A landing platform for an unmanned aerial vehicle, including a plurality of substantially funnel-shaped centering housings configured to cooperate with a corresponding plurality of projections of the aerial vehicle for reaching a predetermined landing position. The platform can include a mechanism for recharging the battery of the aerial vehicle and/or with an arrangement for serial data transfer.

A rotorcraft together with a heat dissipation structure for a motor are provided. The motor includes a body and a revolving shaft driven by the body, and the heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which the body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the body and an inner wall of the casing; a head cover connected to the revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover.

A rotorcraft together with a heat dissipation structure for a motor are provided. The motor includes a body and a revolving shaft driven by the body, and the heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which the body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the body and an inner wall of the casing; a head cover connected to the revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover.

Aerial vehicles are provided with one or more transformable arms (110, 310, 410, 510, 910). The one or more transformable arms (110, 310, 410, 510, 910) may support one or more propulsion units, and transform between a flight configuration where the propulsion units of the arms effect flight of the aerial vehicle, and a landing configuration, wherein the transformable arms (110, 310, 410, 510, 910) are used as a landing support that bears weight of the aerial vehicle when the aerial vehicle is not in flight. Using the transformable arms (110, 310, 410, 510, 910) as legs when the UAV is in a landed state permits the UAV to reduce weight and reduce obstruction to a payload carried by the UAV when the UA is in flight.

Aerial vehicles are provided with one or more transformable arms (110, 310, 410, 510, 910). The one or more transformable arms (110, 310, 410, 510, 910) may support one or more propulsion units, and transform between a flight configuration where the propulsion units of the arms effect flight of the aerial vehicle, and a landing configuration, wherein the transformable arms (110, 310, 410, 510, 910) are used as a landing support that bears weight of the aerial vehicle when the aerial vehicle is not in flight. Using the transformable arms (110, 310, 410, 510, 910) as legs when the UAV is in a landed state permits the UAV to reduce weight and reduce obstruction to a payload carried by the UAV when the UA is in flight.

A connector, a built-in antenna structure, and an unmanned aerial vehicle using the built-in antenna structure. The unmanned aerial vehicle includes a body, and a support stand including a receiving rod. The built-in antenna structure includes a connector, a buffer and an antenna. The antenna and the buffer are received in the receiving rod, with the buffer wrapping the antenna. The connector is disposed between the receiving rod and the body to drive the receiving rod to rotate relative to the body. One end of the antenna protrudes from the connector and is electrically connected with the body. In an embodiment, the space occupied by the antenna is reduced, and the service life of the antenna and the overall appearance of the unmanned aerial vehicle are improved. Moreover, the angle of the receiving rod can be adjusted, for facilitating reception of signals by the antenna.

A connector, a built-in antenna structure, and an unmanned aerial vehicle using the built-in antenna structure. The unmanned aerial vehicle includes a body, and a support stand including a receiving rod. The built-in antenna structure includes a connector, a buffer and an antenna. The antenna and the buffer are received in the receiving rod, with the buffer wrapping the antenna. The connector is disposed between the receiving rod and the body to drive the receiving rod to rotate relative to the body. One end of the antenna protrudes from the connector and is electrically connected with the body. In an embodiment, the space occupied by the antenna is reduced, and the service life of the antenna and the overall appearance of the unmanned aerial vehicle are improved. Moreover, the angle of the receiving rod can be adjusted, for facilitating reception of signals by the antenna.

An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.

A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.

A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.