A method of controlling a hybrid power unit includes receiving a target total thrust value that is converted into a target speed for a propeller. The target speed is transmitted to a motor speed controller. A sensor value for a current speed for the propeller is received at the motor speed controller. The motor speed controller generates a signal to a primary electric motor to selectively output torque to a rotor and regeneratively brake the rotor according to the target speed. A module current set point based at least in part on a state of charge of a battery is received. A throttle set point is determined based in part on the target speed and the module current set point. A throttle set point of an internal-combustion engine of the hybrid power unit is adjusted based at least in part on the target speed and the module current set point.

A method of controlling a hybrid power unit includes receiving a target total thrust value that is converted into a target speed for a propeller. The target speed is transmitted to a motor speed controller. A sensor value for a current speed for the propeller is received at the motor speed controller. The motor speed controller generates a signal to a primary electric motor to selectively output torque to a rotor and regeneratively brake the rotor according to the target speed. A module current set point based at least in part on a state of charge of a battery is received. A throttle set point is determined based in part on the target speed and the module current set point. A throttle set point of an internal-combustion engine of the hybrid power unit is adjusted based at least in part on the target speed and the module current set point.

A cooling system includes a rotor (VTOL rotor, cruise rotor) for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a cooling circuit for cooling the component group, wherein a plurality of the component groups corresponding to a plurality of the rotors are provided, and the plurality of component groups are cooled by the same cooling circuit.

A cooling system includes a rotor (VTOL rotor, cruise rotor) for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a cooling circuit for cooling the component group, wherein a plurality of the component groups corresponding to a plurality of the rotors are provided, and the plurality of component groups are cooled by the same cooling circuit.

Provided is an electric propulsion device 106 including a propeller 131 and a motor 121 for rotating the propeller, wherein the propeller includes a rotary boss 132 secured to a rotating shaft 123 of the motor, and blades 133 protruding radially outward from the rotary boss. Further, the blades include a base end portion with an airfoil continuously changing such that a trailing edge comes to be in parallel to the rotating shaft of the motor from a radially outer side to the rotary boss, in a vicinity of the rotary boss.

Provided is an electric propulsion device 106 including a propeller 131 and a motor 121 for rotating the propeller, wherein the propeller includes a rotary boss 132 secured to a rotating shaft 123 of the motor, and blades 133 protruding radially outward from the rotary boss. Further, the blades include a base end portion with an airfoil continuously changing such that a trailing edge comes to be in parallel to the rotating shaft of the motor from a radially outer side to the rotary boss, in a vicinity of the rotary boss.

Various embodiments of the present disclosure provide a rotorcraft-assisted system and method for launching and retrieving a fixed-wing aircraft into and from free flight. The launch and retrieval system includes a modular multicopter, a storage and launch system, an anchor system, a flexible capture member, and an aircraft-landing structure. The multicopter is attachable to the fixed-wing aircraft to facilitate launching the fixed-wing aircraft into free, wing-borne flight. The storage and launch system is usable to store the multicopter (when disassembled) and to act as a launch mount for the fixed-wing aircraft by retaining the fixed-wing aircraft in a desired launch orientation. The anchor system is usable with the multicopter, the flexible capture member, and the aircraft-landing structure to retrieve the fixed-wing aircraft from free, wing-borne flight.

Various embodiments of the present disclosure provide a rotorcraft-assisted system and method for launching and retrieving a fixed-wing aircraft into and from free flight. The launch and retrieval system includes a modular multicopter, a storage and launch system, an anchor system, a flexible capture member, and an aircraft-landing structure. The multicopter is attachable to the fixed-wing aircraft to facilitate launching the fixed-wing aircraft into free, wing-borne flight. The storage and launch system is usable to store the multicopter (when disassembled) and to act as a launch mount for the fixed-wing aircraft by retaining the fixed-wing aircraft in a desired launch orientation. The anchor system is usable with the multicopter, the flexible capture member, and the aircraft-landing structure to retrieve the fixed-wing aircraft from free, wing-borne flight.

To provide an aircraft having improved efficiency and flexibility of the airframe configuration when installing a functional part in the airframe, and a power unit having a configuration for the improved efficiency and flexibility. To provide an aircraft, comprising: a power unit having a first space open at least one of its upper or lower surface; a propeller having a first through-space and connected to the power unit; and a functional part having a predetermined function and located at least partially in an internal space formed by the first space and the first through-space.

To provide an aircraft having improved efficiency and flexibility of the airframe configuration when installing a functional part in the airframe, and a power unit having a configuration for the improved efficiency and flexibility. To provide an aircraft, comprising: a power unit having a first space open at least one of its upper or lower surface; a propeller having a first through-space and connected to the power unit; and a functional part having a predetermined function and located at least partially in an internal space formed by the first space and the first through-space.