Method for operating a vertical take-off aircraft, vertical take-off aircraft

Abstract

A method for operating a vertical takeoff aircraft (100) is proposed, wherein the vertical takeoff aircraft (100) is operated in a hover mode or in a cruise mode, wherein the flight is controlled by a pilot via a first input element (1) and a second input element (2), wherein inputs to the first input element (1) and the second input element (2) are converted into flight movements depending on the set mode. Furthermore, a vertical takeoff aircraft (100) is proposed.

Description

[0001] The present invention relates to a method for operating a vertical takeoff aircraft. Furthermore, the present invention relates to a vertical takeoff aircraft.

[0002] Vertical takeoff aircraft are known from the state of the art. Typically, a vertical takeoff aircraft can be operated in at least two modes. These include the operating mode in which the vertical takeoff aircraft is launched and the mode in which the vertical takeoff aircraft is typically landed, namely the so-called hover mode. Lift in hover mode is usually generated by downward-facing engines, such as jet engines or propellers.

[0003] For fast forward flight, the vertical takeoff aircraft is typically switched to a so-called cruise mode. In this cruise mode, lift is usually generated aerodynamically by an airflow along the wings. The thrust required for this is provided by rear-facing engines, such as jet engines or propellers.

[0004] In terms of controlling the vertical takeoff aircraft, the two modes mentioned are completely different. For example, the direction of thrust must be adjusted for forward, backward, or sideways movement in hover mode. This can be achieved by pivoting the engines or by pivoting the air control elements on the engines. When changing direction in cruise mode, however, one or more control surfaces on the aerodynamically effective wings are adjusted.

[0005] This represents a major challenge for the pilot, who must be able to operate the aircraft safely in vertical take-off mode, particularly when transitioning between different operating modes.

[0006] An object of the present invention is therefore to provide a method for operating a vertical take-off aircraft and a vertical take-off aircraft which do not have the described disadvantages of the prior art, but enable safe operation of the vertical take-off aircraft.

[0007] This object is achieved by a method for operating a vertical take-off aircraft according to claim 1 and a vertical take-off aircraft according to claim 13.

[0008] The method according to the invention provides that the vertical take-off aircraft is operated in a hover mode or in a cruise mode. The flight of the vertical take-off aircraft is controlled by the pilot of the vertical take-off aircraft using a first input element and a second input element. The inputs to the first input element and the second input element are converted into flight movements depending on the selected mode. This advantageously makes it possible to configure the control system depending on the flight requirements such that the pilot can operate the vertical take-off aircraft highly intuitively. This means that the pilot does not have to concentrate on which input causes which reaction of the vertical take-off aircraft, but can devote his full attention to the flight itself.

[0009] Advantageous embodiments and further features of the invention can be found in the subclaims and the description with reference to the drawings.

[0010] According to a preferred embodiment of the present invention, the vertical takeoff aircraft can be operated in hover mode, cruise mode, or manual cruise mode. The ability to distinguish between hover mode and cruise mode allows optimization of the vertical takeoff aircraft for the respective situation.

[0011] A hover mode within the meaning of the present invention is an operating mode of the vertical take-off aircraft in which the lift is generated substantially by downward air currents generated directly by engines. The cruise mode within the meaning of the present invention is an operating mode of the vertical take-off aircraft in which the lift is generated substantially by aerodynamic action on wings. Preferably, the cruise mode is a partially assisted mode with regard to the control of the vertical take-off aircraft, in which inputs for controlling the vertical take-off aircraft not only cause changes in the position of individual elements of the vertical take-off aircraft, but are converted into a combination of changes in the position of several elements of the vertical take-off aircraft during the control inputs.A manual cruise flight mode within the meaning of the present invention is a cruise flight mode in which the control logic of the vertical takeoff aircraft does not intervene in a supportive manner. It is otherwise characterized in that the modes can be switched using an additional input element. This makes it possible to advantageously actively set the desired mode and thus the desired flight behavior. It is conceivable, for example, that the additional input element comprises a switch or is a switch. However, it is also conceivable that the additional input element is, for example, a rotary control.

