An unmanned aerial vehicle (UAV) includes a vehicle body and a multi-ocular imaging assembly. The multi-ocular imaging assembly includes at least two imaging devices disposed in and fixed to the vehicle body.

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.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extending from the central body. Each of the plurality of arms supports one or more propulsion units. At least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight. The at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extending from the central body. Each of the plurality of arms supports one or more propulsion units. At least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight. The at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.

A signal line protection assembly of an aerial vehicle includes a foot stand and a protection sleeve. The foot stand includes a foot stand sleeve and a lower cover including an antenna compartment configured to receive an antenna of the aerial vehicle. The protection sleeve is configured to receive a signal line. At least a portion of the protection sleeve is received in the foot stand sleeve. The signal line includes a data line for the antenna.

A signal line protection assembly of an aerial vehicle includes a foot stand and a protection sleeve. The foot stand includes a foot stand sleeve and a lower cover including an antenna compartment configured to receive an antenna of the aerial vehicle. The protection sleeve is configured to receive a signal line. At least a portion of the protection sleeve is received in the foot stand sleeve. The signal line includes a data line for the antenna.

According to one implementation, a landing gear of a rotorcraft includes two skid tubes and a cross tube. The cross tube couples the skid tubes to each other and attaches the skid tubes to a fuselage of the rotorcraft. At least a part of the cross tube is made of a composite material so that it becomes possible to achieve both sufficient absorption of energy and preventing the fuselage from coming into contact with a ground surface, at the time of landing the rotorcraft, under a more satisfactory condition. Further, according to one implementation, a rotorcraft includes the above-mentioned landing gear so that it becomes possible to achieve both sufficient absorption of energy and preventing a fuselage from coming into contact with a ground surface, at the time of landing the rotorcraft, under a more satisfactory condition.

In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.

In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.

Aerial vehicles may be configured to control their attitudes by changing one or more physical attributes. For example, an aerial vehicle may be outfitted with propulsion motors having repositionable mounts by which the motors may be rotated about one or more axes, in order to redirect forces generated by the motors during operation. An aerial vehicle may also be outfitted with one or more other movable objects such as landing gear, antenna and/or engaged payloads, and one or more of such objects may be translated in one or more directions in order to adjust a center of gravity of the aerial vehicle. By varying angles by which forces are supplied to the aerial vehicle, or locations of the center of gravity of the aerial vehicle, a desired attitude of the aerial vehicle may be maintained irrespective of velocity, altitude and/or forces of thrust, lift, weight or drag acting upon the aerial vehicle.