An unmanned aerial vehicle comprises a housing, a plurality of first arms, a plurality of second arms, and a landing gear. The housing includes a gimbal attachment to couple a gimbal with a camera. Each of the plurality of first arms and the plurality of second arms rotatably couple with the housing at one end and has a motor coupled with a propeller on the other end. The landing gear includes a plurality of foldable legs and releasably couples with an underside of the housing. The aerial vehicle may be programmed with aerial flight path data that corresponds with a prior traced route.

The invention relates to a propulsion device comprising a platform that is arranged so as to accommodate a passenger and cooperates with a thrust unit comprising a main nozzle, advantageously oriented from the bow to the stern of the device, and two secondary nozzles that are lateral and are positioned essentially at the bow of the propulsion device. The secondary nozzles are mounted so as to be mobile about a transverse axis so as to be moved by actuators controlled by a processing unit that implements a method for controlling the secondary nozzles, thus providing automatic control assistance to the passenger.

The invention relates to a propulsion device comprising a platform that is arranged so as to accommodate a passenger and cooperates with a thrust unit comprising a main nozzle, advantageously oriented from the bow to the stern of the device, and two secondary nozzles that are lateral and are positioned essentially at the bow of the propulsion device. The secondary nozzles are mounted so as to be mobile about a transverse axis so as to be moved by actuators controlled by a processing unit that implements a method for controlling the secondary nozzles, thus providing automatic control assistance to the passenger.

A propulsion device, including a platform; a thrust assembly coupled to the platform, the thrust assembly including at least two nozzles configured to discharge a pressurized fluid therefrom that are movable with respect to the platform; a plurality of actuators, wherein each actuator is coupled to one of the at least two nozzles, wherein each actuator is configured to adjust an angular orientation of its respective nozzle with respect to the platform; a first sensor coupled to the platform to measure at least one of a pitch and roll of the platform; and a controller in communication with the first sensor and the plurality of actuators, wherein the controller is configured to adjust an operation of the actuators based at least in part on information from the first sensor to modify an angular orientation of the at least two nozzles.

A propulsion device, including a platform; a thrust assembly coupled to the platform, the thrust assembly including at least two nozzles configured to discharge a pressurized fluid therefrom that are movable with respect to the platform; a plurality of actuators, wherein each actuator is coupled to one of the at least two nozzles, wherein each actuator is configured to adjust an angular orientation of its respective nozzle with respect to the platform; a first sensor coupled to the platform to measure at least one of a pitch and roll of the platform; and a controller in communication with the first sensor and the plurality of actuators, wherein the controller is configured to adjust an operation of the actuators based at least in part on information from the first sensor to modify an angular orientation of the at least two nozzles.

Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

A flying machine includes: a flying machine body that includes a rotor blade; a protective member that forms a frame shape inside which the rotor blade is disposed, that is rotatably fixed to both end portions of the flying machine body, and that is pipe shaped; and a connecting wire that passes through an inner portion of the protective member to connect the flying machine body and an external device together.

A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.