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 central body comprising an upper housing member and a lower housing member, the upper housing member and the lower housing member forming a central cavity, wherein the central cavity is configured to house one or more electrical components configured to control operation of the UAV; and
one or more branch housing members extending from the central body, the one or more branch housing members each comprising an upper branch housing member and a lower branch housing member,
wherein the one or more branch housing members are configured to support one or more actuator assemblies, each actuator assembly comprising an actuator configured to effect movement of the UAV, wherein the thrust of the one or more actuator assemblies is oriented in a vertical direction relative to the central body, and
wherein at least a portion of each of the lower branch housing members extends beneath at least a portion of the corresponding actuator.
2. The UAV of claim 1 , wherein the one or more upper branch housing members and the upper housing member form an integral upper body portion, the one or more lower branch housing members and the lower housing member form an integral lower body portion, and the integral upper body portion and the integral lower body portion are removably coupled to form a hollow body portion comprising the central cavity.
3. The UAV of claim 1 , further comprising a magnetometer at a distance of at least 3 cm from the one or more electrical components.
4. The UAV of claim 3 , wherein the magnetometer is at a distance of no more than 0.5 m away from the one or more electrical components.
5. The UAV of claim 3 , wherein the magnetometer is secured to an extension member extending away from the central body.
6. The UAV of claim 5 , wherein the extension member is a landing stand configured to bear weight of the UAV when the UAV is not airborne.
7. The UAV of claim 1 , wherein the upper branch housing member and the lower branch housing member form a branch cavity within a corresponding branch housing member.
8. The UAV of claim 1 , wherein the upper branch housing member and the lower branch housing member have substantially the same length.
9. The UAV of claim 1 , wherein the central cavity has one or more interior structures formed therein configured to accommodate the one or more electrical components.
10. The UAV of claim 9 , wherein the interior structures comprise slots, grids, or housings that accommodate the one or more electrical components.
11. The UAV of claim 1 , further comprising an energy source configured to provide energy to the one or more actuator assemblies.
12. The UAV of claim 11 , wherein the energy source is within the central cavity.
13. The UAV of claim 12 , further comprising an opening configured to permit the energy source to be retrieved from the central cavity or inserted into the central cavity.
14. The UAV of claim 13 , further comprising a cover hingedly coupled to the central body to selectively cover the opening.
15. The UAV of claim 1 , further comprising a carrier for supporting a payload device.
16. A multi-rotor unmanned aerial vehicle (UAV), comprising:
a central body comprising a central cavity configured to house one or more electrical components configured to control the operation of the UAV;
one or more branch housing members extending from the central body, the one or more branch housing members each comprising an upper branch housing member and a lower branch housing member; and
one or more actuator assemblies configured to effect movement of the UAV in response to the one or more electrical components, each actuator assembly comprising an actuator and one or more rotor blades,
wherein at least a portion of each of the lower branch housing members extends beneath at least a portion of the corresponding actuator assembly.
17. The UAV of claim 16 , wherein each actuator assembly is (1) partially within a branch cavity of a corresponding branch housing member and (2) partially extending from the branch cavity of the corresponding branch housing member.
18. The UAV of claim 16 , further comprising a magnetometer at a distance of at least 3 cm from the one or more electrical components.
19. The UAV of claim 18 , wherein the magnetometer is at a distance of no more than 0.5 m away from the one or more electrical components.
20. The UAV of claim 18 , wherein the magnetometer is secured to an extension member extending away from the central body.
21. The UAV of claim 20 , wherein the extension member is a landing stand configured to bear weight of the UAV when the UAV is not airborne.
22. The UAV of claim 16 , wherein the actuator is located between a portion of the lower branch housing member and the one or more rotor blades.
23. The UAV of claim 16 , wherein the upper branch housing member and the lower branch housing member have substantially the same length.
24. The UAV of claim 16 , wherein the central cavity has one or more interior structures formed therein configured to accommodate the one or more electrical components.
25. The UAV of claim 16 , further comprising an electronic speed control (ESC) module positioned within the branch housing member beneath a corresponding actuator assembly.
26. The UAV of claim 16 , wherein the upper branch housing member comprises an opening for accepting the actuator assembly.
27. The UAV of claim 26 , wherein the opening is configured for accepting and installing the actuator of the actuator assembly.
28. The UAV of claim 16 , wherein the actuator comprises a shaft that is rotatably attachable to the one or more rotor blades.
29. The UAV of claim 16 , further comprising an energy source within the central cavity configured to provide energy to the one or more actuator assemblies.
30. The UAV of claim 16 , further comprising a carrier for supporting a payload device.