A charging tower for aircraft and method of operation thereof

Abstract

The invention relates to a charging tower for aircraft comprising at least one charging unit (18) mechanically connected to a supporting mast (12) and provided at a free end with a charging docking unit (28) for charging, with a charging rod (20) articulated from a connecting part (16) rotationally pivotable in a first direction (A) or a second direction (B) in a horizontal axis (x) through a circumferential guide line (36) opening on a lateral wall (14) of the charging unit (18) of the mast (12), and electrically connected to the charging clamping unit (28), and the method of operation thereof.

Description

[0001] A CHARGING TOWER FOR AIRCRAFT AND METHOD OF OPERATION THEREOF

[0002] Technical Field

[0003] This invention relates to a charging tower for aircraft and a method of its operation, comprising at least one charging unit having a charging docking unit.

[0004] Prior Art

[0005] In the literature, the features and usage areas of aircraft are increasing day by day. In particular, the concept of More Electric Aircraft (MEA) is becoming an increasingly important element. Aircraft designs that will fly using electrical energy from air taxis to unmanned aerial vehicles (UAVs) are increasing. In addition, in the literature, it is thought that the use of unmanned aerial vehicles (UAVs) and similar vehicles in the logistics sector will be increased. For this reason, aircrafts should be used efficiently. The use of electric vehicles has many advantages, but there are also some limitations due to the level of battery technology in the literature. For this reason, just like in automobiles, charging of aircrafts at certain time intervals is one of the most important problems. Again, in the literature, the first element for charging the aircraft is the charging of the aircraft by coming to the charging station. The charging station can be located in the city or outside the city. Especially for aircraft with vertical take-off and landing (Vertical Take-Off and Landing -VTOL) capability, it is generally necessary to come to such charging stations and dock the charger. After this docking process, the charging process can start safely. Here, the situation where the charging process starts without mutual approval from both the charging station and the aircraft may cause problems in terms of safety. For an aircraft that does not have vertical take-off and landing (VTOL) capability, a runway is first needed for it to come to a charging station in this way. Thanks to this runway, an aircraft that can take off and land can then go to the area where the relevant charger is located and achieve docking. In such a scenario, while the aircraft is in operation in the air, it gives up its altitude, i.e. its potential and kinetic energy, and lands on the ground for an urgent energy requirement. After recharging, it loses some of the energy it gained while charging in order to reach the same altitude again. This situation appears as a negative factor in energy efficiency. As an alternative to this situation, energy loss can be prevented by charging the aircraft while maintaining its altitude. In particular, it is known that a charging tower is provided for charging the aircraft while maintaining altitude, and that the charging process starts after the aircraft is docked to this charging tower. Accordingly, the invention US9387928 relates to multi-use unmanned aerial vehicle (UAV) docking station systems and methods. The invention provides a charging tower design for an unmanned aerial vehicle (UAV) capable of vertical take-off and landing (VTOL). In this invention, the unmanned aerial vehicle (UAV) arrives at the charging tower, docks and charges. After docking, the unmanned aerial vehicle (UAV) remains completely stationary. Here, it preserves some of its potential energy depending on its altitude in the charging tower. However, the vehicle loses its kinetic energy as the unmanned aerial vehicle arrives and stops at the station. In addition, the invention is not usable for fixed wing unmanned aerial vehicles capable of horizontal take-off and landing.

[0006] As a result, all the above-mentioned problems have made it necessary to make an innovation in the relevant technical field.

[0007] Objects of the Invention

[0008] The present invention relates to a charging tower for aircraft and a method of its operation, in order to overcome the above-mentioned disadvantages and to bring new advantages to the relevant technical field.

[0009] An object of the invention is related to a charging tower for aircraft, wherein charging of the aircraft at a given altitude in the air is enabled by a charging unit which can rotate 360 degrees bidirectionally around a horizontal axis.

[0010] Another object of the invention relates to a charging tower in which the potential and kinetic energies of aircraft with vertical take-off and landing or horizontal take-off and landing characteristics can be preserved during docking and charging to an air charger.

