Power assistance system for supporting an electrically powered, vertical take-off and landing aircraft, power assistance device and power assistance procedure

Abstract

Power assistance system (1) for supporting an electrically powered, vertically take-off and landing (VTOL) aircraft (2), wherein the power assistance system (1) is configured to assist the aircraft (2) during a climb, and wherein the power assistance system (1) comprises a coupling device (3) with at least one cable (4) for connecting the power assistance system (1) to the aircraft (2), the power assistance system (1) comprises a flight-capable and vertically take-off and landing (VTOL) capable base device (5), and an assistance drone (6), and through the coupling device (3) the aircraft (2) can be coupled to the base device (5) for a climb by means of the cable (4) and can be uncoupled from the base device (5) after the climb, and the assistance drone (6) is configured to carry or guide the cable (4).

Description

[0001] The invention relates to a performance assistance system for supporting an electrically propelled, vertical takeoff and landing aircraft. The performance assistance system is configured to assist the aircraft during a climb, and the performance assistance system comprises a coupling device with at least one line for connecting the performance assistance system to the aircraft. The invention also relates to a performance assistance device and a performance assistance method for supporting an electrically propelled, vertical takeoff and landing aircraft.

[0002] Aircraft have different power requirements depending on the flight situation, such as climb, descent, or level flight. Climb flight, in particular, requires comparatively high power and energy from the propulsion components, such as an electric motor for propulsion and a battery for energy storage. This requirement is significantly lower during horizontal and descent flight. In most conventional applications, the aircraft spends the majority of its flight time in horizontal flight. Nevertheless, the propulsion components are also designed for climb and are therefore oversized and energy-efficient during horizontal flight.The propulsion components are predominantly operated below their capacity limits, which is disadvantageous in terms of mass, volume, efficiency, and manufacturing costs in terms of the technical design and construction of the aircraft. A design of the propulsion components without excessive consideration of climb is advantageous in this context. However, a solution must be found that enables the aircraft, and any cargo carried by the aircraft, to be transported to a vertical takeoff or target altitude at which the aircraft can transition to horizontal flight, despite the design for lower power requirements.

[0003] US 2014 / 0 251 743 A1 discloses a system for launching an aircraft. The system includes an electrically powered, lift-assisted aircraft, a control system for maneuvering the aircraft, and a linkage configured to couple the aircraft and a ground-based power supply to provide power to the aircraft.

[0004] Ground-based power supply has the disadvantage that the power supply can only be effectively extended to the point where the power is delivered by the electrical cable. This limits the power supply and requires energy efficiency improvements by transporting a potentially long and therefore heavy electrical cable.

[0005] US 2015 / 0 336 677 A1 discloses a system for recharging batteries transported by an electrically powered aircraft. The system comprises a charging aircraft and an aircraft to be charged. For power assistance, the charging aircraft and a coupling device for coupling the charging aircraft to the aircraft to be charged can be configured to provide, in addition to the battery charging current, a power assistance current to support the propulsion and supply of the aircraft to be charged. The charging aircraft can be a drone.

[0006] Due to the required coordination of the positions of the charging aircraft and the aircraft being charged, the proposed battery recharging system requires improvement. Furthermore, the potential application area could be expanded through improvements.

[0007] US 2017 / 0 158 354 A1 discloses a performance assistance system for supporting an electrically powered, vertical takeoff and landing aircraft. The performance assistance system comprises a coupling device connected to a stationary power source via a cable. The coupling device can be transported to the aircraft by means of an assistance drone.

[0008] US 2003 / 0 136 874 A1 discloses an arrangement for refueling a helicopter using a tanker aircraft. This refueling can be performed using an additional drone positioned between the helicopter and the tanker aircraft, allowing safe refueling of the helicopter outside the rotor blades.

[0009] US 2017 / 0 043 872 A1 discloses a fire extinguishing arrangement in which a fire hose can be transported from a tanker vehicle to the vicinity of a fire site by means of a drone.

[0010] US 2013 / 0 037 650 A1 discloses a system by which a long-distance transport aircraft can be connected to a logistics aircraft for intermediate refueling. For this purpose, both aircraft have docking points that can be connected to each other via a supply line during flight operations.

[0011] US 2012 / 0 073 682 A1 discloses a system for distributing energy, particularly liquid hydrogen. This system comprises a plurality of airworthy balloons designed to generate liquid hydrogen. Liquid hydrogen is collected from these balloons by additional aircraft and transported to the destinations.

