An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

A supporting wing structure for an aircraft, in particular for a load-carrying and/or passenger-carrying aircraft, preferably an aircraft in the form of a vertical take-off and landing multicopter having a plurality of electrically driven rotors which are disposed in a distributed manner. The supporting wing structure has a plurality of struts. A first number of the struts are at least largely disposed in a first direction, while a second number of the struts are at least largely disposed in a second direction, the second direction being oriented orthogonal to the first direction. At least the struts of the second number have an aerodynamic profile in cross section, and/or in the struts are connected to one another at least in pairs between neighboring struts by a connecting structure, preferably from individual connecting segments, and the connecting structure or the connecting segments have an aerodynamic profiling. Furthermore an aircraft is provided equipped with such a supporting wing structure.

[Object] To provide a control device which enables a flight vehicle device to obtain a highly precise image.

[Solution] Provided is the control device including an illuminating control unit configured to adjust a light amount of an illuminating device according to an inclination of a fuselage of a flight vehicle device that has an imaging device configured to photograph a photographing target and the illuminating device configured to illuminate the photographing target.

A fail safety apparatus of the air mobility is provided. Locations of propeller modules are adjusted by rotation parts and length adjustment units to evenly distribute thrust of the re-located propeller modules so that the attitude of the air mobility is stabilized. In particular, when one propeller module among a plurality of propeller modules fails, the attitude of the air mobility is normalized by adjusting a location of the failed propeller module and locations of remaining normal propeller modules so that flight safety of the air mobility is secured.

A discharge apparatus for an aerial vehicle is provided which is capable of mounting an aerosol container by effectively utilizing a space outside an airframe.

The discharge apparatus for an aerial vehicle, in which a content is discharged through a nozzle from an aerosol container mounted on an airframe, is characterized in that the aerosol container is mounted outside the airframe, and is arranged so that a central axis of the aerosol container is along a pitch axis of the airframe, or arranged on an extension portion such as a small wing extending from a fuselage of the airframe, an arm portion provided with a rotor blade, a leg portion for taking off and landing, or the like, with the aerosol container and the nozzle being connected to each other through a tube.

A discharge apparatus for an aerial vehicle is provided which is capable of mounting an aerosol container by effectively utilizing a space outside an airframe.

The discharge apparatus for an aerial vehicle, in which a content is discharged through a nozzle from an aerosol container mounted on an airframe, is characterized in that the aerosol container is mounted outside the airframe, and is arranged so that a central axis of the aerosol container is along a pitch axis of the airframe, or arranged on an extension portion such as a small wing extending from a fuselage of the airframe, an arm portion provided with a rotor blade, a leg portion for taking off and landing, or the like, with the aerosol container and the nozzle being connected to each other through a tube.

An electric movable body includes an output shaft and multiple motors that drive the output shaft. The electric movable body performs a double drive control to assign a drive state to at least two of the motors, performs, when the double drive control is performed and on determination that one of the motors is abnormal, a single drive control to assign the drive state to only one of the motors and to assign a stop state to another of the motors, and identifies, when the single drive control is performed, a drive motor, to which the drive state is assigned and which is abnormal, based on a predetermined state quantity correlated with a drive state of the drive motor.

An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.

An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.