Flight control system for an aircraft
Patent Information
- Application Number
- PCT/EP2026/053651
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2025-02-26
- Filing Date
- 2026-02-11
- Publication Date
- 2026-09-03
Smart Images
Figure EP2026053651_03092026_PF_FP_ABST
Abstract
Description
[0001] Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0002] Flight control system for an aircraft
[0003] Technical field
[0004] The present invention relates to a flight control system for an aircraft controlled by a single pilot. The flight control system according to the invention comprises a primary control device, a secondary control device, a thrust control device, and an alternative thrust control device, wherein all devices are designed and arranged such that the devices are functionally independent of one another and / or spatially separated from one another.
[0005] The invention further relates to an aircraft with such a flight control system.
[0006] State of the art
[0007] Various flight control systems for aircraft are known from the state of the art.
[0008] In fixed-wing aircraft, roll and pitch movements are typically controlled via a control stick or rudder. Yaw movements are usually controlled by pedals. The power output of the aircraft's propulsion system(s) is generally controlled by a throttle. The pilot operates the control stick or rudder with one hand and the throttle with the other. The pedals are operated by the pilot's feet. The control stick, throttle, and pedals together form the flight control system of the fixed-wing aircraft.
[0009] Rotary-wing aircraft (aircraft with at least one lift-generating rotor driven by a propulsion device) typically use a "Collective Heave Inceptor" instead of a thrust lever. The "Collective Heave Inceptor" not only controls the power output of the propulsion device, which is related to the rotational speed of the rotor, but also... (Volocopter Technologies GmbH 11.02.2026 FC24007-WO)
[0010] The rotor's speed is correlated with and controlled by the "Collective Heave Inceptor." Furthermore, the angle of attack of the rotor blades can also be changed using this system. This results in the rotor generating more or less lift at a constant rotational speed.
[0011] It is also known in the prior art to implement the aforementioned flight control systems as so-called "fly-by-wire" flight control systems. In this case, the connection between the flight control system and the aircraft's control surfaces or propulsion system is not mechanical, but electronic. This means that the pilot's control inputs are detected by the flight control system, particularly by sensors within the system, and then output as an electrical control signal. These control signals are then further processed within the aircraft and implemented accordingly by the control surfaces and / or propulsion system or rotors.
[0012] Civil aircraft intended for passenger transport must meet stringent regulatory safety requirements. One of these requirements is that an appropriate level of fail-safety, or a very low probability of failure, must be ensured with regard to the flight control system. This requirement is met in the prior art by ensuring that known aircraft are always controllable by two pilots, each with their own independent flight control system. This means that each pilot has their own control device, allowing them to operate the aircraft independently of the other pilot. This ensures that in the event of a mechanical or other failure, the aircraft can be safely flown without interference.In the event of an electro-mechanical failure of the control device of one pilot, the other pilot can take over the control of the aircraft using his control device.
[0013] However, some aircraft, particularly electrically powered aircraft capable of vertical takeoff and landing (eVTOL), require that the aircraft be piloted by a single operator. This allows for the transport of at least one additional passenger and / or more payload, eliminating the need for a second operator and redundant flight control system. Nevertheless, even in such single-pilot aircraft, the following requirements must be met: Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0014] high regulatory safety requirements, analogous to those of large civilian aircraft, are met.
[0015] There is therefore a need for a flight control system that meets the high regulatory safety requirements for flight control systems and that can be operated by a single pilot without the pilot being mentally and physically overloaded by the flight control system.
[0016] Description of the invention
[0017] It is therefore an object of the present invention to satisfy the aforementioned needs. In particular, it is an object of the present invention to provide a flight control system and / or an aircraft with a flight control system with which a single pilot can control the aircraft as easily as possible, wherein the flight control system has a minimal probability of failure with regard to functionality.
[0018] This problem is solved by a flight control system according to claim 1. Advantageous further developments of the flight control system according to the invention are the subject of the dependent claims and / or are explained in the following description.
[0019] According to the invention, a flight control system is proposed that is designed for use in an aircraft, in particular for use in an eVTOL aircraft. The flight control system can be operated by a single pilot and comprises a primary control device, a secondary control device, a thrust control device, and an alternative thrust control device. Simultaneously, the flight control system according to the invention is designed to be operated in a primary control mode, a first alternative control mode, and a second alternative control mode.
[0020] Preferably, the flight control system is configured to automatically switch between the main control mode, the first alternative control mode, and / or the second alternative control mode. For example, the flight control system can be configured to detect a fault in the primary control device and then automatically switch between the primary and alternative control modes. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0021] to switch from the main control mode to the first alternative control mode. Alternatively or additionally, the flight control system may have an input device, in particular a button, for the pilot to manually change the control mode. For example, the flight control system may be configured so that the pilot, by pressing the input device, effects a change from the main control mode to the first alternative control mode and / or to the second alternative control mode (and vice versa).
[0022] The primary control device, in the main control mode of the flight control system, is designed to detect a control input from the pilot. Based on the detected control input, the primary control device outputs a corresponding roll control signal, a pitch control signal, and a yaw control signal. The primary control device can, for example, be a control stick that is movable around at least three axes.
[0023] For the purposes of this invention, the term "roll control signal" refers to a signal whose processing or use by the aircraft directly or indirectly leads to a roll movement of the aircraft corresponding to the roll control signal. A "roll movement" of the aircraft refers in particular to a rotation of the aircraft about its longitudinal axis, which is also commonly referred to as the roll axis. A roll movement of the aircraft, in particular, causes a change in the aircraft's roll angle.
[0024] For the purposes of this invention, the term "pitch control signal" refers to a signal whose processing or use by the aircraft directly or indirectly leads to a pitching movement of the aircraft corresponding to the pitch control signal. A "pitch movement" of the aircraft refers in particular to a rotation of the aircraft about its transverse axis, which is also commonly referred to as the pitch axis. A pitch movement of the aircraft, in particular, causes a change in the aircraft's pitch angle.
[0025] For the purposes of this invention, the term "yaw control signal" refers to a signal whose processing or use by the aircraft directly or indirectly leads to a yaw movement of the aircraft corresponding to the yaw control signal. A "yaw movement" of the aircraft refers in particular to a rotation of the aircraft about its vertical axis, which is also commonly referred to as the yaw axis. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0026] A yaw movement of the aircraft causes, in particular, a change in the yaw angle of the aircraft.