[0012] The invention is based on the object of providing an improved performance assistance for the purpose of reducing the power and energy requirements of the aircraft with improved application possibilities of the performance assistance.

[0013] According to the invention, the performance assistance system comprises a flight-capable base device capable of vertical takeoff and landing, and an assistance drone. The invention comprises a flight-capable base device that accompanies the aircraft during vertical climb and, if necessary, during descent, serving as an energy and power source for the aircraft. The coupling device allows the aircraft, coupled to the base device via the cable for climb, to be decoupled from the base device after the climb. The aircraft can then enter horizontal flight, and the base device can descend to the ground to be available for the next climb of the aircraft or another aircraft. The invention enables performance assistance for various types of aircraft.

[0014] The assistance drone according to the invention is configured to carry or guide the cable. This eliminates the need for the aircraft itself to carry the cable during the climb. This allows the aircraft to be designed more efficiently and lighter for the climb, as it does not need to lift the mass of the cable. Furthermore, the assistance drone serves to coordinate the cable before, during, and / or after the aircraft is coupled to the base device.

[0015] The base device's ability to take off and land vertically eliminates the need for a cable to the ground, thus eliminating the need for ground-based support for the aircraft. This makes power assistance possible not only from the ground up to a height corresponding to the cable length, but also beyond. The distance between the aircraft and the ground is smaller than the distance between the aircraft and the base device. This reduces the weight of the cable compared to current technology, unhinders air traffic between the aircraft and the cable origin, and effectively avoids strong forces due to winds acting on the cable, as well as an increase in the size of the assistance drone due to the cable's weight.

[0016] The aircraft comprises a propulsion system and a propulsion energy storage unit. The power assistance system according to the invention can reduce the power requirements of the propulsion system and / or the required capacity of the propulsion energy storage unit.

[0017] The invention recognizes that with the performance assistance according to the invention, the aircraft does not have to manage the climb completely independently. This allows the components of the corresponding drive train of the aircraft to be designed with lower power and energy consumption, thus making them more cost-effective, lighter, more efficient, and more energy-efficient. The aircraft thus exhibits the usual characteristics, particularly for climbing, and the capabilities for transporting cargo, for example, while at the same time, in conjunction with the base device, it is more efficient and cost-effective than previously known systems.

[0018] The aircraft itself is not transported by the base device; instead, the propulsion system is configured for climbing. However, the aircraft's propulsion energy storage unit can be designed to be smaller and thus lighter and more efficient than in previously known aircraft. Furthermore, the cooling requirements, particularly of the propulsion system and / or the propulsion energy storage unit, can be reduced by the invention, since the cooling requirements are based on the maximum power delivered or drawn. The invention allows for a decoupling of the high takeoff power from the energy required for horizontal flight.

[0019] In a preferred embodiment of the invention, the base device comprises a balloon filled with a gas having a lower density than air in order to improve the energy efficiency of the performance assistance system. The balloon filled with the gas has a buoyancy force that supports the climb of the base device. Hydrogen and helium are advantageously considered as gases. The hydrogen can be supplied via the line from the base device to the aircraft, where the hydrogen is converted, for example, using a fuel cell as a drive energy converter into electrical energy to drive the engine. As an alternative to the balloon, the base device can comprise a performance assistance drone, in particular one that is electrically driven.

[0020] In a further preferred embodiment of the invention, the base device comprises a base energy storage device to provide energy for controlling the base device and / or to support the climb and descent of the base device. The base energy storage device further supports the fact that the base device is not physically connected to a ground station and can therefore manage a climb without restrictions. The energy can be present, in particular, in the form of electrical energy or in the form of a gas from which electrical energy is generated. The base energy storage device can store energy in such a way that it can be supplied to the aircraft via the cable.

[0021] In an advantageous embodiment, the base energy storage device is an electrical energy storage device, and electrical energy from the base energy storage device can be supplied to the aircraft via the coupling device. In this embodiment, the line is an electrical line that supplies electrical energy from the base energy storage device to the propulsion energy storage device and / or the aircraft's drive, wherein the propulsion energy storage device is configured to store electrical energy. The electrical energy in the base energy storage device can, for example, be supplied from an energy reservoir of a ground station before the base device climbs and / or be provided by converting hydrogen contained in a balloon into electrical energy.