[0011] Another object of the invention relates to the method of operation of the charging tower in which the charging process is carried out by ensuring the conservation of kinetic and potential energy in cases where the aircraft can be charged in a moving or stationary manner.

[0012] Brief Description of the Invention

[0013] In order to fulfil all the aforementioned objects and those which will arise from the following detailed description, the present invention is a charging tower for aircraft comprising at least one charging unit mechanically connected to a supporting mast and having at a free end a charging docking unit for charging. Accordingly, the novelty is that the charging unit comprises a charging rod articulated from a rotationally pivotable connecting part in a first direction or a second direction in a horizontal axis into a circumferential guide line opened on a lateral wall of the mast and electrically connected to the charging docking unit. Thus, regardless of the type of aircraft, for example, a horizontal-vertical take-off aircraft or a fixed-wing horizontal flight aircraft, the vehicle is rotated 360 degrees to maintain its kinetic and potential energy at a predetermined altitude.

[0014] A possible embodiment of the invention is characterised in that the charging rod comprises a first rod part connected to the connecting part, a second rod part connected to the first rod part and a third rod part connected to the second rod part. Thus, the length of the rotatable charging rod can be varied, and the first rod part of the rotatable charging rod provides the ability of the charging tower to move up and down at a certain angle in the vertical axis of the ground.

[0015] A possible embodiment of the invention is characterised in that it comprises a suspension assembly in which the docking unit is mounted on the charging rod, and a docking ring mounted at an opposite end of the suspension assembly. In this way, small variations in both planes (up and down and towards and away from the centre) during docking with the suspension assembly are tolerated by the charging tower having a circular rotation in air for aircraft.

[0016] A possible embodiment of the invention is characterised in that the docking ring comprises an in-ring assembly provided with a structure having a diaphragm. Thus, for example in fixed wing aircraft where docking for charging is difficult, the in-ring assembly catches the vehicle charging cable when the aircraft throws the charging cable so that it passes through the docking ring.

[0017] A possible embodiment of the invention is characterised in that the docking ring provided in each charging unit in the charging tower comprises at least one of a circular form, a rectangular form, a triangular form and a pentagonal form. Thus, charging is carried out in accordance with different types of charging terminals of aircraft.

[0018] A possible embodiment of the invention is characterised in that, in a first case, it comprises the process steps of docking an aircraft to the charging tower at a predetermined altitude in the air; rotating the charging rod in the charging unit with the kinetic energy of the aircraft when docking for charging is achieved; charging the aircraft during the rotation of the charging rod; separation of the aircraft from the docking ring after the completion of the charging of the aircraft; and the aircraft continuing its journey in the air. Thus, the potential energy of the aircraft, which is moving in the air, is preserved by being at a certain altitude and the kinetic energy is preserved by being mobile.

[0019] A possible embodiment of the invention is characterised in that, in a second case, it comprises the steps of docking an aircraft to a charging tower at a predetermined altitude; switching the operation of the aircraft to an off mode by docking to the charging tower and rotating the vehicle by the charging rod in the charging unit; charging the aircraft during the rotation of the vehicle; switching the aircraft to an on mode in which the aircraft starts to operate upon completion of the charge replenishment; subsequently disengaging the vehicle from the docking ring and continuing the airborne path of the aircraft. Thus, the potential energy of the aircraft, which is moving in the air, is preserved by being at a certain altitude when the aircraft is switched off. In addition, the kinetic energy provided by the rotating charging rod of the charging unit constitutes the kinetic energy of the vehicle when it works.

[0020] A possible embodiment of the invention is characterised in that, in a third case, it comprises the process steps of docking an aircraft to a charging tower at a predetermined altitude; while rotating with the kinetic energy of the aircraft by docking to the charging tower, the charging rod assists the rotation by expending energy according to a feedback received from the aircraft; the aircraft is charged during the rotation of the vehicle; the vehicle is separated from the docking ring upon completion of the charging of the aircraft; and the aircraft continues its path in the air. Thus, the potential energy of the aircraft moving in the air is preserved at a certain altitude. In addition, the kinetic energy provided by the rotating charging rod of the charging unit provides an energy support to the kinetic energy of the vehicle.

