CHARGING STATION AND CHARGING COMPOSITION STATION

Description

[0001] The invention relates to a charging station for a vertically launching and landing aircraft and a charging combination station.

[0002] Aircraft for transporting people and / or cargo are becoming increasingly important because they enable rapid transport largely independent of infrastructure such as roads, railways, bridges, tunnels, etc. This is especially true for smaller aircraft that can take off and land vertically and therefore do not require a runway.

[0003] For example, WO 2013 / 124300 discloses an aircraft that has several propellers arranged in a single plane and associated electric motors. To power the electric motors, an energy storage device, such as batteries, a supercapacitor, or fuel cells, is integrated into the aircraft's frame structure. Furthermore, an energy converter is provided to supply electrical energy; this could be, for example, an internal combustion engine with a generator or another energy converter, such as a range extender, which recharges the energy storage devices during flight.US 9 505 493 B2 discloses a system for facilitating automated landing and takeoff of an autonomous or pilot-controlled hovering aircraft with a cooperative underbody at a stationary or mobile landing site and an automated storage system used in conjunction with the landing and takeoff mechanism to store and maintain a variety of UAVs.

[0004] A disadvantage of this is that the energy storage, the energy converter, and the fuel required for the energy converter increase the mass of the aircraft, thus impairing the aircraft's flight characteristics and increasing its energy consumption.

[0005] Furthermore, the energy converter and the fuel pose a hazard and thus a safety risk. Energy efficiency is also limited, as decentralized conversion of fuel into electrical energy and its storage are planned. The use of electrical energy from renewable energy sources is either not possible or only possible to a limited extent, except perhaps if the fuel is produced from renewable raw materials.

[0006] The object of the invention is therefore to provide a method for charging the energy storage systems of an aircraft simply, quickly, and safely, thereby reducing the aircraft's energy consumption. It would also be desirable to enable charging using renewable energy sources.

[0007] This problem is solved by the subject matter of the independent claims. Advantageous embodiments of the invention are specified in the dependent claims.

[0008] A charging station according to the invention for a vertical take-off and landing aircraft, which has one or more energy storage devices, comprises a charging device for transferring electrical energy to the energy storage device(s), e.g. . rechargeable batteries or supercapacitors of the aircraft.

[0009] The aircraft can land at or on the charging station for the purpose of electrically charging the energy storage device(s) and take off again from the charging station after the charging process is complete.

[0010] Preferably, the charging station is designed as a stationary charging station, i.e., a fixed charging station. However, the charging station can also be designed as a mobile, relocatable charging station, e.g., by being movable via a conveyor system.

[0011] The charging station can be integrated into a take-off and landing station for a vertical take-off and landing aircraft for the transport of persons and / or cargo, or into another transport and logistics system for aircraft, or be connected in the immediate vicinity of a take-off and landing station or a transport and logistics system.

[0012] Preferably, the charging station can be integrated into or connected to existing infrastructure, such as buildings, traffic engineering objects like bus stops, or street lighting.

[0013] The vertical take-off and landing (VTOL) aircraft is designed for transporting people and / or cargo. For this purpose, the aircraft may be equipped with a suitable transport module.

[0014] It can have a suitable flight module for propelling the vertically launching and landing aircraft.

[0015] The transport module can be attached to and detached from the flight module. The flight module can therefore fly autonomously and be optionally connected to different transport modules. With such a modular design of the aircraft, the charging station can be configured according to various variants for each flight module, with the charging device being designed to transfer electrical energy to the energy storage device(s) of the flight module.

[0016] Thus, a flight module of the aircraft can autonomously land at or on the charging station, the flight module's energy storage devices can be electrically recharged, and the flight module can then take off again. Preferably, the charging station has a charging platform on which the aircraft is parked or the flight module is stored during charging.

[0017] The charging equipment can be attached to or on the loading platform. The loading platform can, for example, have at least the same spatial dimensions as the aircraft or flight module.

[0018] The charging station can preferably be designed and arranged so that it is accessible from multiple directions. For example, the charging station can be built on lampposts, columns, or roofs. This allows the charging station to be reached from various horizontal and vertical directions, meaning the aircraft or flight module can approach the charging station from different directions and land on it, as well as take off from the charging station in different directions. This avoids time-consuming landing or takeoff procedures using predefined flight corridors.