[0027] The secondary control device is functionally independent of the primary control device and spatially separated from it. This ensures, in particular, that the secondary control device is not affected by a mechanical and / or electromechanical failure of the primary control device. Preferably, the secondary control device is arranged relative to the primary control device such that the pilot can reach it with the same hand by simply transferring their hand from the primary to the secondary control device. In other words, the secondary control device can be, for example, spaced between 15 cm and 80 cm away from the primary control device.
[0028] In the first alternative control mode of the flight control system, the secondary control device is configured to take over the functionality of the primary control device. This means that in the first alternative control mode, the secondary control device is configured to detect a control input from the pilot, particularly when the pilot has switched from the primary to the secondary control device. Based on the detected control input, the secondary control device outputs a corresponding roll control signal, pitch control signal, and yaw control signal. The secondary control device could, for example, be a control stick that is movable around at least three axes.
[0029] The thrust control device is functionally independent of the primary and secondary control devices. This ensures, in particular, that the thrust control device is not affected by a mechanical and / or electromechanical failure of the primary and / or secondary control devices. The thrust control device can be spatially separated from the primary and secondary control devices. In the main control mode of the flight control system, the thrust control device is configured to detect a control input from the pilot and, based on the detected control input, output a corresponding thrust control signal. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0030] For the purposes of this invention, the term "thrust control signal" refers to a signal whose processing or use by the aircraft leads directly or indirectly to a change in the power output of the aircraft's lift- and / or thrust-generating propulsion devices that corresponds to the thrust control signal. For example, a thrust control signal can be generated based on a movement of the thrust control device, leading to an increase or a reduction in the power output of the propulsion devices.
[0031] According to the invention, an alternative thrust control device is arranged on the primary or secondary control device. The alternative thrust control device is preferably arranged on the primary or secondary control device such that the pilot can operate the primary or secondary control device simultaneously with the alternative thrust control device. Preferably, the pilot can operate the primary control device and the alternative thrust control device with a single hand if the alternative thrust control device is provided on the primary control device. If the alternative thrust control device is provided on the secondary control device, the pilot can operate the secondary control device and the alternative thrust control device with a single hand.
[0032] The alternative thrust control device is functionally independent of the thrust control device, the primary control device, and the secondary control device. This ensures, in particular, that the alternative thrust control device is not affected by a mechanical and / or electromechanical failure of the thrust control device, the primary control device, and / or the secondary control device. In a second alternative control mode, the alternative thrust control device is configured to take over the functionality of the thrust control device, especially when the pilot has switched from the thrust control device to the alternative thrust control device. This means that, in the main control mode of the flight control system, the alternative thrust control device is configured to detect a pilot input and output a corresponding thrust control signal based on the detected input.Volocopter Technologies GmbH 11.02.2026 FC24007-WO.
[0033] The flight control system according to the invention advantageously ensures that all devices are operable by the pilot and that the pilot can easily and immediately switch from a primary device (primary control device, thrust control) to a secondary device (secondary control device, alternative thrust control) if a malfunction occurs in one of the primary devices. The first and second alternative control modes advantageously each constitute an operating mode in which the pilot controls the aircraft via partial redundancy. Consequently, the pilot has the option of switching to the secondary device for only one of the two primary devices without affecting the control capability of the other primary device.The flight control system according to the invention has the advantage that a single pilot can control the aircraft with maximum reliability.
[0034] In a beneficial further development, the flight control system can be operated in a third alternative control mode. Preferably, the flight control system is designed such that in this third alternative control mode, the aircraft is controlled exclusively via the secondary control device and the alternative thrust control device. In other words, the pilot can control the aircraft in this third alternative control mode solely via the secondary devices. This would be the case, for example, if all primary devices have a mechanical and / or electromechanical defect.
[0035] The third alternative control mode can advantageously enable the flight control system to operate in full redundancy in addition to the two partial redundancy modes. This can further reduce the probability of flight control system failure.
[0036] In another exemplary embodiment, the flight control system can include a display. The display can be, for example, a screen, a monitor, or a touchpad, preferably located in the aircraft cockpit. The display can be configured to show the pilot in which control mode the flight control system is operating. This means that the display provides the pilot with information, in particular, about whether the flight control system is in main control mode.
[0037] control mode, in the first alternative control mode, in the second alternative control mode or in the third alternative control mode.
[0038] The display advantageously allows the pilot to quickly and easily understand the operating mode of the flight control system and to control the aircraft accordingly using the currently active controls. This can further simplify aircraft control and prevent incorrect control inputs via inactive controls.
[0039] In another exemplary embodiment of the flight control system, the primary control device and the secondary control device each have a handle and a base. The handle can be movable relative to the base.
[0040] The base can be designed as a static base for the handle. This means that the base is fixed to the aircraft, particularly its structure. Alternatively or additionally, electronic components of the respective control device can be arranged within the base. These electronic components can, for example, be designed to detect movements of the handle relative to the base.
[0041] The handle is advantageously designed so that it can be grasped by the pilot, particularly with one hand. The handle may have an ergonomic shape that facilitates one-handed grasping. For example, the handle may have ergonomically shaped recesses for the pilot's fingers.
[0042] The handle can be rotatable relative to the base – that is, it can be rotated. For example, the handle can be rotated about a vertical axis of the respective control device. When the handle is rotated about the vertical axis, particularly by the pilot, the respective control device is configured to output the yaw control signal.
[0043] Additionally or alternatively, the handle can be movable about a transverse axis, in particular about the base. The transverse axis is preferably Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0044] oriented orthogonally to the aforementioned vertical axis. If the handle is moved around the lateral axis, in particular by the pilot, the respective control device may be designed to output the pitch control signal.
[0045] Additionally or alternatively, the handle may be movable about a longitudinal axis, in particular about the longitudinal axis relative to the base. The longitudinal axis may be oriented orthogonally to the aforementioned vertical axis and orthogonally to the aforementioned transverse axis. In other words, each of the aforementioned axes may be oriented orthogonally to the other axes. When the handle is moved about the longitudinal axis, in particular by the pilot, the respective control device may be configured to output the roll control signal.
[0046] The handle is advantageously rotatable or movable around the other axes independently of any rotation around the vertical axis, any movement around the transverse axis and / or any movement around the longitudinal axis.
[0047] If the primary and secondary control devices have a movable handle and are therefore identical in design, this can advantageously enable the pilot to control the aircraft's attitude with a single hand movement. When switching from the primary to the secondary control device, particularly when the flight control system changes from the main control mode to the first alternative control mode, the pilot experiences the same control feel with the secondary device as with the primary control device. This eliminates the need for the pilot to relearn or adapt. This has the advantage that the pilot can control the aircraft safely and easily, particularly with one hand, using both the primary and secondary control devices.
