A rotor system for aerial vehicles where two or more rotor systems are used in a coaxial or tandem arrangement on the aerial vehicle.

A motor mounted on a drone includes a rotor including a propeller mounting portion with a propeller detachably attached, the rotor being rotatable about a central axis, a stator radially facing the rotor with a gap therebetween, and an auto-balancer capable of automatically correcting dynamic balance of the rotor.

A flight permitted airspace setting device has a memory and a processor. The memory stores information of first unmanned flight vehicle including first information enabling first-unmanned-flight-vehicle identification, first identification information enabling identification of a first user of a first communication service, and first airspace information about airspace in which the first unmanned flight vehicle flies. The memory also stores corresponding second-unmanned-flight-vehicle information. The processor that transmits first control information to the first unmanned flight vehicle to control a flight state of the first unmanned flight vehicle by using the first identification information when the first unmanned flight vehicle is flying, and transmits second control information to the second unmanned flight vehicle to control a flight state of the second unmanned flight vehicle by using second identification information of a second user when the second unmanned flight vehicle is flying.

A two degrees of freedom actuator for example for multi-bladed rotor of an aircraft with at least two blades that are driven in rotation about a main rotation axis by primary actuator, and a secondary actuator that is arranged to rotate each of said blades about the respective blades' longitudinal axis, with a synchronization means that is operatively arranged for driving the secondary actuator based on an azimuth of the rotor about the main axis for obtaining a determined cyclic pitch of a given amplitude for each blade depending on the azimuth of the rotor.

A vertical take-off and landing aerial vehicle (VTOL) includes a plurality of rotors for producing lift. For each respective rotor the VTOL has an auxiliary power source (APS) and a transformation gear set (TGS) both being associated with the respective rotor, and the VTOL further includes at least one main power source (MPS). Each TGS is configured to form an outgoing power towards its respective rotor from input powers received into the TGS from the MPS and from the APS associated with the respective rotor.

Techniques and architecture are disclosed for a multirotor vehicle having a rotor assembly with a plurality of rotors to provide upward thrust. Attached to the rotor assembly is a frame that includes a frame extension having a first end pivotally attached to the rotor assembly. The extension also includes a second end pivotally attached to a frame body. The vehicle further includes first and second actuators. The first actuator pivots the rotor assembly to position it within a horizontal plane to allow thrust generated by the rotor assembly to lift the vehicle. The second actuator pivots the rotor assembly within the horizontal plane so that thrust generated by the rotor assembly lifts the vehicle. The vehicle also includes a harness connected to the frame and configured to secure an operator's torso to the multirotor vehicle.

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

Systems and methods to reduce aerodynamic drag and/or affect flight characteristics of an aerial vehicle may include adjustable fairings associated with one or more components of the aerial vehicle. The adjustable fairings may be coupled to and at least partially surround a motor, propulsion mechanism, motor arm, strut, or other component of an aerial vehicle. In addition, the adjustable fairings may be passively movable between two or more positions responsive to airflow around the fairings, and/or the adjustable fairings may be actively moved between two more positions to affect flight characteristics. Further, the adjustable fairings may include actuatable elements to alter a portion of an outer surface of the fairings to thereby affect flight characteristics. In this manner, adjustable fairings associated with various components of an aerial vehicle may reduce aerodynamic drag and/or may improve control and safety of an aerial vehicle.

An unmanned flight vehicle includes a rotor, a motor rotating the rotor, and a control device controlling the motor and the vehicle. The control device has a memory storing identification information enabling identification of a user of a communication service for receiving first control information or airspace information about an airspace in which the flight vehicle flies via a wireless base station by the unmanned flight vehicle. The control device also has a processor controlling the vehicle to communicate with the wireless base station based on the stored identification information. The processor controls i) a flight state of the vehicle based on the first control information or the airspace information received via the wireless base station by using the identification information, and ii) the vehicle based on a quality of a radio wave that the vehicle has received from the wireless base station.

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.