[0021] Brief Description of the Figures

[0022] Figure 1 shows a side view of the charging tower, having a configuration provided with a charging unit regarding the charging tower for aircraft and its method of operation according to the invention. Figure 2 shows a side view of the charging tower, having a configuration provided with a plurality of charging units regarding the charging tower for aircraft and its method of operation according to the invention.

[0023] Figure 3 shows a top view of the charging tower rotating in a first direction, having a configuration provided with a charging unit regarding the charging tower for aircraft and its method of operation according to the invention.

[0024] Figure 4 shows a top view of the charging tower rotating in a second direction, having a configuration provided with a charging unit regarding the charging tower for aircraft and its method of operation according to the invention.

[0025] Figure 5 shows a side view of an in-ring assembly in a docking ring regarding the charging tower for aircraft and its method of operation according to the invention.

[0026] Figure 6 shows a representation of the types of configurations of the docking ring regarding the charging tower for aircraft and its method of operation according to the invention.

[0027] Figure 7 shows a flow chart of the charging tower operation method in a first case regarding the charging tower for aircraft and its method of operation according to the invention.

[0028] Figure 8 shows a flow chart of the charging tower operation method in a second case regarding the charging tower for aircraft and its method of operation according to the invention.

[0029] Figure 9 shows a flow chart of the charging tower operation method in a third case regarding the charging tower for aircraft and its method of operation according to the invention.

