Abstract: An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.

Abstract: A multirotor aircraft 10 that is adapted for vertical take-off and landing, comprising a fuselage, a thrust producing units assembly that is provided for producing thrust in operation, and a forward-swept wing that comprises a portside half wing and a starboard side half wing. Each one of the portside and starboard side half wings comprises an inboard section that is connected to the fuselage and an outboard section that forms a wing tip. The inboard sections of the portside and starboard side half wings form a central wing region. The portside and starboard side half wings are respectively connected in the region of their wing tips to an associated outboard wing pod that supports at least two non-tiltably mounted thrust producing units of the thrust producing units assembly.

Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the c

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 multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the c

Abstract: A multirotor aircraft that is adapted for vertical take-off and landing. The multirotor aircraft comprises a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip. The at least one upper wing is joined to the at least one lower wing in a joined-wing configuration.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.

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 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 that is adapted for vertical take-off and landing. The multirotor aircraft comprises a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip. The at least one upper wing is joined to the at least one lower wing in a joined-wing configuration.

Abstract: A multirotor aircraft 10 that is adapted for vertical take-off and landing, comprising a fuselage, a thrust producing units assembly that is provided for producing thrust in operation, and a forward-swept wing that comprises a portside half wing and a starboard side half wing. Each one of the portside and starboard side half wings comprises an inboard section that is connected to the fuselage and an outboard section that forms a wing tip. The inboard sections of the portside and starboard side half wings form a central wing region. The portside and starboard side half wings are respectively connected in the region of their wing tips to an associated outboard wing pod that supports at least two non-tiltably mounted thrust producing units of the thrust producing units assembly.

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 rotor or propeller may have rotor blades and a passive pitch angle adjustment apparatus. The passive pitch angle adjustment apparatus may include levers, rods, and central rod. Levers may be connected to rotor blades and rotate them around a respective pitch axis. Rods may be connected to levers and mechanically link levers with each other via central point that is located outside rotor plane. Central rod may connect central point with base point that is located in a longitudinal direction of rotor axis. The passive pitch angle adjustment apparatus may enable a cyclic pitch adjustment of the rotor blades and block a collective pitch adjustment of the rotor blades.

Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight thrust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.

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: A rotor or propeller may have rotor blades and a passive pitch angle adjustment apparatus. The passive pitch angle adjustment apparatus may include levers, rods, and central rod. Levers may be connected to rotor blades and rotate them around a respective pitch axis. Rods may be connected to levers and mechanically link levers with each other via central point that is located outside rotor plane. Central rod may connect central point with base point that is located in a longitudinal direction of rotor axis. The passive pitch angle adjustment apparatus may enable a cyclic pitch adjustment of the rotor blades and block a collective pitch adjustment of the rotor blades.

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.