An aerodyne comprises a fuselage, a fixed wing , a thruster for cruising flight, and a rotary wing for stages of vertical flight and held stationary during cruising flight. The rotary wing includes at least two contrarotating single-blades disposed at the top of the fuselage and hinged about respective axes perpendicular to the rotor axes of rotation. A maneuvering procedure for maneuvering the aerodyne includes a transition stage between a stage of vertical flight and a stage of cruising flight, wherein in the transition stage, when the speed of each single-blade is less than a threshold speed of rotation, the pitch of each single-blade is such that it no longer provides any lift force and the transverse hinge of the single-blade to its rotor axis is held locked in a position such that the single-blade is perpendicular to the rotor shaft.

A system for stowable propulsion in an electric aircraft that includes at least a propulsor mounted on at least a structural feature that includes at least a rotor and at least a motor mechanically coupled to the at least a rotor, where the motor is configured to cause the rotor to rotate as a function of an activation datum, at least a sensor communicatively coupled to the at least a propulsor configured to detect a position datum as a function of the configuration, generate a clearance datum as a function of the position datum, transmit the clearance datum to a flight controller, and a flight controller communicatively coupled to the at least a propulsor and the at least a sensor configured to receive the clearance datum from the at least a sensor and generate the activation datum as a function of the clearance datum.

A system for stowable propulsion in an electric aircraft that includes at least a propulsor mounted on at least a structural feature that includes at least a rotor and at least a motor mechanically coupled to the at least a rotor, where the motor is configured to cause the rotor to rotate as a function of an activation datum, at least a sensor communicatively coupled to the at least a propulsor configured to detect a position datum as a function of the configuration, generate a clearance datum as a function of the position datum, transmit the clearance datum to a flight controller, and a flight controller communicatively coupled to the at least a propulsor and the at least a sensor configured to receive the clearance datum from the at least a sensor and generate the activation datum as a function of the clearance datum.

A system for reducing air resistance in an electric aircraft flight that comprises at least a flight component connected to the electric aircraft and at least a sensor connected to the at least a flight component, wherein the at least a sensor is configured to detect a status datum of the at least a flight component and transmit the status datum to a computing device communicatively connected to a electric aircraft, wherein the computing device is configured to receive the status datum from the at least a sensor, generate an optimum position of the at least a flight component as a function of the status datum and initiate the optimum position of the at least a flight component.

The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

An aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode. The aircraft includes an airframe having a first wing and a first payload station. A distributed propulsion system that is coupled to the airframe includes a plurality of propulsion assemblies configured to provide vertical thrust in the vertical takeoff and landing flight mode and forward thrust in the forward flight mode. A control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. A payload module is configured to be transported by the airframe from a pickup location to a delivery location. The payload module is magnetically coupled to the first payload station during transportation and, responsive to a command from the control system, is magnetically decoupled from the first payload station at the delivery location.

An aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode. The aircraft includes an airframe having a first wing and a first payload station. A distributed propulsion system that is coupled to the airframe includes a plurality of propulsion assemblies configured to provide vertical thrust in the vertical takeoff and landing flight mode and forward thrust in the forward flight mode. A control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. A payload module is configured to be transported by the airframe from a pickup location to a delivery location. The payload module is magnetically coupled to the first payload station during transportation and, responsive to a command from the control system, is magnetically decoupled from the first payload station at the delivery location.

An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.

An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.