[0030] Detailed Description of the Invention

[0031] Figure 1 shows a charging tower for aircraft according to the invention in the configuration comprising a charging tower and a charging unit for the method of operation from the side, Figure 2 shows a charging tower for aircraft according to the invention in the configuration comprising a charging tower and a plurality of charging units for the method of operation from the side, and Figure 3 shows a charging tower for aircraft according to the invention in the configuration comprising a charging tower and a charging unit for the method of operation, the charging tower rotating in a first direction from above, Figure 4 shows a charging tower for aircraft of the invention and a charging unit for the method of operation, wherein the charging tower is rotated in a second direction from the top, Figure 5 shows a charging tower for aircraft according to the invention and an in-ring assembly in a clamping ring for the method of operation from the side, and Figure 6 shows the types of configurations of a charging tower for aircraft according to the invention and a clamping ring for the method of operation. The charging tower (10) is provided with a supporting mast (12), which enables the aircraft to be at a predetermined altitude height in the air. At least one charging unit (18) is mechanically connected to the supporting mast (12). At a free end of each charging unit (18), a charging docking unit (28) is provided to charge the aircraft. A circumferential guide line (36) is opened on a lateral wall (14) of the mast (12) of the charging unit (18). The guide line (36) includes a charging rod (20) articulated in the horizontal axis (x) in a first direction (A) or in a second direction (B) through a rotationally pivotable connection part (16) and electrically connected to the charging docking unit (28). Figure 1 and Figure 2 show the dual directions (A) (B) parallel to the horizontal axis (x). In Figure 3, the first direction of movement (A) in the top view of the charging tower (10) is counterclockwise in the vertical representation. In Figure 4, in the top view of the charging tower (10), the second direction of movement (B) is clockwise in the vertical representation. By means of the charging tower according to the invention, regardless of the type of aircraft, e.g. a horizontal-vertical take-off aircraft or a fixed-wing horizontal flight aircraft, the aircraft can be charged by rotating the vehicle 360 degrees so as to maintain its kinetic and potential energy at a predetermined altitude. Here, the charging tower (10) provides a charging altitude for the aircraft at a predetermined altitude. The mast (12) is the connection that provides this altitude height. In the charging clamping unit (28), the charging rod (20) is articulated to the mast (12) with the connection part (16), so that it can rotate parallel to the ground on the horizontal axis (x), with the mast (12) in the centre. Here, with the rotation of the charging rod (20), the potential and kinetic energy of the aircraft is conserved regardless of its type. In other words, by preserving the altitude, potential energy and kinetic energy of the aircraft, the altitude and energy losses to be lost by placing the aircraft on a charging station for charging, for example, are prevented, and the energy loss in charging, which will be required to reach the same altitude again after charging, is also eliminated. In the invention, in order to conserve the potential energy of the aircraft, the aircraft is docked with the aircraft at the appropriate altitude. Since the continuity of the movement of the aircraft is required for the conservation of the kinetic energy, the aircraft flying around the charging tower (10) moves completely away from the charging tower (10) after a while, and therefore a movement cycle is provided between the aircraft and the charging tower (10), which will always maintain the same distance. In the invention, the charging rod (20) has a first rod part (22) connected to the connection part (16), a second rod part (24) connected to the first rod part (22) and a third rod part (26) connected to the second rod part (24). In this way, the length of the rotatable charging rod (20) can be varied and the first rod part (22) of the rotatable charging rod (22) is capable of moving at a certain angle up and down the vertical axis of the charging tower (10) to the ground. In one embodiment of the invention, the rod parts (22) (24) (26) are cylindrical. For example, the first rod part (22) is a first cylinder; the second rod part (24) is a second cylinder; the third rod part (26) is a third cylinder. In addition, the connection between the docking unit and the connecting part is provided by means of multi-part cylinders (22) (24) (26). Here, the first cylinder (22) is the cylinder part with the largest diameter, which is connected to the connecting part (16) of the charging rod (20), i.e. to the mast (12) of the charging tower (10), which provides the tower feature. The second cylinder (24) provides the connection between the first cylinder (22) and the third cylinder (24). Moreover, the second cylinder (24) is smaller in diameter than the first cylinder (22) and larger in diameter than the third cylinder (26). In other words, the first cylinder (22) is the cylinder with the largest diameter, the second cylinder (24) is the cylinder of medium diameter and the third cylinder (26) is the cylinder with the smallest diameter. In the invention, the electric cable (32) passes through the largest diameter cylinder (22) of the rotary charging rod (20) through the rotary charging rod (20). In addition, the largest diameter cylinder (22) of the rotary charging rod (20) has a structure that can contain the medium diameter cylinders (24) of more than one number of rotary charging rods (20). The electric cable (32) passing through the rotary charging rod (20) carries the energy from the charging tower (10) to the docking unit (28) of the rotary charging rod (20). In addition, the medium diameter cylinder (24) of the rotary charging rod (20) may be more than one in a rotary charging rod (20) in the charging unit (18) and plays a role in adjusting the length of the rotary charging rod (20). The medium diameter cylinders (24) of the rotary charging rod (20) are arranged so that they fit inside each other. The smallest diameter cylinder (26) of the rotary charging rod is connected to the medium diameter cylinder (24) of the rotary charging rod which is furthest from the charging tower (10). Here, when necessary during operation, the smallest diameter cylinder (26) of the rotary charging rod can also be inserted into the centre diameter cylinder (24) and play a role in adjusting the length of the rotary charging rod (20). In addition, the largest diameter cylinder (22) of the rotary charging rod, the medium diameter cylinder (24) of the rotary charging rod and the smallest diameter cylinder (26) of the rotary charging rod are parts that can be nested in the cylinder structure. However, it is not necessary for all three to be exclusively cylindrical. In other words, the cylinders with the rod part (22) (24) (26) can also have structures such as square prism, rectangular prism, triangular prism and polygonal prism that can be nested into each other. In the invention, the docking unit (28) comprises a suspension assembly (30) to which the charging rod (20) is mounted and a docking ring (34) mounted at an opposite end of the suspension assembly. In this way, it is ensured that small variations in both planes (up-down and towards and away from the centre) during docking with the suspension assembly are tolerated by the charging tower (10) having a circular rotation in air for aircraft. Furthermore, the docking ring (34) is connected to the smallest diameter cylinder (26) and is connected to the suspension assembly (30) connecting the smallest diameter cylinder (26) and the docking ring (34). Here, the docking ring (34) is the part of the aircraft which engages the rotary charging rod (20). In one embodiment of the invention, the docking ring (34) comprises an in-ring assembly (38) provided in a diaphragm structure and shown in Figure 5. In this way, for example in fixed wing aircraft where docking for charging is difficult, the in-ring assembly (38) catches the vehicle charging cable when the aircraft throws the charging cable so that it passes through the docking ring (34). Furthermore, after the charging cable of the aircraft passes through the docking ring (8) of the rotary charging rod, the in-ring assembly (38) having an in-ring system having a diaphragm feature holds the charging cable of the aircraft, thereby preventing the charging cable from separating from the docking ring (28) of the rotary charging rod as a result of the movement of the aircraft. In one configuration of the invention, the clamping ring (34) provided in each charging unit (18) in the charging tower (10) has at least one of circular form (340), rectangular form (342), triangular form (344) and pentagonal form (346) as shown in Figure 6. In this way, charging is carried out in accordance with different types of charging terminals of the aircraft. Here, by having a plurality of charging units (18) in the charging tower (10), different types of aircraft can be charged. In the invention, the general principle for the docking ring (34) is to have a hole in it and to provide a structure for docking. The required energy can also be transferred to the charging cable of the aircraft passing through the docking ring (34) by one of the wireless power transfer (WPT) methods.

