A motor integrated type fluid machine suctions a fluid from a suction port and discharges the suctioned fluid from a discharge outlet. The machine includes: a shaft portion provided at a center of a rotation axis; a rotating portion rotating around the shaft portion; an outer peripheral portion provided on an outer periphery of the shaft portion; and an outer peripheral drive motor rotating the rotating portion. The rotating portion includes a hub rotatably supported by the shaft portion, blades provided on an outer peripheral side of the hub and provided side by side in a circumferential direction of the rotation axis, and a rotating outer peripheral portion having an annular shape along the circumferential direction. A ratio of a rigidity of the rotating outer peripheral portion against a centrifugal force to a rigidity of the rotating portion against the centrifugal force is 50% to 95%.

A motor integrated type fluid machine suctions a fluid from a suction port and discharges the suctioned fluid from a discharge outlet. The machine includes: a shaft portion provided at a center of a rotation axis; a rotating portion rotating around the shaft portion; an outer peripheral portion provided on an outer periphery of the shaft portion; and an outer peripheral drive motor rotating the rotating portion. The rotating portion includes a hub rotatably supported by the shaft portion, blades provided on an outer peripheral side of the hub and provided side by side in a circumferential direction of the rotation axis, and a rotating outer peripheral portion having an annular shape along the circumferential direction. A ratio of a rigidity of the rotating outer peripheral portion against a centrifugal force to a rigidity of the rotating portion against the centrifugal force is 50% to 95%.

Flight equipment according to an embodiment of the present invention includes: an aerial vehicle having a body and at least one rotor held on the body; a plurality of supporters mounted to the aerial vehicle and supporting a protective member stretched therebetween so as to surround an outside of the body; a support information detection unit configured to detect support information indicating a support state of the protective member; and a mounting state determiner configured to determine whether the support state of the protective member is suitable or unsuitable, based on a value detected by the support information detection unit.

Flight equipment according to an embodiment of the present invention includes: an aerial vehicle having a body and at least one rotor held on the body; a plurality of supporters mounted to the aerial vehicle and supporting a protective member stretched therebetween so as to surround an outside of the body; a support information detection unit configured to detect support information indicating a support state of the protective member; and a mounting state determiner configured to determine whether the support state of the protective member is suitable or unsuitable, based on a value detected by the support information detection unit.

A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

A ducted fan of an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan radially at the outside and that defines a flow channel for air flowing via the fan. The stator-side duct has an inner wall facing toward the fan, an outer wall averted from the fan, and at least one stiffening strut that runs within the flow channel. The stiffening strut, at one respective end, extends through the duct and protrudes radially relative to the outer wall of the duct. At the respective end of the stiffening strut, a fastening device is formed. The fastening device is configured to mount the ducted fan on a structural component of the aircraft. The fastening device has an insert composed of a fiber-reinforced plastic and laminated into the respective end of the stiffening strut.

A ducted fan of an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan radially at the outside and that defines a flow channel for air flowing via the fan. The stator-side duct has an inner wall facing toward the fan, an outer wall averted from the fan, and at least one stiffening strut that runs within the flow channel. The stiffening strut, at one respective end, extends through the duct and protrudes radially relative to the outer wall of the duct. At the respective end of the stiffening strut, a fastening device is formed. The fastening device is configured to mount the ducted fan on a structural component of the aircraft. The fastening device has an insert composed of a fiber-reinforced plastic and laminated into the respective end of the stiffening strut.

Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.