[0048] In an exemplary further development of the aforementioned embodiment, a finger input device is arranged on the handle of the primary control device. Preferably, the finger input device is movable relative to the handle. For example, the finger input device can be translationally displaceable relative to the handle and / or rotatable about a pivot axis. The finger input device can be ergonomically arranged on the handle such that the finger input device can be operated by means of Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0049] can be operated by the pilot's thumb, in particular by means of the thumb of the hand with which the pilot also operates the handle.
[0050] The finger input device can be the alternative thrust control device. For example, the finger input device can be inactive in the primary control mode. In the second alternative control mode, the finger input device can act as the alternative thrust control device, so that the thrust control signal corresponds to a control input from the pilot at the finger input device. For example, the flight control system can be designed and positioned relative to the pilot such that the pilot can control the aircraft with a single hand in the second alternative control mode.
[0051] In an alternative embodiment, the finger input device can be the thrust control device. For example, in the main control mode, the finger input device can act as the thrust control device, so that the thrust control signal corresponds to a control input from the pilot at the finger input device. In the second alternative control mode, the finger input device can be inactive.
[0052] The finger input device on the handle of the primary control device can advantageously enable the pilot to control the aircraft's attitude with a movement of his hand and the power output of the aircraft's propulsion system with a finger of the same hand. This has the advantage that the pilot can control the aircraft safely and easily with the flight control system, particularly with one hand.
[0053] In another exemplary embodiment of the flight control system, the thrust control device is spatially separated from the primary control device and the secondary control device.
[0054] Preferably, the thrust control device is spaced apart from the primary control device such that the pilot can operate the thrust control device with one hand, particularly the left hand, and the primary control device with the other hand, particularly the right hand. Such a configuration is particularly advantageous when the flight control system is operating in main control mode. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0055] The thrust control device can be spaced apart from the secondary control device in such a way that the thrust control device can be operated with one hand of the pilot, in particular the left hand, and the secondary control device with the other hand, in particular the right hand. Such a configuration is particularly advantageous when the flight control system is operating in the first alternative control mode.
[0056] For the second alternative control mode, it is advantageous if the finger input device on the handle of the primary control device is designed as an alternative thrust control device. This can, for example, allow the pilot to switch to the finger input device on the handle of the primary control device to regulate or control the aircraft's thrust in the event of a mechanical and / or electromechanical failure of the thrust control device.
[0057] In a further development of the aforementioned embodiments, the thrust control device comprises a thrust lever base and a thrust lever. The thrust lever can be movable, in particular pivotable, relative to the thrust lever base. Advantageously, the thrust control signal, in particular the thrust control signal output by the thrust control device, correlates with the position of the thrust lever relative to the thrust lever base.
[0058] A thrust control device according to the aforementioned embodiments and / or according to the further development of the aforementioned embodiment can advantageously ensure that the thrust control device is particularly easy and intuitive to operate by the aircraft pilot.
[0059] In an alternative embodiment, a finger input device can be arranged on both the handle of the primary control device and the handle of the secondary control device. Advantageously, the finger input device on the handle of the primary control device is then designed as a thrust control device. The finger input device on the handle of the secondary control device can be designed as an alternative thrust control device.
[0060] In the aforementioned embodiment, the pilot can control the aircraft in the main control mode of the flight control system using a single hand via the primary control device and the finger input device on the primary control device. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0061] Alternatively, and particularly in the third alternative control mode of the flight control system, the pilot can control the aircraft using a single hand via the secondary control device and the finger input device on the secondary control device.
[0062] Such an embodiment can advantageously enable the aircraft to be controlled by the pilot with one hand in both the primary control mode and the third alternative control mode. This can have the advantage of making the flight control system particularly easy and intuitive for the pilot to operate the aircraft.
[0063] If one-handed control of the aircraft by the pilot is not desired, the finger input device on the handle of the primary control device can be the alternative thrust control device in an alternative embodiment of the flight control system. The finger input device on the handle of the secondary control device can be the thrust control device.
[0064] In the aforementioned embodiment, the pilot can operate the primary control device with one hand, for example, the right hand, while the flight control system is in main control mode. With the other hand, in particular the thumb of the left hand, the pilot can operate the finger input device on the handle of the secondary control device.
[0065] In a further exemplary embodiment, the primary control device and / or the secondary control device, preferably the handle of the primary control device and / or the secondary control device, may include a further input device. Preferably, the primary control device and / or the secondary control device is configured to output a further control signal, in particular one independent of the aforementioned control signals, when the further input device is actuated by the aircraft pilot.
[0066] The additional control signal could, for example, be a radio control signal designed to activate and / or deactivate the pilot's radio communication system. Alternatively or additionally, the additional control signal could, for example, be an autopilot control signal designed to... (Volocopter Technologies GmbH 11.02.2026 FC24007-WO)
[0067] To activate and / or deactivate the aircraft's autopilot mode. It is also conceivable that the additional control signal could be, for example, a pitch angle and / or airspeed hold signal. The pitch angle and / or airspeed hold signal can cause the current pitch angle and / or airspeed of the aircraft to be maintained even when the handle is returned to its neutral position.
[0068] The additional input device can be a separate switch and / or button on the handle. Alternatively or additionally, the additional input device can also be part of the finger input device. For example, the finger input device can be a rotary dial that rotates around the axis of rotation, with the rotary dial also functioning as a push button. When the pilot rotates the rotary dial around the axis of rotation, the corresponding control device can be configured to output the thrust control signal. When the pilot presses the rotary dial, particularly when pressing it into the handle, the control device can be configured to output the additional control signal, such as the radio control signal, the autopilot control signal, or the pitch angle and / or airspeed hold signal.
[0069] A primary and / or secondary control device with an additional input device can advantageously enable the pilot to make further control inputs using the primary and / or secondary control device. This can further simplify the control of the aircraft with the flight control system.
[0070] The problem stated at the outset of the invention is also solved with an aircraft according to claim 10. Advantageous further developments of the aircraft according to the invention are explained in the following description.
[0071] According to the invention, an aircraft is proposed comprising several propulsion devices, a flight control system according to the aforementioned embodiments, and a flight control computer. The aircraft can, in particular, be electrically powered, preferably exclusively electrically powered. The aircraft is preferably designed for vertical takeoff and landing. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0072] The aircraft can be an "electrical vertical take-off and landing" (eVTOL) aircraft.