[0032] Figure 7 shows a charging tower for the aircraft of the invention and a flowchart of the charging tower operation method in a first case. The flow sequence of the first case operation method of the charging tower shown in Figure 7 is given below; • Firstly, in a first case (40), an aircraft is docked to a charging tower (42) at a predetermined altitude in the air.

[0033] • Then, when charging docking (42) is achieved, the kinetic energy of the air vehicle rotates (44) the charging rod in the charging unit.

[0034] • The aircraft is then charged (46) while the charging rod is rotated (44).

[0035] • Then, the aircraft is separated from the docking ring (50) when the charge replenishment of the aircraft is completed (48).

[0036] • Subsequently, the aircraft continues (52) its path in the air.

[0037] In this way, the potential energy of the aircraft at a certain altitude and the kinetic energy of the aircraft moving in the air are preserved and charging is carried out. In this type of use, in order for the rotary charging rod (20) to rotate in a way to cause less energy loss, the connection part (16) of the rotary charging rod (20) to the charging tower (10) and the connection of the charging tower (10) are designed to create as little friction effect as possible. In addition, due to wind and other factors, the vectorial distance between the charging tower (10) and the aircraft may change over time. The aircraft can be close or far from the charging tower (10) in two planes (up-down and towards and away from the centre). In order to dynamically control this first situation (40), the following features are required for the parts in the charging tower (10) with circular rotation in the air; a) The first cylinder of the rotary charging rod (22), which is the first rod part (22) with the largest diameter, must be able to move up and down at a certain angle to the vertical axis of the charging tower (10). In this way, the up and down movement difference of the aircraft can be tolerated. b) The suspension assembly (30) connecting the third cylinder of the rotary charging rod (26), which is the third rod part of the rotary charging rod with the smallest diameter, and the docking ring (34) ensures that small differences in both planes (up-down and towards the centre and away from the centre) are tolerated by the charging tower (10) having a circular rotation in the air for aircraft. c) The second cylinder (24) of the rotary charging rod, which is the second rod part of the rotary charging rod with a medium diameter, can be more than one in the first case (40) and is arranged in such a way that they can be intertwined with each other and move in the horizontal axis (x) relative to the charging tower (10). This allows the variation of the distance of the aircraft from the centre to be tolerated by the charging tower (10), which has a circular rotation in the air for aircraft.

[0038] Figure 8 shows a charging tower for the aircraft of the invention and a flowchart of the charging tower operation method in a second case. The flow sequence of the second case operation method of the charging tower shown in Figure 8 is given below;

[0039] • Firstly, in a second case (54), an aircraft is docked to a charging tower (42) at a predetermined altitude.

[0040] • Then, by docking with the charging tower, the operation of the aircraft switches to an off mode (56) and the vehicle is rotated (58) by the charging rod in the charging unit.

[0041] • Then, during the rotation (58) of the vehicle, the aircraft is charged (46).

