초록 ▼

The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servo motors and each of the plurality of the servo motors is connected to each of the plurali

The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servo motors and each of the plurality of the servo motors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servo motors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft.

대표청구항 ▼

1. An unmanned aerial vehicle comprising: a hemispherical body;a brushless type electrical motor mounted on top of the hemispherical body;a propeller attached to the brushless type electrical motor;a plurality of wingtip devices arranged around the hemispherical body;a plurality of servo motors conn

1. An unmanned aerial vehicle comprising: a hemispherical body;a brushless type electrical motor mounted on top of the hemispherical body;a propeller attached to the brushless type electrical motor;a plurality of wingtip devices arranged around the hemispherical body;a plurality of servo motors connected to the plurality of the wingtip devices and wherein each of the plurality of the servo motors is connected to each of the plurality of the wingtip devices respectively;a control system to regulate an operation of the plurality of the servo motors;a plurality of carbon rods attached to the hemispherical body to protect the plurality of the wingtip devices from a damage during a take-off and a landing operation; anda casing arranged inside the hemispherical body to accommodate the control system, a surveillance unit, a radio receiver, a battery unit for the radio receiver, a lithium polymer battery, a piezoelectric gyroscope, a rotation speed control motor and a battery for the surveillance unit;wherein the brushless type electrical motor provides a lifting force for a vertical take-off and landing (VTOL) and wherein the plurality of wing tip devices are classified into three types of wing tip devices and wherein three types of wing tip devices are controlled by the respective servo motors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of the aerial vehicle. 2. The unmanned aerial vehicle according to claim 1, wherein the first wing type devices control a movement of the aircraft in a yaw direction, the second wing type devices control a movement of the aircraft in a roll direction and the third wing type devices control a movement of the aircraft in a pitch direction. 3. The unmanned aerial vehicle according to claim 1, wherein the control mechanism regulates an operation of the plurality of the servo motors to changes an angle of the plurality of the wingtip devices against a downward air flow of the propeller to adjust the yaw, pitch and roll movements to stabilize and control the movement of the aerial vehicle. 4. The unmanned aerial vehicle according to claim 1, wherein the piezoelectric gyroscope accommodated in the casing provides a deflection command to the servo motors. 5. The unmanned aerial vehicle according to claim 1, wherein the control system is operated based on a symmetry of configuration and a movement of the plurality of wingtip devices. 6. The unmanned aerial vehicle according to claim 1 further comprising a sensor located in the casing to receive an input from a user to output a commands to the control system to regulate the operation of the servo motors to adjust the movement of the plurality of the wing tip devices to control the yaw, pitch and roll movements of the aerial vehicle. 7. The unmanned aerial vehicle according to claim 6, wherein the user transmits the command to the sensor for controlling the movement of the aerial vehicle in different directions using the radio transmitter. 8. The unmanned aerial vehicle according to claim 6, wherein the command is related to a change of angle against the downward air flow movement of the propeller. 9. The unmanned aerial vehicle according to claim 1, wherein the servo motors control the angle between the plurality of wingtip devices and the downward air flow of the propeller. 10. The unmanned aerial vehicle according to claim 1, wherein the brushless type electric motor directs the aerial vehicle to an appropriate height by decreasing or increasing a rotational speed of the electromotor. 11. The unmanned aerial vehicle according to claim 1, wherein the surveillance unit accommodated in the casing is a visual surveillance camera. 12. The unmanned aerial vehicle according to claim 1, wherein the casing further comprises a video transmitter and an antenna. 13. The unmanned aerial vehicle according to claim 1, wherein the casing comprises a global positioning system. 14. The unmanned aerial vehicle according to claim 1, wherein the piezoelectric gyroscope accommodated in the casing gives the deflection command to servomotors with a priority which is higher than a priority assigned to the command received from a user for changing the movement of the aerial vehicle. 15. The unmanned aerial vehicle according to claim 1, wherein each of the three types of wing tip devices has a plurality of wingtip devices arranged symmetrically with respect to a central axis of the hemispherical body. 16. The unmanned aerial vehicle according to claim 1, wherein the control system regulates the operation of the servo motors to adjust the rotation of the plurality of the wing tip devices in each of the three types of the wing tip devices so that the symmetrically arranged plurality of the wing tip devices in each of the three types of the wing tip devices are rotated in mutually opposite directions to equalize a torque of the brushless type electrical motor to stabilize a movement of the aerial vehicle in a Z-axis. 17. The unmanned aerial vehicle according to claim 1, wherein a curve of the hemispherical body is designed in a way to keep a balance and a stability of the aerial vehicle to provide a flight with more stable dynamics. 18. The unmanned aerial vehicle according to claim 1, wherein the plurality of the wingtip devices are installed around the hemispherical body to regulate and channelize a turbulent downward air flow due to the spinning propeller and to prevent an empty space below the aerial vehicle due to an induction of energetic vortices of the propeller thereby increasing the stability of the aerial vehicle. 19. The unmanned aerial vehicle according to claim 1, wherein the plurality of the wingtip devices and the hemispherical body provide an aerodynamic combination to increase a dynamic stability of the aerial vehicle during a calm air of environment as well as during the landing and take-off operations and in static conditions.