Provided is a drone 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 driving the x-axis tilting mechanism unit; 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, and a wing part installed on an upper portion of the fuselage and formed in a form of an air foil to provide lift.

Provided is a drone 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 driving the x-axis tilting mechanism unit; 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, and a wing part installed on an upper portion of the fuselage and formed in a form of an air foil to provide lift.

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.

A long-distance drone having a main body, a left hind wing, a right hind wing, a left forewing, and a right forewing. There is a left linear support connecting the left forewing to the left hind wing, and a right linear support connecting the right forewing to the right hind wing. A plurality of propellers are disposed on the left and the right linear supports.

An aircraft that can improve cruising speed by making the body shape of the airframe (especially, multicopter) into a shape that has less unnecessary positive lift force by the main body and less drag in the cruising posture of the airframe. An aircraft equipped with a plurality of rotary blades including a propeller and a motor, wherein the aircraft comprises a main body with an inverted airfoil shape. The main body has an attack angle that does not generate a lift force or produces a negative lift force during cruising. The main body has a positive attack angle of 12 degrees or less. Further, it is provided with a mounting unit on which a mounted object can be mounted. The mounting unit is connected to the main body via the connection unit.

Provided is a parachute device capable of reliably opening a parachute. A parachute device includes a parachute, a parachute accommodation section formed in a tubular shape including an opening at one end and a bottom at another end, the parachute accommodation section being configured to accommodate the parachute inside the parachute accommodation section, at least one flying body formed in a tubular shape including an opening at one end and a bottom at another end, the flying body being connected to the parachute, a tubular ejection section fixed at the parachute accommodation section, and configured to hold the flying body and eject the held flying body, a gas generating device fixed at the parachute accommodation section, and configured to generate gas, and a gas introduction path configured to introduce the gas generated from the gas generating device to an interior of the ejection section, wherein at the ejection section, one open end portion of the ejection section is inserted into the flying body, and another open end portion of the ejection section communicates with the gas introduction path.

Eyewear configured to control an unmanned aerial vehicle (UAV). In one example, a user interacts with the eyewear to generate control signals that are transmitted to the UAV to control the flight path, speed, orientation, and to communicate other instructions to the UAV. An input of the eyewear is controlled by the user to control the UAV, such as a touchpad, a microphone, a head movement tracker and a camera. The user is also able to configure and customize the eyewear to send specific control signals to the UAV as a function of user actions. This includes specific head movements and head gestures of the user as a method of controlling the UAV. This allows the user to control the UAV in a more natural and convenient way.

A long-distance drone having a main body, a left hind wing, a right hind wing, a left forewing, and a right forewing. There is a left linear support connecting the left forewing to the left hind wing, and a right linear support connecting the right forewing to the right hind wing. A plurality of propellers are disposed on the left and the right linear supports.

A long-distance drone having a main body, a left hind wing, a right hind wing, a left forewing, and a right forewing. There is a left linear support connecting the left forewing to the left hind wing, and a right linear support connecting the right forewing to the right hind wing. A plurality of propellers are disposed on the left and the right linear supports.