[0012] According to a further preferred embodiment of the present invention, switching the conversion of the inputs at the first input element and the second input element occurs automatically when the mode is changed. This ensures that the pilot is relieved of work and can concentrate on controlling the vertical takeoff aircraft itself.

[0013] For this purpose, it is advantageous that the switching of the input conversion between the first input element and a second input element takes place smoothly. This advantageously further simplifies the operation of the vertical takeoff aircraft and ensures a comfortable flight and trouble-free flight control.

[0014] According to a further preferred embodiment of the present invention, it is provided that in hover mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a forward or backward movement of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a sideways movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotation about the vertical axis of the vertical take-off aircraft is controlled by a rotation of the first input element; in cruise mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a turn to the left or right of the vertically take-off aircraft is controlled by a sideways movement of the second input element, in manual cruise mode preferably a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a roll movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotational movement about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element.

[0015] The control concept according to this particularly preferred embodiment is highly intuitive and facilitates the control of the vertical take-off aircraft, in particular when transitioning between the different modes of the vertical take-off aircraft.

[0016] According to a further preferred embodiment of the present invention, it is provided that in hover mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a forward or backward movement of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a sideways movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotation about the vertical axis of the vertically take-off aircraft is controlled by a sideways movement of the first input element, where in cruise mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a turn to the left or right of the vertically take-off aircraft is controlled by a sideways movement of the second input element, In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a roll movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotational movement about the vertical axis of the vertically take-off aircraft is controlled by a sideways movement of the first input element.

[0017] The control concept according to this particularly preferred embodiment is also highly intuitive and facilitates the control of the vertical take-off aircraft, in particular when transitioning between the different modes of the vertical take-off aircraft.

[0018] According to a further preferred embodiment of the present invention, it is provided that in hover mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a forward or backward movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a sideways movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotation about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element, where in cruise mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a turn to the left or right of the vertically take-off aircraft is controlled by a sideways movement of the second input element, In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a roll movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotational movement about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element.

[0019] The control concept according to this particularly preferred embodiment is also highly intuitive and facilitates the control of the vertical takeoff aircraft, especially when transitioning between the different modes of the vertical takeoff aircraft. The control concept advantageously combines the different modes, allowing the pilot's undivided attention to be focused on the flight itself.

[0020] According to a further preferred embodiment of the present invention, it is provided that in hover mode a vertical movement of the vertically take-off aircraft is controlled by a rotary movement of a third input element, a forward or backward movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a sideways movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotation about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element, where in cruise mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a turn to the left or right of the vertically take-off aircraft is controlled by a sideways movement of the second input element, In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a roll movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotational movement about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element.

[0021] The control concept according to this particularly preferred embodiment is also a highly intuitive alternative and facilitates the control of the vertical takeoff aircraft, especially when transitioning between the different modes of the vertical takeoff aircraft. The control concept advantageously combines the different modes, allowing the pilot's undivided attention to be focused on the flight itself.

[0022] According to a further preferred embodiment of the present invention, it is provided that in hover mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a forward or backward movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a sideways movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotation about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the second input element, where in cruise mode a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a turn to the left or right of the vertically take-off aircraft is controlled by a sideways movement of the second input element, In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft is controlled by a forward or backward movement of the second input element, a speed in the forward direction of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element, a roll movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element and a rotational movement about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element.

[0023] The control concept according to this particularly preferred embodiment is also a highly intuitive alternative and facilitates the control of the vertical takeoff aircraft, especially when transitioning between the different modes of the vertical takeoff aircraft. The control concept advantageously combines the different modes, allowing the pilot's undivided attention to be focused on the flight itself.

[0024] According to a particularly preferred embodiment of the present invention, it is provided that the input to the first input element comprises a deflection from a neutral position of the first input element into a deflected position, wherein a flight parameter changed by the input to the first input element is retained when the deflection is reversed and thus a return to the neutral position is effected, and / or characterized in that the input to the second input element comprises a deflection from a neutral position of the second input element, wherein a flight parameter changed by the input to the second input element is retained when the deflection is reversed and a return to the neutral position thus occurs. This allows inputs to the input elements to advantageously be assigned to changes in the flight movement. If the flight movement is not to be changed, the input elements simply remain in the neutral position.

