[Objective] To provide, as to an aerial vehicle equipped with a multicopter mechanism, an aerial vehicle having both a vertical take-off and landing function and a horizontal cruise function and having an excellent cruising performance.

[Solving Means] In order to accomplish the above-mentioned objective, an aerial vehicle according to an embodiment of the present invention includes a propulsion unit and a fuselage unit. The propulsion unit includes a rotary shaft extending in a first direction and thrust producing mechanisms provided at both ends of the rotary shaft and produces a propulsion force for flying in air. The fuselage unit is suspended from the propulsion unit below the rotary shaft, has a center of gravity at a position below the rotary shaft, is configured to be freely rotate around the rotary shaft, and is capable of storing an article.

An unmanned rotorcraft has a lift module having a propulsion system and coaxial rotors driven in rotation by the propulsion system. The rotorcraft includes a payload support system adapted to couple an external payload directly to the lift module. The rotorcraft is devoid of provisions for human passengers.

The disclosure provides a fixed wing UAV, with two propulsion propellers arranged parallel to each other and providing thrust for the UAV, or two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two propulsion propellers or the two traction propellers respectively, wherein the thrust ratio provided by the two propulsion propellers or the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.

A lift assembly that is releasably fastened to a fuselage of a rotorcraft. The lift assembly comprises a wing comprising at least two spars. A main gearbox passes through an opening in the suction side of a central box of the wing so that its bottom is attached to a resilient suspension system arranged level with the pressure side of the central box, a top of the main gearbox projecting from the central box and being fastened to at least one spar by at least three suspension bars. A reversible fastener system having a plurality of fastener means serves to fasten the central box reversibly to a plurality of fastener points of a fuselage.

An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations.

A passenger module that may be connected to an aircraft for transport, and may be detached and attach different module for carriage to a different destination. In alternative embodiments involving different aircrafts such as fixed wing and helicopter aircraft, a module may be adapted to have a transparent exterior so that passengers may have a broad range of unobstructed view of the outside surroundings. The module may have a range of free movements while still connected to the aircraft for such purposes as sightseeing.

Systems and methods for extending the interior cargo bay of fixed-wing cargo aircraft into a replaceable tailcone bay are disclosed. The system includes an aircraft and a removable tailcone configured couple to the aft end of the fuselage. The aircraft fuselage includes a cargo bay and an aft end opening into the cargo bay. The tailcone, when attached, encloses the aft end opening the cargo bay. The tailcone can include an interior volume configured to extend the fuselage cargo bay such that the interior volume defines an aft end of a cargo bay of the cargo aircraft. In some examples, the tailcone includes a plurality of segments, which can be configured to extend from the aft end of the aircraft to adjust a length of the cargo extension provided by the tailcone.

A rotor mounting boom assembly includes a rotor mounting boom releasably attachable to a wing of the personal aircraft, one or more vertical lift rotors, and one or more rotor controller assemblies. Controller assemblies for each rotor are positioned on the rotor mounting booms such that downwash from the rotor causes increased airflow across the controller assembly to cool the controller assembly components. A rotor controller enclosure includes an air inlet and an air outlet to allow airflow through the enclosure to cool the controller components. The air inlet is positioned relative to the path of the rotor blades such that the downwash from the rotor that flows into the air inlet is maximized. The structure of the enclosure includes features for increasing the airflow through the enclosure.

A UAV with vertical takeoff and landing (VTOL) function having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.

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.