An unmanned and remotely controlled airship has a multirotor system combined with an inflatable envelope. The airship may be lifted/powered by a power system that has three or more rotors. The airship may be constructed using rods, connectors, the main system/control box and the rotors. The airship system may have a systemic symmetry for weight distribution and flight control and may be, for example, a symmetric ellipsoid envelope/blimp.

An unmanned and remotely controlled airship has a multirotor system combined with an inflatable envelope. The airship may be lifted/powered by a power system that has three or more rotors. The airship may be constructed using rods, connectors, the main system/control box and the rotors. The airship system may have a systemic symmetry for weight distribution and flight control and may be, for example, a symmetric ellipsoid envelope/blimp.

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 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.

The method for transporting a payload to a target location, comprises the following steps of providing a hybrid airship comprises a buoyancy enclosure, a gondola carried by the buoyancy enclosure and a payload carrier, and at least one propeller; flying the hybrid airship carrying the payload to a target location, flying the hybrid airship carrying the payload comprising generating a lift force with the at least one propeller. Flying the hybrid airship carrying the payload comprises tilting the longitudinal axis of the buoyancy enclosure to a positive pitch to generate an aerodynamic lift force when the hybrid airship carrying the payload moves longitudinally.

The method for transporting a payload to a target location, comprises the following steps of providing a hybrid airship comprises a buoyancy enclosure, a gondola carried by the buoyancy enclosure and a payload carrier, and at least one propeller; flying the hybrid airship carrying the payload to a target location, flying the hybrid airship carrying the payload comprising generating a lift force with the at least one propeller. Flying the hybrid airship carrying the payload comprises tilting the longitudinal axis of the buoyancy enclosure to a positive pitch to generate an aerodynamic lift force when the hybrid airship carrying the payload moves longitudinally.

Disclosed are an unmanned aerial vehicle (UAV) having a buoyancy apparatus and an attitude control method thereof, in which the buoyancy apparatus is coupled to the UAV to reduce the energy consumption of rotors such that the time of staying in the air is extended, enabling a long flight, and in which the buoyancy apparatus absorbs the impact energy and reduces the falling speed to thereby ensure sufficient safety for the UAV.

Disclosed are an unmanned aerial vehicle (UAV) having a buoyancy apparatus and an attitude control method thereof, in which the buoyancy apparatus is coupled to the UAV to reduce the energy consumption of rotors such that the time of staying in the air is extended, enabling a long flight, and in which the buoyancy apparatus absorbs the impact energy and reduces the falling speed to thereby ensure sufficient safety for the UAV.