[0073] Since the aircraft according to the invention has a flight control system according to one of the aforementioned embodiments, all of the aforementioned features, combinations of features and the respective advantages associated therewith are also transferable to the aircraft according to the invention, or at least transferable in an analogous manner.
[0074] The drive devices can each include an electric motor that drives a rotor, in particular a propeller. Preferably, the drive devices are designed to generate lift for the aircraft. In particular, when the rotors are rotating, they generate a lift force—that is, a vertical thrust—with which the aircraft can take off vertically, land, and / or hover. Alternatively or additionally, the drive devices can be designed to generate thrust. That is, the drive devices can generate an acceleration force—that is, a horizontal thrust—which accelerates the aircraft in a forward direction. This can be the case, for example, when the aircraft is pitching and assumes an angle of attack at which the thrust of the rotors also has a horizontal component.
[0075] The flight control system is connected to the flight control computer via signal communication. This advantageously ensures that the roll, pitch, yaw, and thrust control signals are reliably transmitted from the flight control system to the flight control computer.
[0076] The flight control computer is designed to control the propulsion systems. Advantageously, the flight control computer controls the propulsion systems based on the control signals issued by the flight control system. The flight control computer is connected to the propulsion systems via signal communication.
[0077] In one exemplary embodiment, the flight control computer can individually regulate or control each of the propulsion devices such that the total lift force and / or the total thrust force of all propulsion devices results in a flight movement / attitude of the aircraft corresponding to the control signals. This means that the propulsion devices are controlled by the flight control computer in such a way that Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0078] a) the aircraft performs a yaw movement corresponding to the yaw control signal in flight,
[0079] b) the aircraft performs a pitching movement corresponding to the pitch control signal in flight,
[0080] c) the aircraft performs a roll movement corresponding to the roll control signal in flight, and / or
[0081] d) the drive devices generate a total thrust force corresponding to the thrust control signal.
[0082] The invention, as well as advantageous embodiments of the invention, can also be described by the following aspects. The features listed in these aspects can be combined with the aforementioned features as desired, provided this is technically sensible and appropriate.
[0083] Aspect 1 Flight control system for controlling an aircraft, in particular an eVTOL aircraft, by a single pilot, the flight control system comprising:
[0084] (a) a primary control device configured in a main control mode of the flight control system to detect a pilot input and, based on the detected input, output a corresponding roll control signal, pitch control signal, and yaw control signal; (b) a thrust control device functionally independent of the primary control device, configured in the main control mode of the flight control system to detect a pilot input and, based on the detected input, output a corresponding thrust control signal; (c) a secondary control device spatially separated and functionally independent from the primary control device and the thrust control device, configured in a first alternative control mode of the flight control system to perform the functionality of the primary control device. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0085] (d) an alternative thrust control device arranged on the primary control device or on the secondary control device, but functionally independent of the primary control device and the secondary control device and of the thrust control device, which is configured in a second alternative control mode to assume the functionality of the thrust control device.
[0086] Aspect 2 flight control system according to aspect 1, wherein the flight control system is configured in a third alternative control mode of the flight control system such that the aircraft is controlled exclusively via the secondary control device and the alternative thrust control device.
[0087] Aspect 3 Flight control system according to any of the preceding aspects, wherein the flight control system has a display designed to indicate to the pilot in which control mode the flight control system is operating.
[0088] Aspect 4 Flight control system according to any of the preceding aspects, wherein the primary control device and the secondary control device each (a) have a handle for the pilot, wherein (b) the handle is rotatable about a vertical axis with respect to a base and the output yaw control signal is correlated with the rotation position of the respective handle about the vertical axis,
[0089] (c) the handle is movable about a transverse axis orthogonal to the vertical axis with respect to the base and the output pitch control signal correlates with the position of the handle with respect to the transverse axis,
[0090] (d) the handle is movable about a longitudinal axis orthogonal to the vertical and transverse axes with respect to the base, and the output roll control signal correlates with the position of the handle with respect to the longitudinal axis. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0091] Aspect 5 flight control system according to aspect 4, wherein a finger input device is arranged on the handle of the primary control device, which is movable in relation to the handle.
[0092] Aspect 6 flight control system according to aspect 5, wherein the finger input device is arranged ergonomically on the handle in such a way that the finger input device can be operated by means of a thumb of the aircraft pilot, and / or wherein the finger input device is rotatable about an axis of rotation with respect to the handle and / or is translationally displaceable with respect to the handle.
[0093] Aspect 7 flight control system according to one of aspects 5 or 6, wherein the finger input device of the primary control device
[0094] (a) is inoperative in the main control mode of the flight control system and / or
[0095] (b) in the second alternative control mode of the flight control system, the alternative thrust control device is wherein the thrust control signal output by the alternative thrust control device correlates with the position of the finger input device in relation to the handgrip.
[0096] Aspect 8 Flight control system according to one of the preceding aspects, wherein the thrust control device is spatially separated from the primary control device and the secondary control device.
[0097] Aspect 9 Flight control system according to one of the preceding aspects, wherein the thrust control device has a thrust lever movable with respect to a thrust lever base, wherein the thrust control signal correlates with the position of the thrust lever relative to the thrust lever base.
[0098] Aspect 10 Flight control system according to one of the preceding aspects, wherein the flight control system is designed and arranged such that, in the main control mode of the flight control system, the primary control device can be operated by one hand of the pilot and the thrust control device can be operated by the other hand of the pilot. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0099] Aspect 11 Flight control system according to one of the preceding aspects in combination with one of aspects 5 or 6, wherein the flight control system is designed and arranged such that in the first alternative control mode of the flight control system the aircraft can be controlled by a single hand of the pilot via the primary control device and the finger input device on the first primary control device.
[0100] Aspect 12 Flight control system according to one of the preceding aspects, wherein the flight control system is designed and arranged such that in the first alternative control mode of the flight control system the secondary control device can be operated by one hand of the pilot and the thrust control device can be operated by the other hand of the pilot.
[0101] Aspect 13 Flight control system according to aspect 4, wherein a finger input device is arranged on the handle of the secondary control device, which is movable in relation to the handle of the secondary control device.
[0102] Aspect 14 Flight control system according to Aspect 13 in combination with one of Aspects 5 or 6, wherein the finger input device of the primary control device is the thrust control device and the finger input device of the secondary control device is the alternative thrust control device.