[0019] The charging station has one or more positioning devices for holding, fixing, and aligning the aircraft, for example, for holding, fixing, and aligning a flight module of the aircraft. The positioning device(s) can be attached to or mounted on the charging platform. Optionally, the landing of the aircraft or flight module can be performed such that the aircraft or flight module approaches the charging station and, upon reaching a predetermined approach point, is detected by the positioning device(s) of the charging station.

[0020] The positioning device(s) have one or more arms with gripper and / or support devices, for example in the form of movable gripping arms, e.g. beam-shaped, single- or multi-segment gripping arms, in the form of variable linear units or similar multi-axis mechanical constructions (such as industrial robots).

[0021] Optionally, the positioning device(s) can be designed with variable length, i.e., extendable. Length variation can be achieved, for example, by telescopically sliding several segments of the positioning device into one another. This allows adaptation to aircraft or flight modules with different geometric configurations, enabling various aircraft or flight modules to be detected, aligned, and placed on the loading platform of the charging station. Alternatively or in addition to using a loading platform, gripper and / or support devices of the positioning device can serve as supports and for fixing the aircraft or flight module.

[0022] The positioning device(s) also allow the aircraft or flight module to be aligned in such a way as to enable a connection with the charging device.

[0023] After the charging process is complete, the aircraft or flight module can take off directly from the loading platform or from the gripper and / or support devices of the positioning system.

[0024] Alternatively, aircraft or flight modules can be temporarily stored in or at the charging station, e.g. in preparation or follow-up of a charging process.

[0025] The positioning device(s) can preferably be arranged such that they extend diagonally upwards, thus establishing a safety distance between the positioned aircraft or flight module and the base of the charging station. For example, the positioning device(s) can extend upwards at an angle of approximately 45°.

[0026] In a charging station, which is particularly suitable for charging the electrical energy storage of a flight module of the aircraft, a supporting structure of the flight module can be detected by means of the positioning device(s).

[0027] The flight module has several propulsion units arranged on a supporting structure, wherein the supporting structure has girders connected to each other at nodes, and each propulsion unit can have an electric motor and a propeller operatively connected to the electric motor. The propulsion units can optionally be arranged in a single plane.

[0028] The supporting structure can have radially, axially and tangentially arranged, preferably straight or curved structural beams, which can be connected to each other at nodes and, if necessary, to a central unit located in the middle of the supporting structure, for example by means of connecting pieces assigned to the supporting structure, e.g. T-pieces.

[0029] The structural beams can, for example, be arranged to form a planar, hexagonally braced structural structure. This can be achieved by providing six radially evenly spaced structural beams, such that two adjacent radially arranged structural beams form an angle of approximately 60°.

[0030] The flight module can have a central unit, which may preferably be located centrally. The central unit can, for example, have a housing, e.g., in the form of a hemisphere or an ellipsoid. For example, the central unit can be formed from two interconnected halves, e.g., bolted together. Access points can be provided for maintenance and minor repairs. The central unit can also be designed to accommodate structural beams of the supporting structure, e.g., by attaching structural beams of the supporting structure at one end to the central unit and extending radially outwards from the central unit.

[0031] The central unit can include technical functional units, such as control, positioning, and / or communication technology, and / or a charging module. An integrated charging module can include energy storage devices, e.g., in the form of rechargeable batteries or supercapacitors, a charging device, and / or solar cells. The charging device can be configured to transfer electrical energy from an external charging station, for example, the charging station according to the invention, to the energy storage device(s).

[0032] The flight module can have a coupling device for connecting the transport module to the flight module. In other words, the coupling device is designed for attaching and detaching a transport module. Preferably, the coupling device can be arranged centrally on the central unit.

[0033] This coupling device can also be used for the electrical connection of the flight module to a charging device of the charging station.

[0034] The charging device of the charging station according to the invention serves to transfer electrical energy to the energy storage devices of the aircraft or flight module. For this purpose, it can have conductive cables with suitable electrical connections, e.g., pluggable / connectable media connections. Alternatively or additionally, the charging device can be designed for inductive charging of the aircraft or flight module.

[0035] The charging device can be connected to the aircraft or flight module from a central, i.e., middle, point of the charging station.

