced. Additionally, a system and method that reduces the fuel consumed by a drone during the process of takeoff, landing and initial climb. Hence, there is need for a system and method that reduces the length of runway for aerial vehicle landing and takeoff procedure. There is a need for a more efficient system and method for effectively increasing airport throughput, particularly, a system in aerial vehicle and runway for safely accelerating or decelerating the aerial vehicle using much shorter runway. Also, there is a need of having an efficient system and method for reducing the cost involved in buying land and construction of a longer runway and thereby eliminating the need for extra runways and saving lots of money.Object(s) of the Invention:A primary object of the present invention is to overcome the drawbacks associated with theprior art.The primary object of the present invention is to provide a system for reducing the length ofrunway for aerial vehicle takeoff and landing by 50% and method thereof.Yet another object of the present invention is to provide a runway which solves theconventional aerial vehicle landing runway's shortcomings of long distance and large-arearequirement.Yet another object of the present invention is to provide an efficient landing and takeoffsystem by utilizing very less space.Yet another object of the present invention is to provide a novel and efficient system andmethod of safely accelerating or decelerating the aerial vehicle using much shorter runway.Yet another object of the present invention is to provide a system for reducing the timerequirement by an aerial vehicle for taking off and landing significantly and therebyincreasing the traffic movement of a runway.Yet another object of the present invention is to provide a system for increasing the trafficmovement capacity of a runway by way of pre-assigning the gate to the aerial vehicle duringlanding.Yet another object of the present invention is to provide power to an aerial vehicle on therunway to accelerate or decelerate and thereby reducing the length of runway required fortake-off and landing.Yet another object of the present invention is to provide a runway that can be used by morethan one aerial vehicle and thereby eliminating the need for extra runways.Yet another object of the present invention is to provide an accelerating or deceleratingrunway which is available for use depending upon the various factors to be considered duringtakeoff and landing and after use is automatically restored for reuse. Yet another object of the present invention is to provide a universal system involving accelerating and decelerating for all types of the aerial vehicle.Yet another object of the present invention is to reduce the landing and takeoff time by reducing the runway length and thereby leading to reduction in Airport traffic jams. Yet another object of the present invention is to provide a system for reducing the length of runway that does not require major structural change.Yet another object of the present invention is to provide the rapid exit taxiway to be made longer and wider and also its angle from the runway is very less and slowly curves away from the runway.Yet another object of the present invention is to provide the rapid exit taxiway made up of a material which has a higher frictional coefficient than the runway.Yet another object of the present invention is to provide a novel aerial vehicle and runway accelerating or decelerating unit which may be embodied in existing aerial vehicle and runways at low cost.Yet another object of the present invention is to provide a system for reducing the length of runway which is simple, efficient and cost effective.Yet another object of the present invention is to provide a solenoid-assisted system for take-off and landing of space shuttles.Yet another object of the present invention is to reduce fuel consumption by space shuttles by using solenoids to decelerate the craft during landing and to accelerate the craft during take¬off.Yet another object of the present invention is to provide a system for faster and more efficient drone landings and takeoff.Yet another object of the present invention is to provide a system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle. Yet another object of the present invention is to provide a method of operation of the system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle.Brief Description of the Drawings:To clarify advantages and features of the present invention, a more particular description of the invention will be rendered by reference to specific embodiments thereof, which is illustrated in the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. The invention will be described and explained with additional specificity and detail with the accompanying drawings in which:Fig. 1 illustrates an exemplary embodiment of the system and method as accordance with thepresent invention during takeoff procedure.Fig. 2 illustrates an exemplary embodiment of the system and method as accordance with thepresent invention during landing procedure.Fig. 3 illustrates an exemplary embodiment of the system and method as accordance with thepresent invention involving multiple agentsFig. 