[0042] • Then, upon completion of the charge replenishment (48), the aircraft switches to an on mode (60) in which it starts to operate.

[0043] • Subsequently, the aircraft disengages from the docking ring (50) and the aircraft continues (52) on its path in the air.

[0044] In this way, the potential energy of the aircraft, which is moving in the air, is preserved by being at a certain altitude when it switches off the operation. In addition, the kinetic energy provided by the rotary charging rod of the charging unit constitutes the kinetic energy when the vehicle is in operation. In this type of use, the rotary charging rod (20) must be rotated by expending energy on the charging tower (10). In addition, since the weight of the aircraft will impose an additional load on the charging tower (10) having a circular rotation in the air for aircraft, the charging tower (10) having a circular rotation in the air for aircraft must be designed to withstand the required static and dynamic load. This use case is a use case that can be used mostly for light weight aircraft. In case of the docking of heavy aircraft, due to the length of the rotary charging rod (20), the rotation moment in the charging tower (10) in the vertical direction due to the length of the rotary charging rod (20) creates a difficult usage situation. However, in order to reduce the effect of such a situation, the moment to be applied to the mast (12) can be negated by a secondary charging rod (20), which is always located in the opposite direction of the charging rod (20). For this purpose, the end of the secondary charging rod (20) will not have the clamping unit (28) required for charging, but will instead have a weight to stabilise the moment. Since the length of the charging rod (20) can be varied with this weight attached, the system will be moment balanced. However, in such a case, more static load will be placed on the mast (12) than normal.

[0045] Figure 9 shows a charging tower for the aircraft of the invention and a flowchart of the charging tower operation method in a third case. The flow sequence of the third case operation method of the charging tower shown in Figure 9 is given below;

[0046] • Firstly, in a third case (62), an aircraft is docked (42) to a charging tower at a predetermined altitude.

[0047] • Then, when the aircraft rotates with the kinetic energy of the aircraft by docking to the charging tower, the charging rod provides rotation assistance (64) to the rotation action by expending energy according to a feedback received from the aircraft.

[0048] • The aircraft is then charged (46) when the vehicle is rotated (58).

[0049] • Then, the aircraft is disengaged from the clamping ring (50) upon completion of the charge replenishment (48) of the aircraft.

[0050] • Subsequently, the aircraft continues (52) its path in the air.

[0051] In this way, the potential energy of the air vehicle, which is moving in the air, is maintained at a certain altitude. In addition, the kinetic energy provided by the rotary charging rod (20) of the charging unit provides an energy support to the kinetic energy of the vehicle. In this type of use case, the rotating charging rod (20) is rotated by the charging tower (10), which has a circular rotation in the air for aircraft, according to the feedback from the aircraft. This use case is a solution for the first case (40) and the second case (54) in which the load to be applied to the charging tower (10) by the aircraft is reduced. It is a solution that can be used especially in cases of docking of heavy aircraft. In addition, due to wind and other factors, the vectorial distance between the charging tower (10) and the aircraft may change over time. The aircraft can be close or far from the charging tower (10) in two planes (up-down and towards and away from the centre). In order to dynamically control this third case (62), the following features are required for the parts in the charging tower (10) with circular rotation in the air: a) The largest diameter cylinder (22) of the rotary charging rod must be able to move up and down at a certain angle to the vertical axis of the charging tower (10). In this way, the up and down movement variation of the aircraft is tolerable. b) The suspension device (30) connecting the smallest diameter cylinder (26) of the rotary charging rod and the docking ring (30) ensures that small differences in both planes (up- down and towards and away from the centre) are tolerated by the charging tower (10) having circular rotation in air for aircraft. c) The centre diameter cylinder (24) of the rotary charging rod is multiple in such a scenario, and is arranged in such a way that it can be inserted into each other and move on a horizontal axis relative to the charging tower (10). In this way, it is ensured that the variation of the distance of the aircraft from the centre is tolerated by the charging tower (10) having a circular rotation in the air for aircraft.

