A power package includes a motor and at least one of a propeller or a propeller mounting structure. The propeller mounting structure is configured to detachably mount the propeller at the motor and includes a mounting seat configured to be fixed at an end surface of the motor and rotationally engage with the propeller, a lock member, and an elastic member configured to apply an elastic force to the lock member along an axial direction of a motor shaft of the motor to cause at least part of the lock member to block the propeller from being disengaged from the mounting seat. The motor shaft passes through the mounting seat. The propeller includes a connection assembly and a blade disposed at the connection assembly. The connection assembly is configured to mount at the motor shaft and includes an annular connector configured to rotationally engage with the propeller mounting structure.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more engines or motors are disposed within or attached to the closed wing, fuselage or spokes. Three or more propellers are proximate to a leading edge of the closed wing or the one or more spokes, distributed along the closed wing or the one or more spokes, and operably connected to the one or more engines or motors. The propellers provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more engines or motors are disposed within or attached to the closed wing, fuselage or spokes. Three or more propellers are proximate to a leading edge of the closed wing or the one or more spokes, distributed along the closed wing or the one or more spokes, and operably connected to the one or more engines or motors. The propellers provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.

Systems and methods for a vehicle-compatible drone. In one embodiment, a computer-implemented method includes providing a drone having a plurality of blades and an expansion device. The expansion device is adapted to reconfigure the position of at least one blade of the plurality of blades from a first configuration of the drone to a second configuration of the drone. The computer-implemented method also includes identifying the drone being in a first mode that is associated with the first configuration. The computer-implemented method further includes detecting a trigger signal based on an event. The computer-implemented method includes transmitting a transition signal configured to cause the drone to transition to the second mode that is associated with the second configuration.

Systems and methods for a vehicle-compatible drone. In one embodiment, a computer-implemented method includes providing a drone having a plurality of blades and an expansion device. The expansion device is adapted to reconfigure the position of at least one blade of the plurality of blades from a first configuration of the drone to a second configuration of the drone. The computer-implemented method also includes identifying the drone being in a first mode that is associated with the first configuration. The computer-implemented method further includes detecting a trigger signal based on an event. The computer-implemented method includes transmitting a transition signal configured to cause the drone to transition to the second mode that is associated with the second configuration.

Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.

A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.

An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.

An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.