[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 body 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.

An unmanned aerial vehicle comprises a housing, a plurality of first arms, a plurality of second arms, and a landing gear. The housing includes a gimbal attachment to couple a gimbal with a camera. Each of the plurality of first arms and the plurality of second arms rotatably couple with the housing at one end and has a motor coupled with a propeller on the other end. The landing gear includes a plurality of foldable legs and releasably couples with an underside of the housing. The aerial vehicle may be programmed with aerial flight path data that corresponds with a prior traced route.

A fixed-wing aerial underwater vehicle includes a shell component, a flight component and a pneumatic buoyancy component. The flight component includes a fixed wing and rotors, and the fixed wing and the rotors are mounted in the shell component. The pneumatic buoyancy component includes an air bladder and an inflation and deflation portion, and the inflation and deflation portion can inflate and deflate the air bladder. The air bladder is installed on the shell component, a containing space is formed in the shell component, and the inflation and deflation portion is partially or entirely installed in the containing space. Each rotor includes a rotor supporting rod, a motor base, a motor and a propeller, which are sequentially connected. A control method for the fixed-wing aerial underwater vehicle mentioned above is further provided.

A thrust producing unit with a fail-safe electrical drive unit that drives a rotor of a rotary-wing aircraft. Fail-safe electrical drive unit may include input shafts, fixedly attached belt pulleys that are fixedly attached to the respective input shafts, output shaft that is coupled to rotor, freewheeling belt pulleys that are mounted to output shaft by means of respective freewheels such that output shaft rotates freely when output shaft rotates faster than one of the freewheeling belt pulleys belts that connect fixedly attached belt pulleys with the respective freewheeling belt pulleys, and electric motors that are coupled with the respective input shafts.

An assembly for an aerial system includes a wing support foldably connected to a first and second side of a body of the aerial system, a protection structure coupled to the wing support and disposed over propellers coupled to the wing support, wherein at least one of the protection structure and the wing support includes at least one of a positioning hook and a positioning groove, wherein the protection structure and wing support are fixed relative to each other with the at least one of the positioning hook and the positioning groove.

An unmanned aerial vehicle includes a fuselage body, a foldable wing assembly and a gear assembly. The foldable wing assembly, including a pair of opposing wing members, is coupled to the fuselage body and positionable in a stowed position and a deployed position. The gear assembly positions the wing members in a stowed position and a deployed position and include a support bracket assembly and a pair of opposing hinge members. The support bracket assembly is coupled to the fuselage body and including first and second support brackets forming a cavity therebetween and a pair of opposing hinge members. The pair of opposing hinge members are pivotably coupled to the support bracket assembly and positioned within the cavity. Each hinge member is coupled to a corresponding wing member and includes a set of gear teeth extending outwardly from an arcuate radially outer surface and coupled in a meshed arrangement.

An electronic vertical takeoff and landing (eVTOL) multicopter which includes a communications interface configured to establish a communication channel between a site local server and the eVTOL multicopter and send a vehicle identifier and vehicle state information from the eVTOL multicopter to the site local server. The eVTOL multicopter also includes a processor configured to perform a management operation received from the site local server, wherein the site local server is configured to determine the management operation based at least in part on the vehicle identifier and the vehicle state information.

Methods and apparatus for performing repair operations using an unmanned aerial vehicle (UAV). A UAV carries a repair patch ensemble containing all repair materials (including a repair patch, a heating blanket and other ensemble materials) in a prepackaged form to the repair area. During flight of the UAV, the repair patch is vacuum adhered to the heating blanket. Vacuum pressure is also used to hold the repair patch ensemble in position on the composite surface of the structure. Then the hot bond process is enacted to bond the repair patch to the repair area. In accordance with one embodiment, the hot bond process involves heating the repair patch to adhesively bond the repair patch while applying vacuum pressure to consolidate the composite material. Then the repair patch is released from the ensemble and residual ensemble materials (heating blanket, bleeder material, and release films) are removed by the UAV.

A drone for replacing a removeable device can include a drone body with at least three lift-generating rotors spaced apart from the drone body and operating in concert that provide lift sufficient to propel the drone in at least six directions. The drone can include a first bay attached to the drone body, the first bay comprising a first mounting mechanism to dismount a first removeable device from a device receptacle and to securely stow the first removeable device. The drone can also include a second bay attached to the drone body comprising a second mounting mechanism to stow a second removeable device and to mount the second removeable device on the device receptacle.

A method for controlling movement of a drone is disclosed. A spatial vector between a flight-capable drone and a reference object is computed. The spatial vector defines a direction and a distance by which the drone is spaced from the reference object. Flightpath attributes based on the computed vector are determined. The flightpath attributes include one or more of a flight direction, a flight distance, and a flight speed. The flight direction is variable as a function of the direction of the spatial vector. The flight distance is variable as a function of the distance of the spatial vector. The flight speed is variable as a function of the distance of the spatial vector. In an automated operation, movement of the drone is controlled according to the determined flightpath attributes.