[0036] If the coupling device of the flight module is to be used for electrical connection with the charging device, the coupling device can be designed for electrical connection of the charging device of the charging station and the charging device of the charging station can have a corresponding coupling counterpart which can be coupled to the coupling device of the flight module, so that the electrical energy can be transferred to the energy storage device(s) of the flight module via the coupling device and thus the energy storage device(s) of the flight module can be charged.

[0037] Depending on the design variant, the charging device can have a flexibly designed connector for variable connection to the aircraft or flight module.

[0038] This allows for local adaptation of the charging device connection in order to charge energy storage devices or flight modules of different geometric designs.

[0039] To create a variable connection, the charging device can have a flexible connector, e.g., a telescopic boom with several segments and, for example, an internal cable. By sliding several segments of the boom into one another, a variation in the length of the charging device connector can be achieved.

[0040] To create a further variable connection, the loading device can have a flexible connector, such as an articulated linkage with, for example, several linkage arms connected to each other by joints. This allows, for example, a variable length and radius of the connector of the loading device.

[0041] To create another variable connection, the charging device can have a flexible connector, such as an elastic hose with an internal cable. The length can be varied, for example, by winding or unwinding the hose.

[0042] In addition, the connector can have a joint connection at the central connection point of the charging device at the charging station to further increase the flexibility of the connection options to the energy storage systems of aircraft or flight modules.

[0043] Alternatively, charging can also be done via induction.

[0044] In addition to transmitting electrical energy, the charging device can also be used for data transmission to the aircraft or flight module. For this purpose, the charging device may be equipped with a data cable.

[0045] Optionally, the charging station may include technical functional units, such as control, positioning and / or communication technology.

[0046] Position determination technology can be designed, for example, using location signals, e.g., from a global navigation satellite system such as GPS, Galileo, GLONASS, Beidou, etc., to determine the position of the flight modules and to determine and control the flight route and destination of the flight modules.

[0047] The attitude determination technology can also include systems which, using sensors of different operating principles (optical, ultrasound, induction, eddy current), support the landing / takeoff process as well as the coupling and uncoupling to the charging station, either individually or in combination.

[0048] The communication technology can be designed for internal and / or external communication, whereby internal communication refers to communication with modules that are directly intended for use with the charging station, for example, communication for understanding between aircraft, flight module and charging station.

[0049] External communication includes, for example, communication regarding flight permission, flight route, location, etc. with air traffic control or the exchange of information with weather services.

[0050] For example, the communication technology can be designed to send a message about the status of the charging station, e.g., maintenance or repair needs, or to report a free charging station.

[0051] Depending on the design, the charging station can be connected to a power grid, preferably a high-voltage grid. This allows for the use of an infrastructure connection, i.e., a connection to a local power grid, enabling the direct transfer of electrical energy from the grid to the energy storage system. Depending on the source of the electrical energy fed into the grid, such as solar panels or wind turbines, renewable energy sources can be used to charge the energy storage system and subsequently power the flight module. A connection to a high-voltage grid advantageously enables particularly fast charging of the energy storage system, thereby increasing the flexibility of the flight module's deployment.

[0052] The positioning device(s) comprise one or more gripper and / or support devices. These can be designed, for example, as a fork-shaped receiving device(s) for receiving a supporting structure of the flight module. These receiving device(s) can be arranged, for example, at one end of the positioning device, preferably at an outer end.

[0053] Preferably, the fork-shaped receiving devices can be designed to receive one structural beam of the supporting structure each.

[0054] The fork-shaped mounting device can support and enclose the supporting beam from below, thus enabling secure fixing and simple and precise alignment of the supporting structure and therefore of the flight module.

[0055] The receiving device may optionally include one or more fixing elements for securing the structural beams. These fixing elements may, for example, be in the form of clamps that firmly enclose the structural beams once they have been inserted into the fork-shaped receiving device. This locking mechanism prevents the structural beam from unintentionally detaching from the fork-shaped receiving device. The connection is only released after the locking mechanism has been disengaged by the fixing element(s).

[0056] According to further design variations, several positioning devices can be arranged in a star shape and / or at equal intervals. For example, the positioning devices can radiate outwards from a central point of the charging station. The star-shaped arrangement, as well as the evenly spaced arrangement, enables a uniform distribution of the flight module's mass on the charging station and thus improves the charging station's safety.