4 illustrates an exemplary embodiment of the system and method in the takeoffprocedure.Fig. 5 illustrates an exemplary embodiment of the system and method in the landingprocedure.Summary of the Invention:The present disclosure discloses a system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle and its method of operation thereof. In an aspect of the Invention, there is provided a system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, comprising:plurality of configurable solenoids having north pole and south pole placed on the underlying belling of the aerial vehicle configured to create an electro-magnetic field;plurality of configurable solenoids having north pole and south pole placed on the both sides of runway configured to create an electro-magnetic field; andplurality of artificial intelligence units, comprising:atleast a sending unit in aerial vehicle configured to control the plurality of configurable solenoids on aerial vehicle and send landing and / or takeoff procedure related information;atleast a transceiver unit in Air Traffic Control (ATC) configured to: receive and process the landing and / or takeoff procedure related information from said sending unit; andproduce and transmit the output for configuration of plurality of configurable solenoids on both sides of runway; andatleast a receiving unit in runway configured to receive the output from said transceiver unit and adjust the plurality of configurable solenoids placed on the both sides of runway for landing and / or takeoff procedure depending upon the produced output.In an another aspect of the Invention, there is provided a method of operation of the system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle as described above, comprising the steps of:a. atleast a sending unit in aerial vehicle sending landing and / or takeoffprocedure related information to atleast a transceiver unit in Air TrafficControl (ATC);b. receiving and processing the landing and / or takeoff procedure relatedinformation by said transceiver unit from said sending unit;c. producing and transmitting the output by said transceiver unit forconfiguration of plurality of configurable solenoids placed on both sides ofrunway; andd. receiving the output from said transceiver unit and adjusting the plurality ofconfigurable solenoids placed on the both sides of runway for landing and / ortakeoff procedure depending upon the produced output by receiving unit inrunway.Detailed description:For the purpose of promoting an understanding of the principles of the invention, reference will now be made to the embodiment illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated system, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates. It will be understood by those skilled in the art that the foregoing general description and thefollowing detailed description are exemplary and explanatory of the invention and are notintended to be restrictive thereof. Throughout the patent specification, a convention employedis that in the appended drawings, like numerals denote like components.The present Invention relates to the field of runway management system. Particularly, theInvention provides a system for reducing the length of runway for aerial vehicle takeoff andlanding and method thereof.Therefore the present invention provides a system for reducing the length of runway requiredfor landing and / or takeoff procedure of an aerial vehicle and its method of operation thereof.The Invention provides a system and method for reducing length of runway for aerial vehicletakeoff and landing.In an embodiment, the system and method comprises large magnetic structures on both sidesof entire runway and aerial vehicle to generate a huge magnetic field.In an embodiment, the invention has been described considering solenoids as the preferredmagnetic structures. However, the scope of the invention is not limited to the use of solenoidrather the invention can be implemented by using the other magnetic structures.In one preferred embodiment of the present invention, there is provided a system for reducingthe length of runway required for landing and / or takeoff procedure of an aerial vehicle.In an embodiment of the present invention, a system for reducing the length of runwayrequired for landing and / or takeoff procedure of an aerial vehicle, comprises followingcomponents:plurality of configurable solenoids having north pole and south pole placed on the underlying belling of the aerial vehicle configured to create an electro-magnetic field;plurality of configurable solenoids having north pole and south pole placed on the both sides of runway configured to create an electro-magnetic field;plurality of artificial intelligence units, comprising:atleast a sending unit in aerial vehicle configured to control the plurality of configurable solenoids on aerial vehicle and send landing and / or takeoff procedure related information; atleast a transceiver unit in Air Traffic Control (ATC) configured to:receive and process the landing and / or takeoff procedure related information from said sending unit; andproduce and transmit the output for configuration of plurality of configurable solenoids on both sides of runway; andatleast a receiving unit in runway configured to receive the output from said transceiver unit and adjust the plurality of configurable solenoids placed on the both sides of runway for landing and / or takeoff procedure depending upon the produced output.In one embodiment of present invention, for takeoff procedure:the south pole of the plurality of configurable solenoids on both sides of runway points towards runway and the north pole points away from runway; andthe north pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the south pole points towards the tail of the aerial vehicle, orthe north pole of the plurality of configurable solenoids on both sides of runway points towards runway and the south pole points away from runway;the south pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the north pole points towards the tail of the aerial vehicle. In an another preferred embodiment of the present invention, for landing procedure:the north pole of the plurality of configurable solenoids on both sides of runway points towards runway and the south pole points away from runway; andthe north pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the south pole points towards the tail of the aerial vehicle, orthe south pole of the plurality of configurable solenoids on both sides of runway points towards runway and the north pole points away from runway; andthe south pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the north pole points towards the tail of the aerial vehicle. In an embodiment, the plurality of configurable solenoids on both sides of runway and theplurality of configurable solenoids of aerial vehicle can change the orientation of their polesfrom north pole to south pole or from south pole to north pole depending upon the landingand takeoff procedure.In an embodiment of the present invention, the aerial vehicle comprises space shuttles, dronesand aircrafts of civil and military domain.In an embodiment of the present invention, the landing and / or takeoff procedure relatedinformation sent by sending unit comprises aerial vehicle size and weight, polarity of theplurality of configurable solenoid on the aerial vehicle, landing speed, air density, dynamicweather condition, runway friction, wind drag, wind speed and wind direction.In an embodiment of the present invention, the diameter of atleast one of the plurality ofconfigurable solenoids on the both sides of runway ranges from 16m to 30m and the spacingbetween the plurality of configurable solenoids ranges from 12m to 26m.In another aspect of the invention, the method of operation of the system for reducing thelength of runway required for landing and / or takeoff procedure of an aerial vehicle isprovided. The method comprising the following steps:a. atleast a sending unit in aerial vehicle sending landing and / or takeoff procedurerelated information to atleast a transceiver unit in Air Traffic Control (ATC);b. receiving and processing the landing and / or takeoff procedure related information bysaid transceiver unit from said sending unit;c. producing and transmitting the output by said transceiver unit for configuration ofplurality of configurable solenoids placed on both sides of runway; andd. receiving the output from said transceiver unit and adjusting the plurality ofconfigurable solenoids placed on the both sides of runway for landing and / or takeoffprocedure depending upon the produced output by receiving unit in runway.In another preferred embodiment of the present invention, the orientation of the plurality of configurable solenoids placed on the underlying belly of the aerial vehicle and plurality of configurable solenoids placed on the both sides of runway creates an interaction force responsible for giving acceleration to the aerial vehicle during takeoff procedure and deceleration to the aerial vehicle during landing procedure.In an embodiment of the present invention, the landing and / or takeoff procedure related information sent by sending unit comprises aerial vehicle size and weight, polarity of the plurality of configurable solenoid on the aerial vehicle, landing speed, air density, dynamicweather condition, runway friction, wind drag, wind speed and wind direction.The method and system of the present Invention comprises novel and Inventive technicalfeatures including use of magnetic structure on the both sides of runway and along the aerialvehicle for generating huge magnetic field for accelerating and decelerating the aerial vehiclewhich leads to higher traffic throughput in terms of take-off and landing. The system andmethod further uses the computer implemented method to control electromagnetic structureson the runway and electromagnetic elements on a commercial aerial vehicle that interact viaelectromagnetic force to provide acceleration and deceleration to the aerial vehicle.In an embodiment, the system for Runway Length Reduction is based on computerimplemented method to control electromagnetic structures on the runway andelectromagnetic elements on a commercial aerial vehicle that interact via electromagneticforce to provide acceleration and deceleration to the aerial vehicle. The system also leads tohigher traffic throughput in terms of take-off and landing.In an embodiment, the system comprises magnetic structures i.e. solenoids arranged along therunway in a dynamic orientation and is powered by current varying over time to providemaximal acceleration during take-off and deceleration during landing as well as to savepower.In an embodiment, the system comprises magnetic structures (such as solenoids) arrangedalong the length and / or breadth of the aerial vehicle in a dynamic orientation and is poweredby current varying over time to provide maximum acceleration during take-off anddeceleration during landing and also to minimize power needed.In an embodiment, the system comprises computer implemented method that involvesmultiple units and agents which collaboratively controls the dynamics in