Provided is a drone with a multiple DOF flight mode according to the present invention. The drone may include: a fuselage in which a battery is mounted and a forward direction is set in an x-axis; a plurality of rotors disposed around the fuselage in four or more, each rotational axis of which is aligned in a z-axis direction; an x-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the x-axis; a y-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the y-axis; a first drive motor unit driving the y-axis tilting mechanism unit; a second drive motor unit guiding the x-axis tilting mechanism unit; and a control unit configured to implement a plurality of flight modes by controlling the first rotor, the second rotor, the third rotor, the fourth rotor, the first drive motor unit, and the second drive motor unit.

Provided is a control method of a drone with a multiple DOF flight mode according to the present invention. The drone may include a fuselage in which a battery is mounted and a forward direction is set in an x-axis, a plurality of rotors disposed about the fuselage in four or more, each rotational axis of which is aligned in a z-axis direction, an x-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the x-axis, a y-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the y-axis, a first drive motor unit driving the y-axis tilting mechanism unit, a second drive motor unit guiding the x-axis tilting mechanism unit, and a control unit configured to implement a plurality of flight modes by controlling the first rotor, the second rotor, the third rotor, the fourth rotor, the first drive motor unit, and the second drive motor unit.

An aerial vehicle comprising: at least three support arms for interconnecting at least three motors; at least one battery module; at least one of the support arms is configured to support the at least one battery module such that the battery module forms a structural element of the support arm.

An aerial vehicle comprising: at least three support arms for interconnecting at least three motors; at least one battery module; at least one of the support arms is configured to support the at least one battery module such that the battery module forms a structural element of the support arm.

The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

Provided is a protection device for protecting a sensor mounted on an unmanned aerial vehicle. The protection device includes a housing and a nozzle provided in the housing and connected to a container, and protects the sensor by discharging a content of the container from the nozzle. The protection device may further include an information acquisition unit for acquiring information from an outside, and discharge the content from the nozzle based on the information acquired by the information acquisition unit. The protection device may further include an environment detection unit configured to detect a change in environment, and discharge the content from the nozzle based on the change detected by the environment detection unit. The protection device may further include a foreign object detection unit configured to detect a foreign object, and discharge the content from the nozzle in response to the foreign object detection unit detecting the foreign object.

Provided is a protection device for protecting a sensor mounted on an unmanned aerial vehicle. The protection device includes a housing and a nozzle provided in the housing and connected to a container, and protects the sensor by discharging a content of the container from the nozzle. The protection device may further include an information acquisition unit for acquiring information from an outside, and discharge the content from the nozzle based on the information acquired by the information acquisition unit. The protection device may further include an environment detection unit configured to detect a change in environment, and discharge the content from the nozzle based on the change detected by the environment detection unit. The protection device may further include a foreign object detection unit configured to detect a foreign object, and discharge the content from the nozzle in response to the foreign object detection unit detecting the foreign object.

An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

The present invention addresses the problem of providing a flight vehicle that enables safe and easy test for continuity in structures. The flight vehicle 100 according to the present invention comprises: a flight vehicle body 110; a conductive member 120 for contact with the conductor of a structure; and a movement mechanism 130 capable of moving the conductive member 120 between distal and proximal positions with respect to the flight vehicle body 100. The movement mechanism 130 may be also provided with a support rod 130 that supports the conductive member 120, and a rod movement means 130b capable of moving the support rod 130 in the distal direction.

The present invention addresses the problem of providing a flight vehicle that enables safe and easy test for continuity in structures. The flight vehicle 100 according to the present invention comprises: a flight vehicle body 110; a conductive member 120 for contact with the conductor of a structure; and a movement mechanism 130 capable of moving the conductive member 120 between distal and proximal positions with respect to the flight vehicle body 100. The movement mechanism 130 may be also provided with a support rod 130 that supports the conductive member 120, and a rod movement means 130b capable of moving the support rod 130 in the distal direction.