[0057] The specific arrangement of the positioning devices depends on the design of the flight module, particularly its supporting structure. For example, if the supporting structure has a hexagonal shape with six radially outward-extending support beams, then preferably six positioning devices can be provided, each positioning device serving to fix and align one of the six radial support beams. The positioning devices can radiate outwards in a star shape and be evenly spaced apart from each other, with each pair of positioning devices forming an angle of 60° with each other.

[0058] According to various design variants, the charging station, preferably the charging device and / or the positioning devices, can have a fiber composite material or consist of a fiber composite material.

[0059] The fiber composite material can be, for example, a fiber-reinforced plastic, such as carbon fiber, glass fiber or basalt fiber-reinforced plastic.

[0060] The fiber-reinforced composite material may incorporate special textile fiber reinforcement elements. The textile fiber reinforcement can be in the form of sheet or strip-shaped woven fabrics, knitted fabrics, crocheted fabrics, or braids embedded in a polymer matrix.

[0061] The use of fiber-reinforced composites improves the stability-to-mass ratio of the charging station or its components, as components made from fiber-reinforced composites have a low mass while exhibiting good to very good mechanical properties, such as strength, modulus of elasticity, and impact strength.

[0062] Depending on the load, the booms of the positioning devices can be designed, for example, as rods or beams, and have a solid or hollow profile cross-section.

[0063] The booms have a hollow profile in which the electrical lines are arranged. This allows cables for the charging device or signal lines for the communication systems to be routed within them.

[0064] A charging station according to the invention for vertically launching and landing aircraft, each with one or more energy storage devices, comprises several of the charging stations described above.

[0065] If the aircraft each have a modularly handleable flight module as described above, the charging station according to the invention can be configured in various embodiments for the flight modules of the vertically launching and landing aircraft. This charging station for flight modules, each with one or more energy storage devices, also includes several of the charging stations described above.

[0066] Therefore, the above explanations of the charging station according to the invention also serve to describe the charging network station according to the invention. The advantages of the charging network station according to the invention correspond to those of the charging station according to the invention and its corresponding embodiments.

[0067] By combining multiple charging stations into a single charging hub, it is possible to charge the energy storage systems of several aircraft or flight modules simultaneously. The space requirement is also reduced compared to multiple individual charging stations. Furthermore, only a single infrastructure connection, i.e., a single connection to a local power grid, is required to provide electrical energy for multiple charging stations.

[0068] This provides an efficient charging technology for charging the aircraft or charging modules.

[0069] Each charging station can have a charging platform, preferably a flat one, in addition to the positioning device(s) and the charging device. The charging platform can serve for parking an aircraft or for placing a flight module. The positioning device(s) and / or the charging device can be attached to or on the charging platform. The charging platform can, for example, correspond to the spatial dimensions of the aircraft or flight module.

[0070] Alternatively or in addition to using a loading platform, the mountings of the positioning devices can serve as supports for the aircraft or flight modules.

[0071] Depending on the design, the charging stations can be vertically and / or horizontally movable, e.g., repositionable. This allows for a space-optimized arrangement of the charging stations, both with and without the aircraft or flight modules being charged.

[0072] According to further design variations, the charging station can have a housing to enclose the charging stations. For example, the housing can completely enclose the charging station or at least cover it from above.

[0073] The housing may have one or more openings. One or more upward openings may be provided for the vertical takeoff or landing of the aircraft or flight module(s). One or more lateral openings may be provided for the lateral extension and retraction of positioning devices to bring the aircraft or flight module into a takeoff position or to prepare for the landing of an expected aircraft / flight module.

[0074] The housing serves to protect the charging stations and the aircraft or flight modules from weather and other external, harmful influences.

[0075] Depending on the design, the charging stations can be arranged in a rack configuration, e.g., vertically stacked one above the other in one or more horizontally arranged rows. For loading and unloading the aircraft / flight modules, the positioning devices of the charging stations can be extended horizontally, thus enabling vertical take-off and landing of the aircraft or flight module. The rack configuration represents a particularly space-saving arrangement of the charging station.

[0076] The shelving arrangement can be implemented using a racking system designed, for example, in the style of a paternoster lift. In the style of a paternoster lift, this means that the loading stations are arranged in two vertically adjacent rows and can be moved in a continuous loop – just like a paternoster lift. At the top and bottom turning points, the loading stations are transferred to the other row.