[0025] According to a further preferred embodiment of the present invention, the first input element comprises a control lever and / or the second input element comprises another control lever and / or the third input element preferably comprises a rotary wheel, in particular a thumbwheel. This advantageously enables both experienced and less experienced pilots to perform the inputs on the input elements sensitively, in a well-measured manner, and easily.

[0026] A further object of the present invention for solving the problem formulated at the outset is a vertical take-off aircraft, wherein the vertical take-off aircraft is configured to carry out a method according to the invention.

[0027] All details, features and advantages disclosed above in the context of the method according to the invention for operating the vertical take-off aircraft relate equally to the vertical take-off aircraft according to the invention.

[0028] Further details, features, and advantages of the invention will become apparent from the drawings and the following description of preferred embodiments with reference to the drawings. The drawings merely represent exemplary embodiments of the invention, which do not limit the scope of the invention. Fig. 1 schematically shows a vertical takeoff aircraft according to an exemplary embodiment of the present invention. Fig. 2 (a) and (b) show a schematic plan view of a vertical take-off aircraft according to an exemplary embodiment of the present invention, which performs a method according to an exemplary embodiment of the present invention during flight.

[0029] Fig. 1 schematically shows a vertical takeoff aircraft 100 according to an exemplary embodiment of the present invention. The vertical takeoff aircraft 100 is an electric vertical takeoff aircraft 100, i.e., the vertical takeoff aircraft 100 has electrically powered units for generating thrust. In particular, it is provided that the electrically powered units for generating thrust are powered by a battery.

[0030] The vertical takeoff aircraft 100 can be operated in various operating modes. For example, it is possible to operate the vertical takeoff aircraft 100 in a hover mode, in which lift is generated by downward thrust generated by the thrust-generating units. These units can be, for example, jet engines or propeller engines. In hover mode, it is possible to keep the vertical takeoff aircraft 100 in one place with respect to its position above the ground. It is also possible, for example, for the vertical takeoff aircraft 100 to move backward.

[0031] A cruise mode of the vertical takeoff aircraft 100 is intended for cruising, i.e., for comfortably covering longer distances at high speed. In this cruise mode, the lift of the vertical takeoff aircraft 100 is generated by aerodynamically effective wings. The thrust generation units only provide thrust in the forward direction X.

[0032] Cruise mode is at least partially supported, so that complex control tasks, such as adjusting different flaps to achieve a specific flight movement, are coordinated by an onboard computer. However, the vertical takeoff aircraft 100 can also be operated in a manual cruise mode, in which the flaps, at least divided into groups of flaps, are controlled directly.

[0033] Fig. Figure 1 shows input elements 1, 2, 3 used to control the flight movements of the vertical takeoff aircraft 100. The inputs to the input elements 1, 2, 3 are converted into flight movements depending on the mode in which the vertical takeoff aircraft 100 is operated. The different modes are set using another input element 4.

[0034] The vertical takeoff aircraft 100 has control logic that allows the pilot to control the vertical takeoff aircraft 100 entirely intuitively, even when switching between different modes. It is contemplated that, in hover mode, a vertical movement of the vertical takeoff aircraft 100 is controlled by a forward or backward movement of a second input element 2, a forward X or backward movement of the vertical takeoff aircraft 100 is controlled by a forward or backward movement of the first input element 1, a sideways Y movement of the vertical takeoff aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotation about the vertical axis of the vertical takeoff aircraft 100 is controlled by a rotation of the first input element 1.In cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element, a left or right turn of the vertical take-off aircraft is controlled by a sideways movement of the second input element.In manual cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 2, a rolling movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotational movement about the vertical axis of the vertical take-off aircraft 100 is controlled by a rotational movement of the first input element 1.

[0035] Alternatively, in hover mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of a second input element 2, a forward X or backward movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a sideways Y movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotation about the vertical axis of the vertical take-off aircraft 100 is controlled by a sideways movement of the first input element.In cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element 1, a left or right turn of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2.In manual cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a rolling movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotational movement about the vertical axis of the vertical take-off aircraft 100 is controlled by a sideways movement of the first input element.