[0103] Aspect 15 Flight control system according to aspect 14, wherein the flight control system is designed and arranged such that in the main control mode of the flight control system the aircraft can be controlled by a single hand of the pilot via the primary control device and the finger input device on the primary control device.
[0104] Aspect 16 flight control system according to Aspect 13 in combination with one of Aspects 5 or 6, wherein the finger input device of the primary control device is the alternative thrust control device and the finger input device of the secondary control device is the thrust control device. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0105] Aspect 17 Flight control system according to aspect 16, wherein the flight control system is designed and arranged such that in the main control mode of the flight control system the primary control device can be operated by one hand of the pilot and the finger input device can be operated by the other hand of the pilot.
[0106] Aspect 18 Flight control system according to one of the preceding aspects, wherein the flight control system is designed to automatically and / or based on input from the pilot switch between the main control mode, the first alternative control mode and the second alternative control mode.
[0107] Aspect 19 Flight control system according to one of the preceding aspects, wherein a further input device is arranged on the primary control device and / or the secondary control device, and wherein the flight control system is configured to output a further control signal, preferably a radio control signal, an autopilot control signal and / or a pitch angle and / or airspeed hold signal, when the further input device is actuated by the pilot.
[0108] Aspect 20 aircraft, preferably eVTOL aircraft, with
[0109] (a) several lift- and / or thrust-generating drive devices, preferably several electric motors, each driving at least one rotor,
[0110] (b) a flight control system according to any of the preceding aspects, and (c) a flight control computer connected to the flight control system via signal communication, which is designed to
[0111] (cl) to control the propulsion systems so that the aircraft performs a yaw movement in flight corresponding to the yaw control signal, (c2) to control the propulsion systems so that the aircraft performs a pitch movement in flight corresponding to the pitch control signal, (c3) to control the propulsion systems so that the aircraft performs a roll movement in flight corresponding to the roll control signal, and Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0112] (c4) to control the drive devices so that the drive devices generate a total thrust force corresponding to the thrust control signal.
[0113] Brief description of the drawings
[0114] The various exemplary features described above can be combined with one another, provided this is technically feasible and appropriate. Further combinable features, advantages, and embodiments of the invention will become apparent from the following description of exemplary embodiments and with reference to the figures. These show:
[0115] Figure 1 shows a schematic representation of a first embodiment of a flight control system,
[0116] Figure 2 shows a schematic representation of an exemplary display concept of the flight control system according to the first embodiment.
[0117] Figure 3 shows a schematic representation of a second embodiment of a flight control system,
[0118] Figure 4 shows a schematic representation of an exemplary primary control device according to the aforementioned embodiments and a secondary control device according to the second embodiment, and
[0119] Figure 5 shows a schematic side view of an embodiment of an aircraft with a flight control system according to one of the aforementioned embodiments.
[0120] Ways to implement the invention
[0121] Figure 1 shows a schematic representation of a flight control system 100 according to a first embodiment. The flight control system 100 is designed to control an eVTOL aircraft 400 (see Figure 5). Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0122] The flight control system 100 comprises a primary control device 110, a secondary control device 120, and a thrust control device 130. The devices 110, 120, and 130 are designed and arranged relative to a pilot 300 of the aircraft 400 (not shown in Figure 1) such that the pilot 300 can operate the primary control device 110 or the secondary control device 120 with his right hand. With his left hand, the pilot 300 can operate the thrust control device 130. The primary control device 110, the secondary control device 120, and the thrust control device 130 are functionally independent of one another and spatially separated.
[0123] In a main control mode 102 (see Figure 2) of the flight control system 100, the pilot 300 controls the aircraft 400 via the primary control device 110 and the thrust control device 130. The primary control device 110 is configured to detect a control input from the pilot 300 and, based on the detected control input, output a corresponding roll control signal, pitch control signal, and / or yaw control signal. The thrust control device 130 is configured to detect a control input from the pilot 300 and, based on the detected control input, output a corresponding thrust control signal.
[0124] In a first alternative control mode 103 (see Figure 2) of the flight control system 100, the pilot 300 controls the aircraft 400 via the secondary control device 120 and the thrust control device 130. This means that, during the transition from the primary control mode 102 to the first alternative control mode 103, the pilot 300 switches with his right hand from the primary control device 110 to the secondary control device 120. The secondary control device 120 is configured to take over the functionality of the primary control device 110. That is, in the first alternative control mode 103 (see Figure 2) of the flight control system 100, the secondary control device 120 is configured to detect a control input from the pilot 300 and, based on the detected control input, output a corresponding roll, pitch, and / or yaw control signal.The thrust control device 130 is also configured in the first alternative control mode 103 of the flight control system 100 to detect a control input from the aircraft pilot 300 and to output a corresponding thrust control signal based on the detected control input. Volocopter Technologies GmbH 11.02.2026 FC24007-WO.
[0125] The primary control device 110 has a base 111 and a handle 112. The handle 112 is movable about three axes relative to the base 111, with each roll, pitch, and yaw control signal corresponding to a movement of the handle 112 about a corresponding axis. This is particularly the case in the main control mode 102 of the flight control system 100. In the embodiment shown in Figure 1, the primary control device 110 is designed as a "Pilot Control Stick (PCS)."
[0126] A finger input device 113 is provided on the handle 112 of the primary control device 110. The finger input device 113 is ergonomically arranged on the handle 112 such that it can be operated with the thumb of the right hand of the aircraft pilot 300. The finger input device 113 is movable relative to the handle 112. For example, the finger input device 113 can be rotatable about a pivot axis DF (not shown in Figure 1) and / or translationally displaceable relative to the handle 112. For the detailed construction of the primary control device 110, reference is made to the description below for Figure 4 and to the illustration in Figure 4.
[0127] The secondary control device 120 has a base 121 and a handle 122. The handle 122 is movable about three axes relative to the base 121, with each roll, pitch, and yaw control signal corresponding to a movement of the handle 122 about a corresponding axis. This is particularly the case in the first alternative control mode 103 of the flight control system 100. In the embodiment shown in Figure 1, the secondary control device 120 is configured as a "Back-Up Pilot Control Stick (BPCS)." For the detailed construction of the primary control device 110, reference is made to the description below for Figure 4 and to the illustration in Figure 4.
[0128] The thrust control device 130 has a thrust lever base 131 and a thrust lever 132. The thrust lever 132 is movable back and forth in a pivoting direction S relative to the thrust lever base 131, in particular pivotable. The thrust control signal output by the thrust control device 130 correlates with the position, in particular the pivoting position, of the thrust lever 132 relative to the thrust lever base 131. The thrust control device 130 shown in the first embodiment is designed as a Heave Interceptor. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0129] The flight control system 100 has an alternative thrust control device 140. In the embodiment shown in Figure 1, the alternative thrust control device 140 is the finger input device 113 on the handle 112 of the primary control device 110.
