Abstract: A method for controlling an aircraft, in particular a VTOL multirotor aircraft, in which flight influencing units of the aircraft a) are supplied with control commands via a first/control channel from a first computer (COM), which control commands originate or are derived from a pilot input (PE), and b) the control commands are monitored by a second/monitoring channel and a second computer (MON), which checks whether the control commands are suitable for a given physical state of the aircraft and the pilot input, c) the second computer determines whether a current navigation state of the aircraft coincides with the pilot input, which has been transformed into a desired navigation state of the aircraft, preferably by the second computer, within a prescribed deviation, and d) a control signal for controlling the aircraft is generated in dependence on a determination result of step c).

Abstract: A method for operating an aircraft with N>4 drive units. A flight control system (FCS) generates control commands u_COM, u_COM?U?R{circumflex over (?)}N, for the drive units, via a first channel. u represents limitations of the drive units. The FCS generates pseudo-control commands ?_COM, ?_COMER{circumflex over (?)}4, in the first channel, which specify torques about corresponding axes of rotation of the aircraft and a thrust, a control matrix M?R{circumflex over (?)}(4×N) with ?=M u establishing a relationship with the control commands u; in the first channel. Admissible control commands u_COM?U are calculated from the pseudo-control commands; and the first channel is monitored and, based on a result, is passivated.

Abstract: A method of controlling an actuator system including a plurality of k actuators. Each of the actuators-receives a control input ui, wherein index i denotes a particular actuator, which control input ui is determined depending on a weight matrix W including a weighting factor wi for each actuator and depending on at least a physical maximum control limit uimax for each of the actuators. The weighting factors wi and/or physical maximum control limit uimax are actively changed during operation if a first comparison of the control input ui or a function f(ui) thereof with a set first threshold value yields that the control input ui or function f(ui) thereof exceeds the set first threshold value. The first comparison is repeated during operation, and a new control input ui is determined from the adjusted weighting factor wi and/or the adjusted physical maximum control limit uimax and applied to the actuators.

Abstract: A method is provided for stabilizing an orientation and height of a person or load-carrying multicopter with a plurality of motors, wherein the drive of the individual motors in flight is continuously calculated by a flight control unit and correspondingly prescribed to the motors using control technology, for which purpose, based on a desired torque ?, of a desired thrust s preferably prescribed by a pilot signal, and of a motor matrix M, the drive of the motors is calculated by a motor allocation algorithm f and provided as a control signal to the motors, wherein the following applies to the drive and the corresponding motor control variables u: u=f(?, s, M).

Abstract: A method for operating an eVTOL multirotor aircraft having distributed actuators activated by controllers that each determines an associated manipulated variable signal at least for a subset of actuators and provides it for the relevant actuator. The method provides that for an actuator: i) assigning a different priority ranking for each controller; ii) determining, by way of a given controller having a given priority ranking, at least one manipulated variable signal for the actuator and transmitting the signal identified by the given priority ranking to the relevant actuator and to a controller having a successive priority ranking; iii) receiving, via a given controller having a given priority ranking, manipulated variable signals from controllers having higher priority ranking and relaying these signals to the actuator and to a controller having a successive priority ranking; and iv) activating the actuator using the manipulated variable signal identified by the highest priority ranking.

Abstract: A method for operating an aircraft with N>4 drive units, preferably in the form of electrically driven rotors, where a flight control system generates control commands ?COM, ?COM?U?RN, for the drive units, via a first channel and transmits them to the drive units, where U represents limitations of the drive units; the flight control system also generates pseudo-control commands ?COM, ?COM?R4, in the first channel, which specify torques about corresponding axes of rotation of the aircraft and a thrust, a control matrix M?R4×N according to ?=M ? establishing a relationship with the control commands ?; in the first channel, admissible control commands ?COM?U are calculated from the pseudo-control commands ?COM by an allocation algorithm; and the first channel is monitored by an independent second channel and, based on a monitoring result, is passivated.

Abstract: A method for controlling an aircraft (1), in particular a VTOL multirotor aircraft, in which flight influencing units of the aircraft a) are supplied with control commands via a first/control channel from a first computer (COM), which control commands originate or are derived from a pilot input (PE), and b) the control commands are monitored by a second/monitoring channel and a second computer (MON), which checks whether the control commands are suitable for a given physical state of the aircraft and the pilot input, c) the second computer determines whether a current navigation state of the aircraft (1) coincides with the pilot input, which has been transformed into a desired navigation state of the aircraft, preferably by the second computer, within a prescribed deviation, and d) a control signal for controlling the aircraft (1) is generated in dependence on a determination result of step c). A corresponding control device (4) and aircraft (1) with such a device are provided.

Abstract: A method of controlling an actuator system including a plurality of k actuators, preferably for controlling a multiactuator aerial vehicle with the actuators configured as individual propulsion units thereof. Each of the actuators, during operation, receives a control input ui, wherein index i denotes a particular actuator, which control input ui is determined depending on a weight matrix W including a weighting factor wi for each actuator and depending on at least a physical maximum control limit uimax for each of the actuators. The weighting factors wi and/or physical maximum control limit uimax are actively changed during operation if a first comparison, for at least some of the actuators, of the control input ui or a function ƒ(ui) thereof with a set first threshold value yields that the control input ui or function ƒ(ui) thereof exceeds the set first threshold value.

Abstract: A method is provided for stabilizing an orientation and height of a person or load-carrying multicopter with a plurality of motors, wherein the drive of the individual motors in flight is continuously calculated by a flight control unit and correspondingly prescribed to the motors using control technology, for which purpose, based on a desired torque ?, of a desired thrust s preferably prescribed by a pilot signal, and of a motor matrix M, the drive of the motors is calculated by a motor allocation algorithm f and provided as a control signal to the motors, wherein the following applies to the drive and the corresponding manipulated motor variables u: u=f(?, s, M).