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 system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.

An aircraft that can fly stably when water is discharged from a hose installed on the airframe, and an aircraft system, are provided. The aircraft system can include a master aircraft, slave aircrafts and a remote control device. The aircraft preferably fly as a unit. Each slave aircraft can include four rotary blade portions having propellers, and a suspending means for suspending a part of a hose. The master aircraft may include four first rotary blade portions having first propellers arranged to rotate in a horizontal plane, four second rotary blade portions having second propellers arranged to rotate in a vertical plane, and a nozzle on which a tip end part of the hose is installed. The direction of the center axis of the nozzle is parallel to the direction of the rotational axes of the second propellers.

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.

The invention concerns an airborne device comprising at least three supporting wings and a linking device, the wings being linked to each other by first flexible cables, each wing being further linked to the linking device by a second flexible cable, the linking device being linked to a third flexible cable intended to be linked to a base, the first second, and third cables being tensioned when the airborne device is carried in the wind.

A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

The present invention discloses a wirelessly controlled vehicle that is configured to travel in air, on liquid and under liquid with an ability to communicate with a remote operator through wireless communication.

An unmanned aerial vehicle (UAV) is provided for the lifting and carrying payloads of up to 100 kg. The UAV can include a pair of counter-rotating propellers enclosed in a cage with attitude control motors for providing directional thrust mounted on the top of the cage. One or more motors can rotate the propellers via co-axially concentric vertical output shafts. The motor can include an internal combustion motor or an electric motor.

An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.

The present application provides methods and systems for launching an unmanned aerial vehicle (UAV). An exemplary system for launching a UAV includes a detector configured to detect acceleration of the UAV in a launch mode. The exemplary system may also include a memory storing instructions and a processor configured to execute the instructions to cause the system to: obtain a signal configured to notify the UAV to enter the launch mode, determine whether the acceleration of the UAV satisfies a condition corresponding to threshold acceleration in the launch mode, and responsive to the determination that the acceleration of the UAV satisfies the condition, turn on a motor of the UAV.