[0022] Advantageously, the base device comprises an energy converter for converting energy stored in the base energy storage device into electrical energy, wherein the base energy storage device is formed at least partially by the balloon. For example, the base energy storage device can be a hydrogen-filled balloon, and the energy converter can comprise a fuel cell that converts the hydrogen into electrical energy. This allows for the use of hydrogen synergy, in which hydrogen is used simultaneously as a buoyancy medium and as a fuel.

[0023] The base device advantageously has a winding device for winding up the cable in order to control its length. The length of the cable is advantageously controlled such that the cable is neither overtightened, which would inhibit the aircraft's climb, nor too long and thus heavy, which would interfere with the base device, for example, by the cable getting caught in the engines. The winding device can, in particular, be electrically driven and advantageously supported by a spring that creates a preload.

[0024] The assistance drone is preferably configured to guide the line for coupling to the aircraft in order to advantageously coordinate the length and route of the line between the base device and the aircraft. The assistance drone can preferably also support the coupling and / or decoupling of the aircraft and the line. The line can be rigidly connected to the assistance drone at a distance from a coupling configured to couple the aircraft to the line. The coupling can, in particular, comprise an electrical contact, for example a plug, and / or a hydrogen line.

[0025] The base device advantageously has a propulsion unit for horizontal positioning of the base device. The propulsion unit improves the horizontal positioning of the base device, particularly in crosswinds and / or during vertical flight maneuvers, such as for corrections if necessary, as well as during climbs and descents depending on the load and the current lift force. The base device advantageously comprises multiple propulsion units. The propulsion units can either be pivoted horizontally and vertically and / or have different mounting angles to ensure control of the base device. The propulsion unit(s) are advantageously electrically driven.

[0026] A performance assistance device according to the invention comprises a previously described performance assistance system and a ground station, wherein the ground station has a landing area for landing the base device and an energy reservoir for storing energy that can be supplied to the base device. The invention has recognized that the performance assistance system can be operated particularly effectively with the ground station. The landing area can have landing sites assigned to a base device, wherein each landing site is assigned one or more further landing sections for one or more aircraft. The energy reservoir can be configured, in particular, to provide energy for the base device and / or the aircraft. For example, the energy reservoir can comprise an electrical energy reservoir and / or a gas reservoir.

[0027] According to the invention, a power assistance method for supporting an electrically propelled, vertical takeoff and landing aircraft comprises the following steps: establishing a connection for energy transmission between the aircraft and a base device via a cable, climbing the aircraft and simultaneously climbing the base device, with the cable being guided by an assistance drone, and severing the connection between the aircraft and the base device upon reaching a target altitude. After the connection is established, the aircraft can be supplied with energy from the base device. This means that, in particular, a propulsion energy storage device of the aircraft does not need to meet high requirements to manage the climb.The invention also recognizes that by routing the cable through the assistance drone, the aircraft can be designed for a significantly easier climb, resulting in increased component efficiency. After the connection is severed, the aircraft can, in particular, efficiently perform horizontal flight.

[0028] Further preferred embodiments of the invention emerge from the remaining features mentioned in the subclaims.

[0029] The various embodiments of the invention mentioned in this application can be advantageously combined with one another, unless otherwise stated in the individual case.

[0030] The invention is explained below in exemplary embodiments with reference to the accompanying drawings. They show: Fig. 1 an embodiment of a performance assistance system with a balloon; Fig. 2 an embodiment of a performance assistance system with a performance assistance drone; and Fig. 3 an embodiment of a performance assistance system with multiple aircraft.

[0031] Fig. 1 shows an embodiment of a performance assistance system 1 with a balloon 8. The performance assistance system 1 for supporting an electrically propelled, vertically take-off and landing capable aircraft 2 or a drone is configured to assist the aircraft 2 during a climb.

[0032] The aircraft 2 has an electric drive 19 and a drive energy storage unit 20. The drive 19 and the drive energy storage unit 20 are also designed for climbing, but primarily for horizontal flight and a comparatively low-power climb. This allows the drive 19 and the drive energy storage unit 20 to be designed particularly efficiently and lightweight.

[0033] The performance assistance system 1 comprises a flight-capable and vertically take-off and landing base device 5 and an assistance drone 6.

[0034] The base device 5 comprises a construct with, for example, two levels 15, 16. An upper level 15 comprises engines 11 and a system component 14 as an electronic control device, in particular for controlling the base device 5. The system component 14 is configured to control the base device 5, in particular to control a winding device 10 and the engines 11, to coordinate the base device 5 with the assistance drone 6 and / or to coordinate the base device 5 with the aircraft 2.