[0130] In a second alternative control mode 104 (see Figure 2) of the flight control system 100, the pilot 300 controls the aircraft 400 exclusively via the primary control device 110. This means that, unlike in the main control mode 102 and / or the first alternative control mode 103, the pilot 300 no longer controls the thrust of the aircraft 400 via the thrust control device 130, but via the alternative thrust control device 140, in particular the finger input device 113 on the handle 112 of the primary control device 110. In the second alternative control mode 104 of the flight control system 100, the pilot 300 controls the aircraft 400 with one hand, in particular exclusively with his right hand. The alternative thrust control device 140 is designed to take over the functionality of the thrust control device 130 in the second alternative control mode 104 of the flight control system 100.This means that the alternative thrust control device 140 is designed to detect a control input from the aircraft pilot 300 and to output a corresponding thrust control signal based on the detected control input.
[0131] Figure 2 shows a schematic representation of an exemplary display concept of the flight control system 100 according to the aforementioned embodiment.
[0132] The flight control system 100 can have a display 101 which is configured to show the pilot 300 the current control mode 102, 103, 104 of the flight control system 100. The illustration of display 1 in Figure 2 shows an overview of all symbols that can be displayed by display 1.
[0133] In the main control mode 102 of the flight control system 100, the display 101 shows the pilot 300 the symbol “H + PCS” (compare the left-hand representation of display 101 in Figure 2). “H” stands for “Heave Interceptor”, i.e., the thrust control device 130, and “PCS” for “Pilot Control Stick”, i.e., the primary control device 110. Through the display 101 in the main control mode 102, the Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0134] The aircraft pilot 300 thus indicates that the aircraft 400 is currently controllable via the primary control device 110 and the thrust control device 130.
[0135] In the first alternative control mode 103 of the flight control system 100, the display 101 shows the pilot 300 the symbol “H + BPCS” (compare the lower illustration of display 101 in Figure 2). Here, “H” stands for “Heave Interceptor”, i.e., the thrust control device 130, and “BPCS” for “Back-up Pilot Control Stick”, i.e., the secondary control device 120. Thus, the display 101 in the first alternative control mode 103 indicates to the pilot 300 that the aircraft 400 is currently controllable via the secondary control device 120 and the thrust control device 130.
[0136] In the second alternative control mode 104 of the flight control system 100, the display 101 shows the pilot 300 the symbol “PCS” (compare the right-hand illustration of display 101 in Figure 2). “PCS” stands for “Pilot Control Stick”, i.e., the primary control device 110. Through the display 101 in the second alternative control mode 104, the pilot 300 thus receives the indication that the aircraft 400 can currently only be controlled via the primary control device 110, with the finger input device 113 on the handle 112 of the primary control device 110 being the alternative thrust control device 140.
[0137] The flight control system 100 is configured to automatically switch between the main control mode 102, the first alternative control mode 103, and the second alternative control mode 104. This can occur, in particular, when the flight control system 100 detects a mechanical and / or electromechanical defect in one of the control devices 110, 120, the thrust control device 130, or the alternative thrust control device 140. Additionally, the flight control system 100 can be configured to automatically switch between the main control mode 102, the first alternative control mode 103, and the second alternative control mode 104 when it detects a corresponding input from the pilot 300, for example, via a key 224 (not shown in Figure 3).
[0138] Figure 3 shows a schematic representation of a second embodiment of a flight control system 200. The flight control system 200 according to the second Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0139] The second embodiment differs essentially from the flight control system 100 according to the first embodiment in that a finger input device 223 is also provided on the handle 222 of the secondary control device 220. In the second embodiment, the finger input device 213 on the handle 212 of the primary control device 210 forms the thrust control device 230. The finger input device 223 on the handle 222 of the secondary control device 220 forms the alternative thrust control device 240. Consequently, in the second embodiment of the flight control system 200, a thrust lever base and a thrust lever can be omitted. Otherwise, the flight control system 200 according to the second embodiment corresponds to the first embodiment. For functional details, reference is made to the above descriptions of the first embodiment.
[0140] In the representation shown in Figure 3, the pilot 300 can operate the primary control device 210 with his right hand. The pilot 300 can operate the secondary control device 220 with his left hand. Alternatively, embodiments are also conceivable in which the secondary control device 220 is also arranged to the right of the pilot 300, so that the pilot 300 can also operate the secondary control device 220 with his right hand.
[0141] Figure 4 shows a schematic representation of an embodiment of a primary control device 210 and a secondary control device 220 according to the second embodiment of the flight control system 200, as well as a primary control device 110 according to the first embodiment of the flight control system 100. For the sake of simplicity, only one control device 110; 210; 220 will be described below.
[0142] The control device 110; 210; 220 comprises the aforementioned base 111; 211; 221 and the aforementioned handle 112; 212; 222. The handle 112; 212; 222 is movable with respect to the base 111; 211; 221 about three mutually orthogonal axes Xs, Ys, Zs, namely a longitudinal axis Xs, a transverse axis Ys, and a vertical axis Zs. For example, the handle 112; 212; 222 can be pushed forward and / or pulled backward by the aircraft pilot 300 (not shown in Figure 4). This would correspond to a movement of the handle 112; 212; 222 in the direction N shown in Figure 1. In this movement, the handle 112; 212; 222 moved about the transverse axis Ys relative to base 111; 211; 221. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0143] Control device 110; 210; 220 is configured to generate and / or output a corresponding pitch control signal when the handle 112; 212; 222 is moved about the transverse axis Ys. When the pilot 300 pushes the handle 112; 212; 222 to port or starboard (the direction indicated by reference numeral R in Figure 1), the handle 112; 212; 222 is moved about the longitudinal axis Xs with respect to the base 111; 211; 221. The control device 110; 210; 220 is configured to generate and / or output a roll control signal that correlates with the movement of the handle 112; 212; 222 about the longitudinal axis Xs. When the handle 112; 212; When the 222 is rotated about the vertical axis Zs, in particular in the direction with reference numeral G, a corresponding yaw control signal is generated and / or output by the control device 110; 210; 220.
