A device for controlling thrust vectoring of a cyclorotor includes a control cam positionable relative to a drive shaft of a cyclorotor along each of a first axis and a second axis, where the drive shaft is rotatable about a third axis. The device may further include a frame having a plurality of sides, where the frame is disposed at least partly around the drive shaft of the cyclorotor, a first positioning assembly disposed on a first side of the frame, where the first positioning assembly is structurally configured to move the frame along the first axis, and a second positioning assembly disposed on a second side of the frame, where the second positioning assembly is engaged with the control cam and structurally configured to move the control cam relative to the frame along the second axis.

A hybrid VTOL vehicle having an envelope configured to provide hydrostatic buoyancy, a fuselage attached to the envelope and having at least one pair of wings extending from opposing sides thereof to produce dynamic lift through movement, and a thrust generation device on each wing and configured to rotate with each wing about an axis that is lateral to a longitudinal axis of the envelope to provide vertical takeoff or landing capabilities. Ideally, the envelope provides negative hydrostatic lift to enhance low-speed and on-the-ground stability. A vehicle comprising a first lift device capable of providing hydrostatic lift; a second lift device capable of providing dynamic lift through movement; and a system structured to generate thrust coupled to the second lift device, the second lift device and the thrust generation system capable of rotating together about an axis that is lateral to a longitudinal axis of the vehicle at angles at least in the range of 90 degrees to and including 180 degrees.

A hybrid VTOL vehicle having an envelope configured to provide hydrostatic buoyancy, a fuselage attached to the envelope and having at least one pair of wings extending from opposing sides thereof to produce dynamic lift through movement, and a thrust generation device on each wing and configured to rotate with each wing about an axis that is lateral to a longitudinal axis of the envelope to provide vertical takeoff or landing capabilities. Ideally, the envelope provides negative hydrostatic lift to enhance low-speed and on-the-ground stability. A vehicle comprising a first lift device capable of providing hydrostatic lift; a second lift device capable of providing dynamic lift through movement; and a system structured to generate thrust coupled to the second lift device, the second lift device and the thrust generation system capable of rotating together about an axis that is lateral to a longitudinal axis of the vehicle at angles at least in the range of 90 degrees to and including 180 degrees.

A lighter than air craft having an airframe that has at least one tank in the airframe for holding compressed or liquid hydrogen or helium and at least one compartment in the airframe holding an inflatable bladder. The inflatable bladder can be inflated with hydrogen or helium gas from the first tank. There is a vent in the compartment allowing air to exit the compartment when the bladder is inflated and allowing air to enter the compartment when the bladder is deflated. Inflating and deflating the bladder partially controls buoyancy of the craft. Inflating bladders in compartments fore and aft controls pitch and trim.

A lighter than air craft having an airframe that has at least one tank in the airframe for holding compressed or liquid hydrogen or helium and at least one compartment in the airframe holding an inflatable bladder. The inflatable bladder can be inflated with hydrogen or helium gas from the first tank. There is a vent in the compartment allowing air to exit the compartment when the bladder is inflated and allowing air to enter the compartment when the bladder is deflated. Inflating and deflating the bladder partially controls buoyancy of the craft. Inflating bladders in compartments fore and aft controls pitch and trim.

A falling-resistant and anti-drifting unmanned aerial vehicle has a main body and at least one rotor wing thereon. Both sides of the main body have a wing with an airbag filled with gas lighter than air. Bulges protruding downwards are arranged at the bottoms of the airbag. The two airbags are at the same height symmetrically arranged based on the main body. The airbag can function as an undercarriage when the aircraft lands down, and as a buffer when crash landing and then reduce damage to the main body. If the aircraft falls in water, the aircraft can float on the water to avoid damage caused by sinking. As bulges protruding downwards are arranged at the bottoms of the airbags, in spraying operation, side wing can be relatively well baffled by the bulges in case of side wing blowing in the flying process, resulting in less droplets draft.

A falling-resistant and anti-drifting unmanned aerial vehicle has a main body and at least one rotor wing thereon. Both sides of the main body have a wing with an airbag filled with gas lighter than air. Bulges protruding downwards are arranged at the bottoms of the airbag. The two airbags are at the same height symmetrically arranged based on the main body. The airbag can function as an undercarriage when the aircraft lands down, and as a buffer when crash landing and then reduce damage to the main body. If the aircraft falls in water, the aircraft can float on the water to avoid damage caused by sinking. As bulges protruding downwards are arranged at the bottoms of the airbags, in spraying operation, side wing can be relatively well baffled by the bulges in case of side wing blowing in the flying process, resulting in less droplets draft.

A highly maneuverable craft, which may be lighter-than-air, is disclosed, having undulating fins of a light-weight material that may undulate along the horizontal axis of the craft and/or rotate 360 degrees and continuously about the central longitudinal axis of the craft. The fins may be actuated by motors coupled to the fins and coupled to the exterior of the craft via circumferential bands. Motion of the fins creates aerodynamic thrust. The circumferential bands may serve as tracks or channels along which the motors run, allowing the motors to travel 360 degrees or travel continuously around the exterior of the craft and thereby draw the fins about the craft. The circumferential bands may serve as reinforcing components, allowing the motors to exert torque against the body of the craft which may be thin-walled for maximum positive buoyancy. An on-board battery may power the motors via electrical circuits extending around the bands. The position and travel of the motors about the bands may be controlled by a central processing unit. A moveable weight, such as on a track with a motor, may be incorporated into or onto the craft for additional pitch control.

A highly maneuverable craft, which may be lighter-than-air, is disclosed, having undulating fins of a light-weight material that may undulate along the horizontal axis of the craft and/or rotate 360 degrees and continuously about the central longitudinal axis of the craft. The fins may be actuated by motors coupled to the fins and coupled to the exterior of the craft via circumferential bands. Motion of the fins creates aerodynamic thrust. The circumferential bands may serve as tracks or channels along which the motors run, allowing the motors to travel 360 degrees or travel continuously around the exterior of the craft and thereby draw the fins about the craft. The circumferential bands may serve as reinforcing components, allowing the motors to exert torque against the body of the craft which may be thin-walled for maximum positive buoyancy. An on-board battery may power the motors via electrical circuits extending around the bands. The position and travel of the motors about the bands may be controlled by a central processing unit. A moveable weight, such as on a track with a motor, may be incorporated into or onto the craft for additional pitch control.

The present invention relates to a hydrogen recycling flight system and flight method, the hydrogen recycling flight system including: a flight fuselage which has at least one pair of wings at each of both sides of a body; a hydrogen gas balloon which is air-tightly connected to the flight fuselage; a hydrogen fuel cell which is connected with the hydrogen gas balloon and is installed outside or inside the flight fuselage; and a secondary battery which is charged with electricity generated from the hydrogen fuel cell, electricity generated from a solar cell provided at an outer peripheral portion of the flight fuselage, or electricity of an external power network, in which by using a switch, the hydrogen fuel cell is switched to a water electrolysis device or the water electrolysis device is switched to the hydrogen fuel cell, the hydrogen recycling flight system includes: a water tank which stores water generated from the hydrogen fuel cell; the water electrolysis device which electrolyzes the stored water; a switch control device which switches functions of the hydrogen fuel cell and the water electrolysis device; and a high-pressure gas barrel which high-pressure stores hydrogen gas and oxygen gas generated in the water electrolysis device, and the flight fuselage flies by controlling the volume of the hydrogen gas balloon that is flotation power of a flight vehicle by an operation of the hydrogen fuel cell or the high-pressure gas barrel.