[0077] Depending on the design, the charging stations can be arranged in a revolver configuration. For this purpose, the charging stations can be mounted together on a base plate, e.g. . The charging station is arranged on a circular base plate that can rotate around a preferably vertical axis of rotation. For receiving or releasing the aircraft / flight modules, or for launching or landing them, the charging station can be rotated by means of the rotatable base plate in front of a lateral opening or under a top opening of the housing of the charging station to bring the respective aircraft / flight module into a launch-ready position or to enable the landing of the expected aircraft / flight module.

[0078] The revolver arrangement represents another particularly space-saving arrangement variant of the charging station.

[0079] Further advantages of the present invention are evident from the illustrations and the accompanying description. They show, in schematic representation: Figure 1 shows a top view of a charging station according to the invention in a revolver arrangement with a side opening; Figure 2 shows a top view of a charging station according to the invention in a revolver arrangement with a top opening; Figure 3 shows a perspective view of a charging station according to the invention in a rack arrangement with side openings; Figure 4 shows a perspective view of a charging station according to the invention in a rack arrangement with a top opening; Figure 5 shows a perspective view of a charging station according to the invention in a star arrangement on a lighting mast.

[0080] In the examples described below, reference is made to the accompanying drawings, which form part of the examples and in which specific embodiments of the invention are shown for illustrative purposes. In this respect, directional terminology such as "top," "bottom," "front," "back," "anterior," "rear," etc., is used with reference to the orientation of the figures described. Since components of embodiments can be positioned in a number of different orientations, the directional terminology serves for illustrative purposes and is in no way restrictive.

[0081] It is understood that other embodiments may be used and structural or logical modifications made without deviating from the scope of protection of the present invention. It is understood that the features of the various exemplary embodiments described herein may be combined with one another, unless specifically stated otherwise. The following detailed description is therefore not to be interpreted as limiting, and the scope of protection of the present invention is defined by the appended claims.

[0082] Within the scope of this description, the terms "connected", "connected" and "coupled" are used to describe both a direct and an indirect connection, a direct or indirect connection and a direct or indirect coupling.

[0083] In the figures, identical or similar elements are provided with identical reference symbols where appropriate.

[0084] Figure 1 shows a first variant of a charging station 12 according to the invention for flight modules 1 in a turret arrangement of the individual charging stations 2.

[0085] The charging station 12 comprises four charging stations 2 arranged on a rotating base plate 4. Each charging station 2 has a charging platform for parking one flight module 1. Three of the four charging stations 2 each contain a parked and charging flight module 1, with these charging stations 2 being located in a parking position 11.

[0086] The charging station 12 has a housing with a lateral, lockable opening 7.

[0087] The charging station 2 located in front of opening 7 is unoccupied and is in a ready position 3 to receive a flight module 1 into charging station 2 or to release a flight module 1 from charging station 2.

[0088] The charging station 12 has a positioning device 5 near the opening 7 for holding, fixing and aligning a flight module 1, which is designed as a telescopic device and extends into Figure 1 is in an extended position.

[0089] A flight module 1 is held in a take-off / landing position 6 on the positioning device 5 extended through the opening 7, wherein the flight module 1 is detected and aligned by the positioning device 5 from the landing approach or the flight module 1 is held ready for take-off.

[0090] The flight module 1 can be moved to the charging station 2, which is in ready position 3, using the positioning device 5 and, if necessary, placed on the charging platform of the charging station 2.

[0091] Here, the flight module 1 can be connected to a charging device (not shown) of the charging station 2 in order to be charged.

[0092] For an electrical connection of the flight module 1 with the charging device, a conventional electrical plug device can be provided, or the coupling device of the flight module 1, which is intended for coupling a transport module, can also be designed as an electrical coupling device.

[0093] At the same time, the charging device of charging station 2 has a corresponding coupling counterpart which can be coupled to the coupling device of flight module 1 and transmits the electrical energy to flight module 1.

[0094] Alternatively, the flight module 1 can be charged inductively via coils.

[0095] Meanwhile, the base plate 4 can be rotated so that an adjacent charging station 2, previously in parking position 11, is positioned in the ready position 3 in front of the opening 7.

[0096] Using the positioning device 5, the previously parked flight module 1 can be removed from the charging station 2, which is now in ready position 3, and moved to the take-off / landing position 6 for departure.

[0097] Figure 2 shows a second variant of a charging station 12 according to the invention in a revolver arrangement similar to the charging station 12 according to Figure 1 .