[0036] Alternatively, in hover mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of a first input element 1, a forward X or backward movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a sideways Y movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotation about the vertical axis of the vertical take-off aircraft is controlled by a rotational movement of the first input element 1.In cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a left or right turn of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2.In manual cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a roll movement of the vertical take-off aircraft is controlled by a sideways movement of the second input element 2, and a rotational movement about the vertical axis of the vertical take-off aircraft 100 is controlled by a rotational movement of the first input element 1.

[0037] Alternatively, in hover mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a rotational movement of a third input element 3, a forward-X or backward movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a sideways movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotation about the vertical axis of the vertical take-off aircraft 100 is controlled by a rotational movement of the first input element 1.In cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a turn to the left or right of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2.In manual cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft is controlled by a forward or backward movement of the first input element 1, a rolling movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element, and a rotational movement about the vertical axis of the vertical take-off aircraft 100 is controlled by a rotational movement of the first input element 1.

[0038] Alternatively, in hover mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of a first input element 1, a forward X or backward movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a sideways Y movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotation about the vertical axis of the vertical take-off aircraft 100 is controlled by a rotational movement of the second input element 2.In cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a left or right turn of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2.In manual cruise mode, a vertical movement of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the second input element 2, a speed in the forward direction X of the vertical take-off aircraft 100 is controlled by a forward or backward movement of the first input element 1, a rolling movement of the vertical take-off aircraft 100 is controlled by a sideways movement of the second input element 2, and a rotational movement about the vertical axis of the vertical take-off aircraft 100 is controlled by a rotational movement of the first input element 1.

[0039] The inputs to input elements 1, 2, and 3 involve a deflection of the respective input element from a neutral position. A flight parameter changed by the input to input element 1, 2, and 3 remains unchanged if the deflection is reversed, thus causing a return to the neutral position.

[0040] This is in Fig.2 (a) and (b) are shown as an example of the control of the vertical take-off aircraft 100 in cruise mode (Figure (a)) and in hover mode (Figure (b)). In hover mode, the deflection of the second input element 2 causes a lateral movement of the vertical take-off aircraft 100. The further the second input element 2 is deflected, the faster the lateral movement of the vertical take-off aircraft 100. When the deflection of the second input element 2 is terminated, the second input element 2 returns to its neutral position and the lateral movement of the vertical take-off aircraft 100 is terminated. In cruise mode, a turn is initiated by a lateral deflection of the second input element 2. The greater the deflection of the second input element 2 is selected, the tighter the turn is flown.If the deflection of the second input element 2 is terminated and the second input element 2 returns to its neutral position, the curved flight is terminated with a subsequent straight flight.

