Unmanned aerial vehicle and operations thereof
The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
1. A multi-rotor unmanned aerial vehicle (UAV), comprising:
a housing forming a central body of the UAV, said housing comprising an outer surface and an inner surface, wherein said inner surface forms a cavity;
one or more electrical components disposed inside the cavity of the central body and adapted to control operation of the UAV; and
a magnetometer secured onto an extension member at a position sufficiently distal from the housing to effect a reduction of interference from said one or more electrical components disposed within the cavity of the central body, said one or more electrical components selected from the group including a power source, flight control module, inertial measurement unit (IMU), or GPS receiver, and wherein said extension member is a landing stand configured to bear weight of the UAV when the UAV is not airborne.
2. The UAV of claim 1 , wherein the landing stand includes a substantially vertical portion and the magnetometer is secured to the substantially vertical portion.
3. The UAV of claim 2 , wherein the landing stand to which the magnetometer is secured extends downward from the housing.
4. The UAV of claim 1 , wherein the magnetometer is a compass.
5. The UAV of claim 1 , wherein the minimum distance between the magnetometer and the one or more electrical components is at least about 3 cm.
6. The UAV of claim 1 , wherein the UAV comprises a plurality of rotor blades.
7. The UAV of claim 6 , wherein at least one of the electrical components is pre-configured by a manufacturer of the UAV, and wherein the at least one of the electrical components forms an electric unit necessary and sufficient for controlling operation of said UAV.
8. The UAV of claim 1 , wherein the one or more electrical components include a GPS receiver.
9. The UAV of claim 8 , wherein the magnetometer is at least 3 cm away from the GPS receiver.
10. The UAV of claim 1 , wherein the housing comprises an upper housing member and a lower housing member that are removably coupled to form the cavity.
11. The UAV of claim 1 , wherein the central body is connected to one or more branch housing members, wherein the central body forms a central cavity, and wherein the one or more branch housing members forms one or more branch cavities.
12. The UAV of claim 11 , wherein at least one of the one or more electrical components is located inside one of the one or more branch cavities.
13. The UAV of claim 12 , wherein the at least one electrical component located inside one of the one or more branch cavities includes an electronic speed control (ESC) module or an actuator.
14. The UAV of claim 1 , wherein the one or more electrical components includes an inertial measurement unit (IMU), or GPS receiver.
15. A method of reducing interference experienced by a magnetometer from one or more electrical components of a multi-rotor unmanned aerial vehicle (UAV), the method comprising: providing the UAV of claim 1 , thereby reducing said interference.