[0098] Therefore, only the differences to the version according to the following will be discussed below. Figure 1 described.

[0099] The charging station 12 has a housing with an upper, lockable opening 7 in the roof of the housing.

[0100] The charging station 2, located directly below opening 7, is unoccupied and is in a ready position 3 to receive a flight module 1 into the charging station 2 or to release a flight module 1 from the charging station 2.

[0101] The charging station 12 has a positioning device 5 near the opening 7 for holding, fixing and aligning a flight module 1, which can be designed as a telescopic or stationary device.

[0102] At the positioning device 5, a flight module 1 can be detected, held and aligned during landing approach and moved to the charging station 2 located in the ready position 3 (not shown).

[0103] Here, the flight module 1 can be connected to a charging device (not shown) of the charging station 2 in order to be charged.

[0104] At the same time or subsequently, the base plate 4 can be rotated so that an adjacent charging station 2, previously in parking position 11, is positioned in the ready position 3 under the opening 7.

[0105] By means of the positioning device 5, the flight module 1, which was previously in parking position 11, can be detected by the charging station 2, which is now in ready position 3, and moved to a take-off / landing position 6 (not shown) for departure.

[0106] Figure 3 Figure 1 shows a charging station 12 according to the invention for flight modules 1 in a rack arrangement with side openings.

[0107] The charging station 12 comprises six charging stations 2, which are arranged one above the other in a racking system 8 in the manner of a high-bay warehouse. At each charging station 2, there is a parked and charging flight module 1, which is held by a positioning device 5 of the charging stations 2. Five of the six charging stations 2 are located in a parking position 11.

[0108] The charging station 12 has a housing with six lateral, lockable openings 7, each of which is assigned to a charging station 2.

[0109] The positioning devices 5 of the charging stations 2 are designed here as a telescopic device. In Figure 3 The positioning device 5 of a charging station 2 is in an extended position.

[0110] A flight module 1 is held in a take-off / landing position 6 on the positioning device 5, which is extended through an associated opening 7, wherein the flight module 1 is detected and aligned by the positioning device 5 from the landing approach or the flight module 1 is held ready for take-off.

[0111] The flight module 1 can be inserted into the housing using the positioning device 5.

[0112] The positioning device 5 can be connected to a charging device (not shown) so that the flight module 1 held at the positioning device 5 can be charged directly.

[0113] Here too, a conventional electrical connector can be provided for the electrical connection of the flight module 1 to the charging device, or the coupling device of the flight module 1 can simultaneously be designed as an electrical coupling device that corresponds to a corresponding coupling counterpart of the charging device. Alternatively, the flight module 1 can be charged inductively via coils.

[0114] Meanwhile, a parked, charged flight module 1 from another charging station 2 can be moved to the take-off / landing position 6 for take-off by means of the positioning device 5 of this charging station 2 through the associated opening 7.

[0115] Figure 4 A second variant of a charging station 12 according to the invention is shown in a rack arrangement similar to the charging station 12 according to Figure 3 .

[0116] Therefore, only the differences to the version according to the following will be discussed below. Figure 3 described.

[0117] The charging station 12 comprises twelve charging stations 2, arranged in a two-row racking system 8. At five charging stations 2, a parked and charging flight module 1 is located in a parking position 11, each held by a positioning device 5 of the charging stations 2.

[0118] The charging station 12 has a housing with an upper, lockable opening 7.

[0119] The racking system 8 is designed in the form of a paternoster lift, on which the loading stations 2 can be moved and repositioned in the transport direction 9.

[0120] Thus, each of the charging stations 2 can be positioned under the opening 7 and the flight module 1, held by the positioning device 5, can be moved into the take-off / landing position 6. Alternatively, an expected flight module 1 can be detected and aligned by the positioning device 5 of a charging station 2 that has advanced via the paternoster system and is in ready position 3 under the opening 7.

[0121] The charging process for flight modules 1 can be carried out as described above.

[0122] Figure 5 Figure 1 shows a charging station 12 according to the invention with four star-shaped charging stations 2 arranged on a light pole 10 of an existing infrastructure.

[0123] At each of the three charging stations 2 there is a parked and charging flight module 1, which is held and fixed by a positioning device 5 of the charging stations 2.

[0124] The positioning devices 5 of the charging stations 2 are designed as a telescopic device.