the system duringtake-off and landing.In an embodiment, the system comprises atleast a first agent that controls the system on theaerial vehicle while atleast a second agent that controls the magnetic structures on the runwayand atleast a third agent that sits at ATC overlooking the scheduling of aerial vehicles acrossmultiple runways.In an embodiment, the system works in a manner of collaborative play between multipleagents and units to control the currents and orientation of magnetic structures on the runwayand the aerial vehicle while considering dynamic conditions of weather, aerial vehicle,runway friction, wind drag, speed and direction, and optimizing for stable acceleration andcurrent demand. In an embodiment, system is based on Artificial Intelligence for dynamic adjustment with respect to the varying weather and runway conditions, so that the appropriate acceleration can be provided to the aerial vehicle by changing the current flow through the solenoid. In an embodiment, such control can be done by using Artificial Intelligence algorithms such as Reinforcement Learning (e.g. DQNs: Deep Q Networks). The training for such RL algorithms can be done using large data so that the model is trained for all varying scenarios representing combinations of the above variations mentioned for mass of aerial vehicle, runway friction, weather conditions, failure in any part of the system etc. In another aspect of the Invention, there is provided a process of accelerating or decelerating the aerial vehicle involving computer implemented method which involves sending unit, transceiver unit, receiving unit and other related units as shown in Fig.3 These multiple units collaborate to make sure that the landing and take-off get decelerated and accelerated respectively using interaction between magnetic structures. Each aerial vehicle has an agent that controls the magnetic structures on the aerial vehicle and interacts with the existing system on the aerial vehicle. Each runway has an agent that controls the current and orientation of the magnetic structures to ensure optimal force on the flying vehicle. There is another agent at the Air traffic control (ATC) that schedules the simultaneous landing and take-off of various flying vehicles in a way that optimizes the peak loads during take-off and landing for the complete airport, while also ensuring smooth take-off and landing with reduced runway for each flying vehicle. This whole process of collaborating of multiple agents for ensuring smooth take-off and landing with reduced runway for each flying vehicle is based on Artificial Intelligence.In an another preferred embodiment of the present invention, for the safety of operation the Air traffic control (ATC) includes a deterministic algorithm that makes sure that AI agents don't make any incorrect or unsafe move. Adaptation to Variable Weather Conditions:1. In the case of extremely hot weather, the lift decreases and thus more speed is required to generate the same lift. Thus the solenoids will generate a greater field so that a greater force is exerted on the plane to get a higher speed.2. In the case of heavy rain, the friction will decrease and thus more force will be generated by the solenoids to generate sufficient speed.3. The case of tailwind / crosswind the solenoids will adjust themselves and change the direction of the magnetic fields providing sufficient force in order to balance out the change caused by heavy winds. The Invention is further described with the help of non-limiting examples.Example 1:Force Calculation involved in the landing and takeoff procedure:An aircraft typically requires 3 km of runway, which can be reduced to 1.5 km with the abovemodular components added to the aircraft and the runway (both sides). In this section,representative calculation on the acceleration needed by the aircraft to get to the releasevelocity within 1.5 km of the runway to take-off in a smooth way is demonstrated.The above solenoid arrangement on both sides of the runway is used only for 750m in theinitial part of the runway. On the final part of the runway, the magnetic structures on therunway are not placed, so that any last minute changes in decisions can be done easily.For the dynamics calculations, it is assumed that the aircraft to be of mass = 300 * 10A3 Kg(Airbus A340-600) and the release velocity of around 300 Km / hr (~ 84m / s)Assuming constant acceleration of the aircraft with 3 km runway (starting from rest), it is9 9given by: v = u + 2asThus, acceleration, a = (84)*(84) / (2*3000) m / s2 = 1.2 m / s2When magnetic structures based proposed design is used, the velocity 'u', immediately afterthe solenoid zone is given by:v2 = u2 + 2as u2 = v2 - 2as = (84 * 84) - 2* 1.2*750 = 5256 (m / s)2 Now, the acceleration needed to achieve this velocity, 'u', after starting from rest and accelerating through the solenoid zone, 'ace', for a distance, 's' = 750m, is given by:u2 = 0 + 2*acc*sace = u2 / 2s = 5256 / (2 * 750) = 3.5 m / s2 Hence, the additional acceleration, am, provided by the solenoid zone should be:a_m = 3.5- 1.2 = 2.3 m / s2 So, the magnetic force on the plane, owing to the solenoid interactions, should be,F = m*a_m = 300*1000 * 2.3 N = 690* 103 N Example 2:Magnetic Force Computation required during takeoff and landing procedure Now, that the magnetic force required to give additional acceleration to the plane is known, further the size of the magnetic structures required can be computed. Assuming the runway width of around 80m, and aircraft length of around 75m. Magnetic flux density for a solenoid, B = uo * n * I Force on the plane solenoid, is approximated by force between 2 magnets, F = B *A / (2*uo)Force between a solenoid on the ground and that on the plane = (u_0 * n * 1) * A / (2 * uo)Force = u0 * n2 * I2 * A / 2 NAssuming that current is around 60A, number of turns per unit length = 1000, and A = 500m2 (A = IT * r2, where r = -12 m)Uo = 1.26 * le-6, so, force F = 1.26 * le-6 * le6 * 36 * le2 * 500 / 2 = 1.26 * 9 * le5 N =11.34* le5NThus, with such a sizing of the solenoid and current, the magnetic force on the plane solenoidwill be adequate enough to provide the needed additional acceleration.Example 3:Aircraft takeoff procedure and arrangement of magnetic structuresFig. 