[0144] A finger input device 113; 213; 223 is provided on the handle 112; 212; 222. As shown in Figure 4, the finger input device 113; 213; 223 is arranged on the handle 112; 212; 222 such that the pilot 300 can operate the finger input device 113; 213; 223 with his thumb. The finger input device 113; 213; 223 is rotatable about a pivot axis DF with respect to the handle 112; 212; 222, and in particular, rotatably movable. In an alternative embodiment not shown in Figure 4, the finger input device 113; 213; 223 can be rotated about a pivot axis DF with respect to the handle 112; 212; 222 be translationally movable, in particular be displaceably movable.
[0145] When the finger input device 113; 213; 223 is rotated about the axis of rotation DF, the control device 110; 210; 220 generates and / or outputs a corresponding thrust control signal. For example, the control device 110; 210; 220 can generate and / or output a thrust control signal that correlates with an increase in thrust of propulsion devices 410 of the aircraft 400 (see Figure 5) when the finger input device 113; 213; 223 is rotated forward about the axis of rotation DF. When the finger input device 113; 213; 223 is rotated in the opposite direction, the control device 110; 210; 220 can generate and / or output a thrust control signal that correlates with a reduction in thrust of the propulsion devices 410.
[0146] In the embodiment shown in Figure 4, the control device 110; 210; 220, in particular the handle 112; 212; 222, comprises a further input device 114; 214; 224. Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0147] In particular, a button for changing the control mode. The further input device 114; 214; 224 is arranged on the handgrip 112; 212; 222 such that the input device 114; 214; 224 can be operated by the pilot 300 with his thumb. When the input device 114; 214; 224 is operated by the pilot 300, the flight control system 100; 200 switches between the main control mode 102, the first alternative control mode 103, or the second alternative control mode 104.
[0148] Figure 5 shows a schematic side view of an embodiment of an aircraft 400 with a flight control system 100; 200 according to one of the aforementioned embodiments.
[0149] Aircraft 400 has an aircraft-specific coordinate system. This coordinate system comprises three mutually orthogonal axes: a longitudinal axis XL, a lateral axis YL, and a vertical axis ZL. The longitudinal axis XL is the roll axis XL of aircraft 400. This means that aircraft 400 rolls when it rotates around the roll axis XL in flight. The lateral axis YL is the pitch axis YL of aircraft 400. This means that aircraft 400 pitches, and thus its angle of attack changes, when it rotates around the pitch axis YL in flight. The aircraft's vertical axis ZL is the yaw axis YL of aircraft 400. This means that aircraft 400 performs a yaw movement when it rotates around its yaw axis YL in flight.
[0150] The aircraft 400 comprises several propulsion devices 410. Each of the propulsion devices 410 has an electric motor 412 and a rotor 411. The rotor 411 is driven by the respective electric motor 412. For the sake of clarity, the electric motor 412 and the rotor 411 are only shown for the rightmost propulsion device 410.
[0151] During takeoff, landing, and / or hovering, the propulsion units 410 generate lift. As shown in Figure 5, the propulsion units 410 are oriented essentially parallel to the ground. During forward flight, the propulsion units 410 generate lift and thrust. This can, for example, be used in Volocopter Technologies GmbH 11.02.2026 FC24007-WO
[0152] This can be achieved by changing the pitch angle of the aircraft 400 in such a way that the drive devices 410 are no longer aligned parallel to the ground.
[0153] A flight control computer 420 of the aircraft 400 is connected to the flight control system 100; 200 via signal communication. The flight control computer 420 is configured to receive the control signals from the flight control system 100; 200, process them electronically, and control or regulate the propulsion devices 410 based on the control signals. For this purpose, the flight control computer 420 is also connected to each of the propulsion devices 410 via signal communication.
[0154] For example, if the flight control computer 420 receives a pitch control signal from the flight control system 100; 200, the flight control computer 420 will control the propulsion devices 410 such that the aircraft 400 performs a corresponding pitch movement about the pitch axis YL in flight. If the flight control computer 420 receives a roll control signal from the flight control system 100; 200, the flight control computer 420 will control the propulsion devices 410 such that the aircraft 400 performs a corresponding roll movement about the roll axis XL in flight. If the flight control computer 420 receives a yaw control signal from the flight control system 100; 200, the flight control computer 420 will control the propulsion devices 410 such that the aircraft 400 performs a corresponding yaw movement about the yaw axis ZL in flight.If the flight control computer 420 receives a thrust control signal from the flight control system 100; 200, the flight control computer 420 will control or regulate the propulsion devices 410 such that the total thrust of all propulsion devices 410 increases or decreases according to the thrust control signal. Volocopter Technologies GmbH 11.02.2026.
[0155] FC24007-WO
[0156] Reference symbol list
[0157] 100 flight control systems
[0158] 101 advertisement
[0159] 102 Main Control Mode
[0160] 103 First alternative control mode
[0161] 104 second alternative control mode
[0162] 110 Primary control device
[0163] 111 Basis of the primary control device
[0164] 112 Primary control device handle
[0165] 113 Finger input device of the primary control device 114 Button for changing the control mode
[0166] 120 S secondary tax device
[0167] 121 Basis of the secondary control device
[0168] 122 Handle of the secondary control device
[0169] 130 S chub control device
[0170] 131 Thrust lever base
[0171] 132 thrust levers
[0172] 140 Alternative- S chub control device
[0173] 200 flight control system
[0174] 210 Primary control device
[0175] 211 Basis of the primary control device
[0176] 212 Handle of the primary control device
[0177] 213 Finger input device of the primary control device 214 Button for changing the control mode
[0178] 220 S secondary tax device
[0179] 221 Basis of the secondary control device
[0180] 222 Handle of the secondary control device
[0181] 223 Finger input device of the secondary control unit Volocopter Technologies GmbH 11.02.2026
[0182] FC24007-WO
[0183] 224 Key for changing control mode
[0184] 230 Thrust control device
[0185] 240 Alternative thrust control device
[0186] 300 pilots
[0187] 400 aircraft
[0188] 410 Drive device
[0189] 411 Rotor
[0190] 412 Electric motor
[0191] 420 flight control computers
[0192] 430 signal-communicating connection
[0193] Xs longitudinal axis control stick
[0194] Ys transverse axis control stick
[0195] Zs vertical axis control stick
[0196] DF rotary axis finger input device
[0197] G Rotary movement for yaw control of the aircraft
[0198] N Forward and backward movement for pitch control of the aircraft. R Left and right movement for roll control of the aircraft.