[0052] Reference Numbers Given in the Figures

[0053] 10 Charging tower 38 In-ring assembly

[0054] 12 Mast 40 First case

[0055] 14 Lateral wall 42 Clamping to the charging tower

[0056] 16 Connection part 44 Charging rod rotation

[0057] 18 Charging unit 46 Charging the vehicle

[0058] 20 Charging rod 48 Completion of charge replenishment

[0059] 22 First rod piece 50 Separation of the vehicle from the docking ring

[0060] 24 Second rod piece

[0061] 52 Vehicle continuing on its path

[0062] 26 Third cylinder

[0063] 54 Second case

[0064] 28 Docking unit

[0065] 56 Switching to off mode

[0066] 30 Suspension assembly

[0067] 58 Rotation of the vehicle

[0068] 32 Electric cable

[0069] 60 Switching to on mode

[0070] 34 Docking ring

[0071] 62 Third case

[0072] 340 Circular form

[0073] 64 Rotation assistance

[0074] 342 Rectangular form

[0075] A First direction

[0076] 344 Triangular form 346 Pentagonal form B second direction

[0077] 36 Guide line x Horizontal axis

Claims

CLAIMS1. A charging tower for aircraft comprising at least one charging unit (18) mechanically connected to a supporting mast (12) and having at a free end at least one charging docking unit (28) for charging characterized by comprising;- a charging rod (20) articulated from a connecting part (16) rotationally pivotable in a first direction (A) or in a second direction (B) in a horizontal axis (x) through a circumferential guide line (36) opened on a lateral wall (14) of the mast (12) of the charging unit (18) and electrically connected to the charging docking unit (28),- comprising a first rod piece (22) connected to the connecting part (16) of the a charging rod (20), a second rod piece (24) connected to the first rod piece (22) and a third rod piece (26) connected to the second rod piece (24), configured to be intermeshed with each other.

2. A charging tower for aircraft according to claim 1, characterised by comprising a suspension assembly (30) in which a docking unit (28) is mounted to the charging rod (20) and a docking ring (34) mounted at an opposite end of the suspension assembly (30).

3. A charging tower for aircraft according to claim 2, characterised by comprising an inring assembly (38) provided in the docking ring (34) having a diaphragm structure.

4. A charging tower for aircraft according to any of the preceding claims, characterised by comprising at least one form of the docking ring (34) provided in each charging unit (18) in the charging tower (10) among a circular form (340), a rectangular form (342), a triangular form (344) and a pentagonal form (346).

5. A method of operation of a charging tower for aircraft according to any of the preceding claims, characterised by comprising the process steps in a first case (40), docking (42) of an aircraft to a charging tower at a predetermined altitude in the air; rotation (44) of the charging rod in the charging unit with the kinetic energy of the aircraft when chargingdocking (42) is achieved; charging (46) of the aircraft during the rotation (44) of the charging rod; separation (50) of the vehicle from the docking ring when the aircraft completes charge replenishment (48) and the aircraft continues its path in the air (52).

6. A method of operation of a charging tower for aircraft according to any of the preceding claims, characterised by comprising the process steps in a second case (54) docking (42) of an aircraft to the charging tower at a predetermined altitude; upon docking to the charging tower, the operation of the aircraft switches to an off mode (56) and the vehicle is rotated (58) by the charging bar in the charging unit; charging (46) of the aircraft during the rotation (58) of the vehicle; completing charge replenishment (48), the aircraft switches to an on mode (60), in which the aircraft starts to operate; subsequently, the vehicle is detached from the docking ring (50) and the aircraft continues its path in the air (52).

7. A method of operation of a charging tower for aircraft according to any of the preceding claims, characterised by comprising the process steps in a third case (62), an aircraft at a predetermined altitude is docked (42) to a charging tower; when rotating with the kinetic energy possessed by the aircraft upon docking to the charging tower, the charging rod assists the rotation by expending energy according to a feedback received from the aircraft (64); during the rotation of the vehicle (58), the aircraft is charged (46); upon completing charge replenishment (48) of the aircraft, the vehicle is detached from the docking ring (50) and the aircraft continues its path in the air (52)

Images