1 illustrates magnetic structures being oriented perpendicular to the runway, and the current flows through them in such a way that their South poles are pointing towards runway, while their North pole points away from the runway. The magnetic structures are lined up along the runway, through which the plane runs in the initial part during take-off. It further illustrates that the plane also has magnetic structures of smaller size connected to its underlying belly. These magnetic structures are oriented along the length of the plane. The current in these magnetic structures flows such that their North Pole points at the nose of the plane and their South pole points towards the tail of the plane as shown in Fig. 1. As the plane runs past these magnetic structures on the runway, the North pole of the magnetic structure on the plane get attracted in the forward direction by the magnetic structure on the sides of the runway, that are ahead of the current position of the plane. Further, the South pole of the plane's magnetic structure gets repelled forward by the South pole of the magnetic structure on the ground, which are behind the current position of the plane. The red marked magnetic structures are turned off to save electricity cost. Figure 4 discloses a method and system for takeoff procedure in accordance to an embodiment of the Invention. As an example, A340 when fully loaded rotates at about 150kts at about 300kmph. So, the plane achieves 260kmph in the first 750m under magnetic structure acceleration as per the claimed invention. The remaining 40kmph is achieved in the next 750m under its own acceleration and blasts off. Example 4:Aircraft landing procedure and arrangement of magnetic structure:Fig. 2 illustrates magnetic structures being oriented perpendicular to the runway, and the current flows through them in such a way that their South poles are pointing away from the runway, while their North poles points towards the runway. The magnetic structures are lined up along the runway. It further illustrates that the plane also has magnetic structures of smaller size connected to its underlying belly. These magnetic structures are oriented along the length of the plane. The current in these magnetic structures flows such that their North pole points at the nose of the plane and their South pole points towards the tail of the plane as shown in Fig. 2. Thus, as the plane runs past these magnetic structures on the runway, the North pole of the magnetic structure on the plane get repelled by the north pole of the magnetic structure on the sides of the runway, that are ahead of the current position of the plane. Further, the South pole of the plane's magnetic structure gets attracted by the North pole of the magnetic structure on the ground, which are behind the current position of the plane. The red marked magnetic structures are turned off to save electricity cost. The present invention as described above, it is to be understood that this invention is not limited to particular methodologies and materials described, as these may vary as per the person skilled in the art. It is also to be understood that the terminology used in the description is for the purpose of describing the particular embodiments only, and is not intended to limit the scope of the present invention.In another embodiment, figure 5 discloses the method and system for landing procedure. In an embodiment of the present invention, on achieving a much lower velocity say 70kts, the aircraft turns very slightly off the runway and on to the taxiway which is specifically designed to ensure that the aircraft comes to a complete stop. The system further includes the rapid exit taxiway to be made longer and wider and also its angle from the runway is very less and slowly curves away from the runway. In this case the aircraft decelerates to about 60-70kts., after which it veers onto the rapid exit taxiway. The aircraft further decelerates in here and slows down to a minimal speed. The taxiways will be made on both sides of the runway. Depending upon which gate / stand the aircraft has to taxi, the aircraft can turn onto either of the taxiway. Further this taxiway will be made of a material which has a higher frictional coefficient than the runway, e.g. A340-600 lands at about 140kts. On planting it's mains it decelerates under magnetic structure force and at 70kts turns on the taxiway which is not a steep turn and finally stops on the specifically designed rapid exit taxiway after 600-700m.

Claims

