Abstract: A method of controlling an aircraft having multiple configurations is provided, wherein each configuration is controlled by a different control law implemented by a flight control device and transition from one configuration to another configuration is achieved by gradually blending out a control law for one configuration and by gradually increasing an impact of a control law for another configuration in the flight control device based on an estimated flight condition of the aircraft by dynamically adjusting, in the flight control device, respective maximum and minimum limit values of control volumes, which control volumes are defined by parameter ranges of control parameters in connection with a corresponding control law for the one configuration and for the other configuration, respectively.

Abstract: A motor control system (1), preferably for an aircraft, having a plurality of motors (3), each having a motor control unit (2) that includes a primary motor controller (COM) configured to provide motor control commands (9) to a corresponding motor (3). The system (1) also has a system control unit (COMstring) in communication with each of the primary motor controllers (COM), configured to provide motor control commands (9) to the primary motor controllers. A system monitoring unit (MONstring) is connected to the system control unit for monitoring an operation thereof, and at least one sensor (4) determines an operation state of at least one of the motors. The sensor is connected with the system monitoring unit, which is configured to disable communication between the system control unit and the primary motor controllers and/or between the primary motor controllers and the motors based on the monitoring and/or the determined operation state.

Abstract: A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b?) and at least one motor (6a) driving the propeller (6b, 6b?), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

Abstract: A method of controlling a multi-rotor aircraft (1) including at least five, preferably at least six, lifting rotors (2; R1-R6), each having a first rotation axis which is essentially parallel to a yaw axis (z) of the aircraft (1), and at least one forward propulsion device (3), preferably two forward propulsion devices (P1, P2), the at least one forward propulsion device having at least two rotors (P1_R1, P1_R2, P2_R1, P2_R2) that are arranged coaxially with a second rotation axis which is essentially parallel to a roll axis (x) of the aircraft. The at least one or each of the forward propulsion devices (3, P1, P2) being arranged at a respective distance (+y, ?y) from said roll axis (x). The method further includes: using at least one of the rotors of the at least one forward propulsion device to control the aircraft's moment about the yaw and/or roll axes independently from each other.

Abstract: A VTOL aircraft (1) having a fuselage (2) for transporting passengers and/or load, front and rear wings (3, 4) attached to the fuselage, a right connecting beam (5a) and a left connecting beam (5b), which connecting beams structurally connect the front wing and the rear wing, and which connecting beams are spaced apart from the fuselage, and at least two lifting units (M1-M6) on each one of the connecting beams. The lifting units each include at least one propeller (6b) and at least one motor (6a) driving the propeller, preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation. The front wing, at least in portions thereof, has a sweep angle ? between ?=450 and ?=135°, and the rear wing, at least in portions thereof, has a forward sweep with sweep angle ??30°.

Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding that accommodates at most one of the at least two rotor assemblies, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein the air inlet region exhibits in circumferential direction of the cylindrical air duct an undulated geometry.

Abstract: A method of controlling a multi-rotor aircraft (1) including at least five, preferably at least six, lifting rotors (2; R1-R6), each having a first rotation axis which is essentially parallel to a yaw axis (z) of the aircraft (1), and at least one forward propulsion device (3), preferably two forward propulsion devices (P1, P2), the at least one forward propulsion device having at least two rotors (P1_R1, P1_R2, P2_R1, P2_R2) that are arranged coaxially with a second rotation axis which is essentially parallel to a roll axis (x) of the aircraft. The at least one or each of the forward propulsion devices (3, P1, P2) being arranged at a respective distance (+y, ?y) from said roll axis (x). The method further includes: using at least one of the rotors of the at least one forward propulsion device to control the aircraft's moment about the yaw and/or roll axes independently from each other.

Abstract: A method of controlling an aircraft having multiple configurations or modes is provided, wherein each configuration is controlled by a different control law implemented by a flight control device and transition from one configuration to another configuration is achieved by gradually blending out a control law for said one configuration and by gradually increasing an impact of a control law for said other configuration in said flight control device based on an estimated flight condition of the aircraft by dynamically adjusting, in said flight control device, respective maximum and minimum limit values of control volumes, which control volumes are defined by parameter ranges of control parameters in connection with a corresponding control law for said one configuration and for said other configuration, respectively.

Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

Abstract: A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

Abstract: A motor control system (1), preferably for an aircraft, having a plurality of motors (3), each having a motor control unit (2), each of the motor control units (2) including a primary motor controller (COM) configured to provide motor control commands (9) to a corresponding motor (3). The motor control system (1) also has a system control unit (COMstring) in communication with each of the primary motor controllers (COM), configured to provide motor control commands (9) to the primary motor controllers (COM). A system monitoring unit (MONstring) is connected to the system control unit (COMstring) for monitoring an operation thereof, and at least one sensor (4) determines an operation state of at least one of the motors (3).

Abstract: A multirotor aircraft with an airframe and a thrust producing units arrangement, wherein the thrust producing units arrangement comprises a predetermined number of thrust producing units for producing thrust in a predetermined direction, and wherein a flexible suspension unit is rigidly mounted to the airframe, wherein the flexible suspension unit comprises at least one bearing that mechanically couples the thrust producing units arrangement to the airframe such that the thrust producing units of the predetermined number of thrust producing units are inclinable in relation to the airframe.

Abstract: A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b?) and at least one motor (6a) driving the propeller (6b, 6b?), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

Abstract: A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units that are arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

Abstract: A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising a shrouding and at least two rotor assemblies, wherein the shrouding defines an internal volume, and wherein a first rotor assembly of the at least two rotor assemblies defines a first rotor axis and a second rotor assembly of the at least two rotor assemblies defines a second rotor axis, the first and second rotor axes being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles with respect to the predetermined direction, the associated inclination angles being comprised in a range between ?60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly is arranged outside of the internal volume of the shrouding.

Abstract: A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising associated leading and trailing edges that define a respective chord and quarter chord line thereof, wherein the common pitch axis is arranged with a predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, and wherein the associated connection means is adapted to enable, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis.

Abstract: An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.

Abstract: A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units that are arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

Abstract: A multirotor aircraft with an airframe and a thrust producing units arrangement, wherein the thrust producing units arrangement comprises a predetermined number of thrust producing units for producing thrust in a predetermined direction, and wherein a flexible suspension unit is rigidly mounted to the airframe, wherein the flexible suspension unit comprises at least one bearing that mechanically couples the thrust producing units arrangement to the airframe such that the thrust producing units of the predetermined number of thrust producing units are inclinable in relation to the airframe.