[0125] With the telescopic positioning device 5 (not shown) extended, the flight module can be moved into the take-off / landing position 6, or an expected flight module can be detected and aligned using the positioning device 5.

[0126] The charging process for flight modules 1 can be carried out as described above.

[0127] The Figure 5 also represents an embodiment of a single charging station 2 according to the invention with only one charging device and four star-shaped positioning devices 5 for holding, fixing and aligning each of a flight module 1, wherein only one of the four flight modules is charged at a time by means of the charging device.

[0128] The expression "and / or" used here, when used in a series of two or more elements, means that each of the listed elements can be used alone, or any combination of two or more of the listed elements can be used.

[0129] For example, if a relationship is described that contains the components A, B and / or C, the relationship can contain the components A alone; B alone; C alone; A and B in combination; A and C in combination; B and C in combination; or A, B, and C in combination. Reference symbol list

[0130] 1 Flight module 2 Charging station 3 Charging station standby position 4 Rotating base plate 5 Positioning device 6 Flight module take-off / landing position 7 Lockable opening 8 Shelving system 9 Direction of movement of the paternoster shelving system 10 Light mast 11 Charging station parking position 12 Charging station

Claims

1. Charging station (2), designed for charging one or more electrical energy stores of a flight module (1) of a vertical take-off and landing aircraft, wherein the aircraft comprises the flight module (1) for the propulsion of the aircraft, which has several drive units arranged on a wing assembly, and a transport module for transporting persons and / or loads, which transport module can be coupled to and uncoupled from the flight module (1), wherein the flight module lands autonomously at or on the charging station (2) and, once the energy store(s) of the flight module (1) has / have been electrically charged, takes off again; and wherein the charging station (2) has: - a) a charging device for transferring electrical energy to the energy store(s) of the flight module (1), and - b) one or more positioning device(s) (5) designed to hold, fix and align the flight module (1), wherein the wing assembly of the flight module (1) is detected in the charging station (2) by means of the positioning device(s) (5) and the flight module (1) is aligned to enable a connection of the flight module (1) landed at or on the charging station (2) to the charging device, characterised in that the positioning device(s) (5) have one or more arms with gripper and / or support devices and the arms have a hollow profile in which the electrical wiring of the charging device is arranged.

2. Charging station (2) according to claim 1, wherein the charging device has a flexibly designed connector.

3. Charging station (2) according to one of the preceding claims, wherein the charging device has a coupling counterpart which can be coupled to a coupling device of the flight module designed for coupling a transport module, so that the electrical energy is transmitted to the energy store(s) of the flight module via the coupling device of the flight module.

4. Charging station (2) according to one of the preceding claims, wherein the one or more gripper and / or support device(s) are designed as one or more fork-shaped receiving device(s) for receiving the wing assembly of the flight module (1).

5. Charging station (2) according to claim 4, wherein the one or more fork-shaped receiving device(s) are each designed to receive a wing assembly strut of the wing assembly of the flight module (1).

6. Charging station (2) according to claim 4 or claim 5, wherein the fork-shaped receiving device(s) has / have one or more fixing element(s) for fixing a wing assembly strut.

7. Charging station (2) according to one of the preceding claims, wherein several positioning devices (5) are arranged in a star shape and / or at a uniform distance from one another.

8. Charging station (2) according to one of the preceding claims, wherein the charging station (2) comprises a fibre-reinforced composite material or is made of a fibre-reinforced composite material.

9. Charging station (2) according to claim 8, wherein the charging device and / or the positioning device(s) (5) comprise a fibre-reinforced composite material or are made of a fibre-reinforced composite material.

10. Charging station (2) according to one of the preceding claims, wherein the charging station (2) is designed to be arranged on a lamp post, pillar or roof.

11. Combined charging station (12) with several charging stations (2) according to one of the preceding claims.

12. Combined charging station (12) according to claim 11, wherein the charging stations (2) are designed to be movable vertically and / or horizontally.

13. Combined charging station (12) according to claim 11 or 12, wherein the charging stations (2) are arranged in a revolver arrangement.

14. Combined charging station (12) according to one of claims 11 to 13, wherein the charging stations (2) are arranged in a rack arrangement.

15. Combined charging station (12) according to claim 14, wherein the rack arrangement is formed by a rack system in the manner of a paternoster.