We Claim:1) A system for reducing the length of runway required for landing and / or takeoffprocedure of an aerial vehicle:plurality of configurable solenoids having north pole and south pole placed on the underlying belling of the aerial vehicle configured to create an electro-magnetic field;plurality of configurable solenoids having north pole and south pole placed on the both sides of runway configured to create an electro-magnetic field; andplurality of artificial intelligence units, comprising:atleast a sending unit in aerial vehicle configured to control the plurality of configurable solenoids on aerial vehicle and send landing and / or takeoff procedure related information;atleast a transceiver unit in Air Traffic Control (ATC) configured to:receive and process the landing and / or takeoff procedure related information from said sending unit; andproduce and transmit the output for configuration of plurality of configurable solenoids on both sides of runway; andatleast a receiving unit in runway configured to receive the output from said transceiver unit and adjust the plurality of configurable solenoids placed on the both sides of runway for landing and / or takeoff procedure depending upon the produced output.2) A system for reducing the length of runway required for landing and / or takeoffprocedure of an aerial vehicle, as claimed in claim 1, wherein for takeoff procedure:the south pole of the plurality of configurable solenoids on both sides of runway points towards runway and the north pole points away from runway; and the north pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the south pole points towards the tail of the aerial vehicle, or the north pole of the plurality of configurable solenoids on both sides of runway points towards runway and the south pole points away from runway;the south pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the north pole points towards the tail of the aerial vehicle.3) A system for reducing the length of runway required for landing and / or takeoffprocedure of an aerial vehicle, as claimed in claim 1, wherein for landing procedure:the north pole of the plurality of configurable solenoids on both sides of runway points towards runway and the south pole points away from runway; and the north pole of the plurality of configurable solenoids on aerial vehicle points towards nose of the aerial vehicle and the south pole points towards the tail of the aerial vehicle, or the south pole of the plurality of configurable solenoids on both sides of runway points towards runway and the north pole points away from runway; and4) A system for reducing the length of runway required for landing and / or takeoffprocedure of an aerial vehicle, as claimed in claim 1, wherein the plurality ofconfigurable solenoids on both sides of runway and the plurality of configurablesolenoids of aerial vehicle can change the orientation of their poles from north pole tosouth pole or from south pole to north pole depending upon the landing and takeoffprocedure.5) A system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, as claimed in claim 1, wherein the aerial vehicle comprises space shuttles, drones and aircrafts of civil and military domain.6) A system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, as claimed in claim 1, wherein the landing and / or takeoff procedure related information sent by sending unit comprises aerial vehicle size and weight, polarity of the plurality of configurable solenoid on the aerial vehicle, landing speed, air density, dynamic weather condition, runway friction, wind drag, wind speed and wind direction.7) A system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, as claimed in claim 1, wherein the diameter of atleast one of the plurality of configurable solenoids on the both sides of runway ranges from 16m to 30m and the spacing between the plurality of configurable solenoids ranges from 12m to 26m.8) A method of operation of the system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, as claimed in claim 1, comprising:a. atleast a sending unit in aerial vehicle sending landing and / or takeoffprocedure related information to atleast a transceiver unit in Air TrafficControl (ATC);b. receiving and processing the landing and / or takeoff procedure relatedinformation by said transceiver unit from said sending unit;c. producing and transmitting the output by said transceiver unit forconfiguration of plurality of configurable solenoids placed on both sides ofd. receiving the output from said transceiver unit and adjusting the plurality oftakeoff procedure depending upon the produced output by receiving unit inrunway.9) A method of operation of the system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, as claimed in claim 8, wherein the orientation of the plurality of configurable solenoids placed on the underlying belly of the aerial vehicle and plurality of configurable solenoids placed on the both sides of runway creates an interaction force responsible for giving acceleration to the aerial vehicle during takeoff procedure and deceleration to the aerial vehicle during landing procedure.10) A method of operation of the system for reducing the length of runway required for landing and / or takeoff procedure of an aerial vehicle, as claimed in claim 8, wherein the landing and / or takeoff procedure related information sent by sending unit comprises aerial vehicle size and weight, polarity of the plurality of configurable solenoid on the aerial vehicle, landing speed, air density, dynamic weather condition, runway friction, wind drag, wind speed and wind direction.