[0035] The electrically driven engines 11 of the base device 5 are either horizontally and vertically pivotable and / or have different mounting angles to ensure control of the base device 5. The engines 11 serve to horizontally position the base device 5, particularly for sidewalls and during vertical flight maneuvers, such as for corrections if necessary, as well as for climb and descent depending on the load and the current lift force.

[0036] The base device 1 comprises a balloon 8, wherein the balloon 8 is arranged within a frame structure 18 in a lower level 16 of the base device 1. The balloon 8 of the base device 5 is filled with a gas 7 that has a lower density than air. This allows the base device 5 to climb with the aid of a buoyancy force. The balloon 8 or its envelope is impermeable to the gas 7. The balloon 8 does not require any further frame structure. The balloon 8 is flexible in its shape and can expand and contract within certain limits depending on the gas content. The gas 7 with which the balloon 8 is filled can, in particular, be hydrogen. The gas 7 can thus serve both to provide buoyancy for the base device 5 and to provide energy that can be converted into electrical energy by means of an energy converter 12.Thus, in this embodiment, the balloon 8 forms a basic energy storage device 9, wherein the energy stored in the basic energy storage device 9 can be supplied both to the engines 11 of the base device 5 and to the aircraft 2 for power assistance.

[0037] In the upper level 15 of the base device 5, an electrical energy storage device 13 and an energy converter 12 are provided on an annular section of the frame structure 18. The energy converter 12 is configured to convert the energy present in the balloon 8 in the form of hydrogen, advantageously as a gas 7, into electrical energy and supply it to the electrical energy storage device 13. The energy converter 12 can comprise, for example, a fuel cell, a gas turbine, and / or a generator. The electrical energy storage device 13 comprises, for example, a rechargeable battery.

[0038] The electrical energy generated from the gas 7 and / or the electrical energy stored in the electrical energy storage device 13 can be used to drive the engines 11. Furthermore, the electrical energy stored from the gas 7 and / or in the electrical energy storage device 13 can be supplied to the aircraft 2 for power assistance.

[0039] A coupling device 3 is provided for electrically connecting the base device 5 to the aircraft 2. The coupling device 3 comprises an electrical line 4, an assistance drone 6 for supplying the electrical line 4 to the aircraft 2, and a coupling 21 for coupling the electrical line 4 to the aircraft 2. The aircraft 2 has a coupling device for connecting the coupling 21 to the electrical line 4. For example, the coupling device can comprise a socket, and the coupling 21 can comprise a plug.

[0040] The electrical cable 4 is wound up and unwound via an active winding device 10 of the base device 5, depending on the distance between the base device 5 and the aircraft 2. The winding device 10 is arranged on the upper level 15 of the base device 5. A parking space 17 is provided for the assistance drone 6 on the upper level 15. The parking space 17 is mechanically supported by the frame structure 18.

[0041] The propulsion energy storage device 20 of the aircraft 2 can, in particular, be an electrical energy storage device. The propulsion energy storage device 20 can be filled before and / or during the climb. During the climb, the propulsion energy storage device 20 can be supplied with electrical energy via the electrical line 4, which is provided by the electrical energy storage device 13 of the base device 5.

[0042] The energy supplied to the aircraft 2 from the electrical energy storage device 13 can also be provided directly to power the drive 19. The energy supplied to the aircraft 2 from the electrical energy storage device 13 does not need to be stored in the drive energy storage device 20. For example, the aircraft 2 can have drives 19 designed only for climbing flight, which can be supplied with electrical energy exclusively from the electrical energy storage device 13 of the base device 5.

[0043] Alternatively, the aircraft 2 can, for example, have a fuel cell for converting hydrogen into electrical energy. In this embodiment, the base device 5 can supply the hydrogen stored in the balloon 8 as gas 7 to the aircraft 2. This eliminates the need to convert the energy to be supplied to the aircraft 2 into electrical energy. In this example, the drive energy storage device 20 is a hydrogen storage device to which energy in the form of hydrogen can be supplied from the base energy storage device 9 or the balloon 8 via the line 4. The fuel cell of the aircraft 2 converts the hydrogen into electrical energy to drive the drive 19. In this alternative embodiment, the line 4, the coupling 21, and the coupling device of the aircraft 2 are designed to transport hydrogen.