Claims

[1] Method for operating a vertical take-off aircraft (100), wherein the vertical take-off aircraft (100) is operated in a hover mode or in a cruise flight mode, wherein the flight is controlled by a pilot via a first input element (1) and a second input element (2), wherein inputs to the first input element (1) and to the second input element (2) are converted into flight movements depending on the set mode. [2] Method according to claim 1, characterized by that the vertical take-off aircraft (100) can be operated in hover mode or in cruise mode or in a manual cruise mode. [3] Method according to one of the preceding claims, characterized by that the modes can be switched by means of another input element (4). [4] Method according to one of the preceding claims, characterized bythat the switching of the conversion of the inputs at the first input element (1) and at the second input element (2) occurs automatically when the mode is changed. [5] Method according to claim 4, characterized by that the switching of the conversion of the inputs at the first input element (1) and at the second input element (2) takes place smoothly. [6] Method according to one of the preceding claims, characterized by , that in hover mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a forward (X) or backward movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a sideways (Y) movement of the vertical take-off aircraft (100) is controlled by a sideways movement of the second input element (2) and a rotation about the vertical axis of the vertically take-off aircraft (100) is controlled by a rotation of the first input element (1), wherein in travel mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a turn to the left or right of the vertically take-off aircraft (100) is controlled by a sideways movement of the second input element (2), In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a rolling movement of the vertical take-off aircraft (100) is controlled by a lateral movement of the second input element (2) and a rotational movement about the vertical axis of a vertical take-off aircraft (100) is controlled by a rotational movement of the first input element (1). [7] Method according to one of claims 1 to 5, characterized by that in hover mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a forward (X) or backward movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a sideways (Y) movement of the vertical take-off aircraft (100) is controlled by a sideways movement of the second input element (2) and a rotation about the vertical axis of the vertically take-off aircraft (100) is controlled by a lateral movement of the first input element (1), where in travel mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a turn to the left or right of the vertically take-off aircraft (100) is controlled by a sideways movement of the second input element (2), In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a rolling movement of the vertical take-off aircraft (100) is controlled by a lateral movement of the second input element (2) and a rotational movement about the vertical axis of the vertical take-off aircraft (100) is controlled by a lateral movement of the first input element (1). [8] Method according to one of claims 1 to 5, characterized by that in hover mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a forward (X) or backward movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a sideways (Y) movement of the vertical take-off aircraft (100) is controlled by a sideways movement of the second input element (2) and a rotation about the vertical axis of the vertical take-off aircraft (100) is controlled by a rotational movement of the first input element (1), where in travel mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a turn to the left or right of the vertically take-off aircraft (100) is controlled by a sideways movement of the second input element (2), In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a rolling movement of the vertical take-off aircraft (100) is controlled by a lateral movement of the second input element (2) and a rotational movement about the vertical axis of the vertical take-off aircraft (100) is controlled by a rotational movement of the first input element (1). [9] Method according to one of claims 1 to 5, characterized by that in hover mode a vertical movement of the vertically take-off aircraft (100) is controlled by a rotational movement of a third input element (3), a forward (X) or backward movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a sideways (Y) movement of the vertical take-off aircraft (100) is controlled by a sideways movement of the second input element (2) and a rotation about the vertical axis of the vertical take-off aircraft (100) is controlled by a rotational movement of the first input element (1), where in travel mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a turn to the left or right of the vertically take-off aircraft (100) is controlled by a sideways movement of the second input element (2), In manual cruise mode, preferably a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a rolling movement of the vertical take-off aircraft (100) is controlled by a lateral movement of the second input element (2) and a rotational movement about the vertical axis of the vertical take-off aircraft (100) is controlled by a rotational movement of the first input element (1). [10] Method according to one of claims 1 to 5, characterized by that in hover mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a forward (X) or backward movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a sideways (Y) movement of the vertical take-off aircraft (100) is controlled by a sideways movement of the second input element (2) and a rotation about the vertical axis of the vertical take-off aircraft (100) is controlled by a rotational movement of the second input element (2), where in travel mode a vertical movement of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a turn to the left or right of the vertically take-off aircraft (100) is controlled by a sideways movement (Y) of the second input element (2), wherein in the manual cruise mode, a vertical movement of the vertically take-off aircraft (100) is preferably controlled by a forward or backward movement of the second input element (2), a speed in the forward direction (X) of the vertical take-off aircraft (100) is controlled by a forward or backward movement of the first input element (1), a rolling movement of the vertical take-off aircraft (100) is controlled by a lateral movement of the second input element (2) and a rotational movement about the vertical axis of the vertical take-off aircraft (100) is controlled by a rotational movement of the first input element (1). [11] Method according to one of the preceding claims, characterized bythat the input to the first input element (1) comprises a deflection from a neutral position of the first input element (1) into a deflected position, wherein a flight parameter changed by the input to the first input element (1) is retained when the deflection is reversed and thus a return to the neutral position is effected, and / or characterized by that the input to the second input element (2) comprises a deflection from a neutral position of the second input element (2), wherein a flight parameter changed by the input to the second input element (2) is retained when the deflection is reversed and thus a return to the neutral position occurs. [12] Method according to one of the preceding claims, characterized bythat the first input element (1) comprises a control lever and / or the second input element (2) comprises a further control lever and / or the third input element (3) preferably comprises a rotary wheel, in particular a thumb wheel. [13] Vertical take-off aircraft (100), characterized by that the vertical take-off aircraft (100) is configured to carry out a method according to one of the preceding claims.

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