[0199] S Swivel direction Thrust lever
[0200] XL Roll Axle Aircraft
[0201] YL Pitch Axis Aircraft
[0202] ZL yaw axis aircraft
Claims
Volocopter Technologies GmbH 11.02.2026 FC24007-WO Patent claims 1. Flight control system (100; 200) for controlling an aircraft (400), in particular for controlling an eVTOL aircraft (400), by a single pilot (300), the flight control system (100; 200) comprising: (a) a primary control device (110; 210) configured in a main control mode (102) of the flight control system (100; 200) to detect a control input from the pilot (300) and, based on the detected control input, to output a corresponding roll control signal, pitch control signal and yaw control signal, (b) a thrust control device (130; 230) that is functionally independent of the primary control device (110; 210) and is configured in the main control mode (102) of the flight control system (100; 200) to detect a thrust control input from the pilot (300) and to output a corresponding thrust control signal based on the detected thrust control input; (c) a secondary control device (120; 220) that is spatially separated from the primary control device (HO; 210) and from the thrust control device (130; 230) and is functionally independent, and which in a first alternative control mode (103) of the flight control system (100; 200) is configured to assume the functionality of the primary control device (110; 210); and (d) a device arranged on the primary control device (HO; 210) or on the secondary control device (120; 220), but from the primary control device (110; 210), from the secondary control device (120; 220), and from the thrust control device (130;230) functionally independent alternative thrust control device (140; 240), wherein the alternative thrust control device (140; 240) is configured in a second alternative control mode (104) to take over the functionality of the thrust control device (130; 230).; 2. Flight control system (100; 200) according to claim 1, wherein the flight control system (100; 200) has a display (101) configured to indicate to the pilot (300) in which control mode (102, 103, 104) the flight control system (100; 200) is operating. Volocopter Technologies GmbH 11.02.2026 FC24007-WO 3. Flight control system (100; 200) according to one of the preceding claims, wherein the primary control device (110; 210) and the secondary control device (120; 220) respectively, (a) have a handle (112, 122; 212, 222) for the pilot (300), wherein (b) the handle (112, 122; 212, 222) is rotatable about a vertical axis (Zs) with respect to a base (111, 121; 211, 221) and the output yaw control signal correlates with the rotation position of the respective handle (112, 122; 212, 222) about the vertical axis (Zs), (c) the handle (112, 122; 212, 222) is movable about a transverse axis (Ys) orthogonal to the vertical axis (Zs) with respect to the base (111, 121; 211, 221) and the output pitch control signal correlates with the position of the handle (112, 122; 212, 222) with respect to the transverse axis (Ys), (d) the handle (112, 122; 212, 222) is movable about a longitudinal axis (Xs) orthogonal to the vertical axis (Zs) and the transverse axis (Ys) with respect to the base (111, 121; 211, 221) and the output roll control signal correlates with the position of the handle (112, 122; 212, 222) with respect to the longitudinal axis (Xs).
4. Flight control system (100; 200) according to claim 3, wherein a finger input device (113; 213) is arranged on the handle (112; 212) of the primary control device (HO; 210), which is movable in relation to the handle (112; 212), preferably rotatable about a rotational axis (DF) in relation to the handle (112; 212) and / or translationally displaceable in relation to the handle (112; 212), and preferably operable by means of a thumb of the aircraft pilot (300).
5. Flight control system (100) according to one of the preceding claims, wherein the flight control system (100) is designed and arranged such that, in the main control mode (102) of the flight control system (100), the primary control device (110) can be operated by one hand of the pilot (300) and the thrust control device (130) can be operated by the other hand of the pilot (300). Volocopter Technologies GmbH 11.02.2026 FC24007-WO 6. Flight control system (100) according to claim 4 or claim 5, wherein the finger input device (113) of the primary control device (110) (a) is non-functional in the main control mode (102) of the flight control system (100) and / or (b) in the second alternative control mode (104) of the flight control system (100) is the alternative thrust control device (140), wherein the thrust control signal output by the alternative thrust control device (140) correlates with the position of the finger input device (113) in relation to the handle (112) of the primary control device (110).
7. Flight control system (100) according to one of the preceding claims, wherein the thrust control device (130) is spatially spaced apart from the primary control device (110) and the secondary control device (120) and / or has a thrust lever (132) movable with respect to a thrust lever base (131), wherein the thrust control signal correlates with the position of the thrust lever (132) relative to the thrust lever base (131).
8. Flight control system (100; 200) according to one of the preceding claims in combination with claim 4, wherein the flight control system (100; 200) is designed and arranged such that at least in one control mode (102, 103, 104) of the flight control system (100; 200) the aircraft (400) can be controlled by means of a single hand of the aircraft pilot (300) via the primary control device (110; 210) and the finger input device (113; 213) on the primary control device (110; 210).
9. Flight control system (200) according to claim 4, wherein a finger input device (223) is arranged on the handle (222) of the secondary control device (220), the finger input device being movable relative to the handle (222) of the secondary control device (220), and wherein the finger input device (213) of the primary control device (210) is the thrust control device (230) and the finger input device (223) of the secondary control device (220) is the alternative thrust control device (240). Volocopter Technologies GmbH 11.02.2026 FC24007-WO 10. Flight control system (100; 200) according to one of the preceding claims, wherein the flight control system (100; 200) is configured to automatically and / or based on an input from the pilot (300) switch between the main control mode (102), the first alternative control mode (103) and the second alternative control mode (104).
11. Flight control system (100; 200) according to one of the preceding claims, wherein a further input device (114) is arranged on the primary control device (110) and / or the secondary control device (120), and wherein the flight control system (100; 200) is configured to output a further control signal, preferably a radio control signal, an autopilot control signal and / or a pitch angle and / or airspeed hold signal, when the further input device (114) is actuated by the pilot (300).
12. Aircraft (400), preferably eVTOL aircraft (400), with (a) several lift- and / or thrust-generating drive devices (410), each preferably comprising an electric motor (412) for driving a rotor (411), (b) a flight control system (100; 200) according to any one of the preceding claims, and (c) a flight control computer (420) connected by signal communication to the flight control system (100; 200), which is configured to (1) control the propulsion devices (410) so that the aircraft (400) performs a yaw movement in flight corresponding to the yaw control signal, (c2) control the propulsion devices (410) so that the aircraft (400) performs a pitch movement in flight corresponding to the pitch control signal, (c3) control the propulsion devices (410) so that the aircraft (400) performs a roll movement in flight corresponding to the roll control signal, and (c4) to control the drive devices (410) so that the drive devices (410) generate a total thrust force corresponding to the thrust control signal.