[0044] For example, the propulsion energy storage unit 20 can store approximately 15 kg of hydrogen. Approximately 150 kg of hydrogen are required to lift approximately 2,000 kg of cargo. Thus, the proportion of hydrogen stored in the aircraft 2 accounts for approximately up to 10% of the hydrogen to be stored in the base energy storage unit 9.

[0045] The assistance drone 6 is an electrically powered, vertical takeoff and landing aircraft. The assistance drone 6 is configured to carry or guide the electrical cable 4.

[0046] Fig. 1 also shows a performance assistance device 100, comprising a ground station 101 with a landing area 102, an energy reservoir 103, and the previously described performance assistance system 1. The landing area 102 has sufficient space for landing the base device 5 and for parking one or more aircraft 2, as well as takeoff areas for the beginning of the climb. Located in the area of ​​the ground station 101 is a stationary energy reservoir 102, which includes, for example, accumulators, batteries, and / or storage for the gas 7 of the balloon 8. Furthermore, various service and maintenance units for the balloons 8 and, if necessary, a power supply for the base energy storage unit 9 can be provided.

[0047] The performance assistance system 1 can, for example, be used as part of a mobility service in the area of ​​vertical mobility.

[0048] A performance assistance method for supporting the aircraft 2 advantageously begins with the deployment of the base device 5 at the ground station 101. Initially, the base device 5 is on the ground and the engines 11 are not in use. The base device 5 can be held to the ground by a mechanical holding connection to prevent the base device 5 from climbing due to its lift.

[0049] Subsequently, an electrical connection is established between the aircraft 2 and the base device 5 by means of the electrical line 4.

[0050] The mechanical connection between the base device 5 and the ground is released, and the aircraft 2 and, at the same time, the base device 5 ascend toward a target altitude. The distance between the base device 5 and the aircraft 2 is coordinated by a control system, which can be part of both the ground station 101 and the base device 5. The electrical line 4 is wound up and unwound via the active winding device 10 depending on the distance between the base device 5 and the aircraft 2. The length of the unwound electrical line 4 is intelligently controlled so that the electrical line 4 does not sag excessively and / or rests on the base device 5, in particular the balloon 8. At the same time, the length of the electrical line 4 is dimensioned such that the electrical line 4 is not too taut and thus experiences mechanical stress that inhibits the ascent of the aircraft 2.

[0051] The electrical cable 4 is guided by the assistance drone 6. The assistance drone 6 accompanies the base device 5 during the climb and supports the guidance of the electrical cable 4 and, in particular, the control of the length of the electrical cable 4.

[0052] The electrical line 4, and thus the distance between the base device 5 and the aircraft 2, can be increased with increasing altitude, i.e., the distance of the base device 5 from the ground, and can be maximized, particularly upon arrival at the target altitude. This makes it possible for the aircraft 2 to have a higher vertical flight speed than the base device 4. This can compensate for potential disadvantages of a potentially comparatively slow base device 4.

[0053] The vertical speed of the base device 4 can be controlled, for example, by filling the balloon 8 and by the engines 11 on the upper level 15. A reduction in the buoyancy of the base device 5 can be achieved both by the engines 11 and by removing the gas 7 from the balloon 8. When the gas 7 is removed, an energy converter 12 can be supplied and generate electrical energy. Alternatively, the gas 7 can be released into the environment.

[0054] During the climb, both the electric drive of the aircraft 2 and the propulsion energy storage unit 20 of the aircraft 2 can be supplied or charged. This allows for a longer operating time. It is also conceivable to supply the aircraft 2 with hydrogen, provided the aircraft 2 is powered, for example, by a fuel cell.

[0055] Upon reaching the target altitude, the electrical connection between the aircraft 2 and the base unit 5 is severed. The assistance drone 6 disconnects the power connection from the aircraft 2 or a decoupling mechanism is activated. After the separation, the winding device 10 rolls up the electrical cable 4 in cooperation with the assistance drone 6, which assists in the return of the electrical cable 4. The assistance drone 6 ensures that the electrical cable 4 does not fall onto the base unit 5 and, for example, get caught in its engines 11. The assistance drone then lands on the parking space 17 of the upper level 15.

[0056] The aircraft 2 can now begin horizontal flight, and the base device 5 can land on the ground station 101. Optionally, the aircraft 2 can be received for landing by a base device 5, which assists the aircraft 2 during a descent.

[0057] Fig. 2 shows an embodiment of a performance assistance system 1 with a performance assistance drone as the base device 5. The embodiment according to Fig. 2 is explained with regard to the differences of the embodiment according to Fig. 1. In this example, the base device 5 is not supported by a lift force. The base device 5 has engines 11 configured to lift the base device 5 using electrical energy and to perform a climb. In this exemplary embodiment, the base energy storage device 9 is an electrical energy storage device 13. The base energy storage device 9 must be charged before the base device 5 takes off so that the base energy storage device 9 has sufficient energy for the climb of the base device 5 and for power assistance for the aircraft 2.

[0058] Fig. 3 shows an embodiment of a performance assistance system 1 with a base device 5 and several aircraft 2. The embodiment according to Fig. 3 is explained with regard to the differences of the embodiment according to Fig. 1 described.

[0059] According to the embodiment in Fig. 3, the performance assistance system 1 is configured to provide performance assistance to multiple aircraft 2. For this purpose, the performance assistance system 1 comprises a base device 5 and several assistance drones 6. A parking space is provided for each assistance drone 6.

[0060] To provide performance assistance to multiple aircraft 2, the performance assistance system 1 comprises multiple coupling devices 3. This means that the performance assistance system 1 comprises multiple assistance drones 6, multiple cables 4, multiple couplings 21, and multiple winding devices 10. Each aircraft 2 can thus be assisted in its climb by the base device 5 and by an assistance drone 6. List of reference symbols 1 performance assistance system 2 aircraft 3 Coupling device 4 Line 5 Basic device 6 Assistance drone 7 Gas 8 Balloon 9 Basic energy storage 10 Winding device 11 Engine 12 energy converters 13 electrical energy storage 14 System components 15 upper level 16 lower level 17 parking spaces 18 Frame construction 19 Drive 20 drive energy storage units 21 Clutch 100 performance assistance facility 101 Ground Station 102 landing area 103 Energy reservoir

Claims

[1] Performance assistance system (1) for assisting an electrically driven, vertical take-off and landing capable aircraft (2), wherein the performance assistance system (1) is configured to assist the aircraft (2) during a climb, and wherein the performance assistance system (1) has a coupling device (3) with at least one line (4) for connecting the performance assistance system (1) to the aircraft (2), the performance assistance system (1) comprises a flyable and vertical take-off and landing capable base device (5), and an assistance drone (6), and by means of the coupling device (3), the aircraft (2) can be coupled to the base device (5) by means of the line (4) for the climb and can be decoupled from the base device (5) after the climb, and the assistance drone (6) is configured to carry or guide the line (4). [2] Performance assistance system (1) according to claim 1, characterized bythat the base device (5) comprises a balloon (8) filled with a gas (7) having a lower density than air. [3] Performance assistance system (1) according to one of the preceding claims, characterized by that the base device (5) has a base energy store (9). [4] Performance assistance system (1) according to claim 3, characterized by that the basic energy store (9) is an electrical energy store (13), and electrical energy from the basic energy store (9) can be supplied to the aircraft (2) via the coupling device (3). [5] Performance assistance system (1) according to claims 2 and 3, characterized by that the base device (5) has an energy converter (12) for converting energy stored by the base energy store (9) into electrical energy, wherein the energy store (9) is formed at least partially by the balloon (8). [6] Performance assistance system (1) according to one of the preceding claims, characterized bythat the base device (5) has a winding device (10) for winding up the cable (3). [7] Performance assistance system (1) according to one of the preceding claims, characterized by that the assistance drone (6) is designed to guide the cable (4) for coupling with the aircraft (2). [8] Performance assistance system (1) according to one of the preceding claims, characterized by that the base device (5) has a drive mechanism (11) for horizontally positioning the base device (5). [9] Performance assistance device (100) comprising a performance assistance system (1) according to one of the preceding claims and a ground station (101), wherein the ground station (101) has a landing area (102) for landing the base device (5) and an energy reservoir (103) for storing energy that can be supplied by the base device (5). [10] Performance assistance method for supporting an electrically propelled, vertical take-off and landing aircraft (2), comprising the following steps: - establishing a connection for energy transmission between the aircraft (2) and a base device (5) by means of a line (4), - climb of the aircraft (2) and simultaneous climb of the base device (5), whereby - the line (4) is guided by an assistant drone (6), and - Disconnection between the aircraft (2) and the base device (5) when a target altitude is reached.

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