UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF

• US 20160083084A1
• Filed: 11/30/2015
• Published: 03/24/2016
• Est. Priority Date: 11/15/2012
• Status: Active Grant

• Current Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Original Assignee: SZ DJI Technology Co., Ltd. (d/b/a DJI) (iFlight Technology Company Limited)
• Inventors: Wang, Tao, Zhao, Tao, Chen, Shaojie, Ou, Zhigang
• Granted Patent: US 9,284,049 B1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64C 1/30 Parts of fuselage relatively movable to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 25/06 fixed
• CPC Class Codes: B64C 25/32 characterised by elements which contact the ground or similar surface arrester hooks B64C25/68
• CPC Class Codes: B64C 27/00 Rotorcraft; Rotors peculiar thereto
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/54 Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 31/14 Transmitting means between initiating means and power plants
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 20/80 Arrangement of on-board electronics, e.g. avionics systems or wiring
• CPC Class Codes: B64U 2101/00 UAVs specially adapted for particular uses or applications
• CPC Class Codes: B64U 2101/20 for use as communications relays, e.g. high-altitude platforms
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 2201/00 UAVs characterised by their flight controls
• CPC Class Codes: B64U 2201/10 : autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 30/20 : Rotors; Rotor supports
• CPC Class Codes: B64U 30/291 : Detachable rotors or rotor supports
• CPC Class Codes: B64U 30/293 : Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 50/19 : using electrically powered motors
• CPC Class Codes: B64U 60/50 : with landing legs
• CPC Class Codes: B64U 80/00 : Transport or storage specially adapted for UAVs
• CPC Class Codes: G01R 33/0047 : Housings or packaging of magnetic sensors packaging of semiconductor devices H01L23/00; Holders
• CPC Class Codes: G01V 3/16 : specially adapted for use from aircraft G01V3/165 - G01V3/175 take precedence
• CPC Class Codes: G05D 1/00 : Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots drive control systems specially adapted for autonomous road vehicles B60W60/00
• CPC Class Codes: Y10T 29/49117 : Conductor or circuit manufacturing

Abstract

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.

Claims

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 (1) configured to control the operation of the UAV, and (2) comprising at least a flight control module; 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 configured to effect movement of the UAV in response to communications from the flight control module,

wherein the upper branch housing member and the lower branch housing members are configured to extend to a length at least to support the one or more actuator assemblies, and

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.

2. The UAV of claim 1, further comprising a magnetometer at a distance of at least 3 cm from the one or more electrical components.

3. The UAV of claim 2, wherein the magnetometer is at a distance of no more than 0.5 m away from the one or more electrical components.

4. The UAV of claim 2, wherein the magnetometer is secured to an extension member extending away from the central body.

5. The UAV of claim 4, wherein the extension member is a landing stand configured to bear weight of the UAV when the UAV is not airborne.

6. The UAV of claim 1, wherein the integral upper body portion and the integral lower body portion are removably coupled with aid of one or fasteners.

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 11, 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 (1) configured to control the operation of the UAV, and (2) comprising at least a flight control module;

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 communications from the flight control module, each actuator assembly comprising an actuator and one or more rotor blades;

wherein each actuator assembly is (1) partially within a branch cavity of a corresponding branch housing member, (2) partially extending from the branch cavity of the corresponding branch housing member, and (3) has, beneath the actuator assembly, a portion of the lower branch housing member of the corresponding branch housing member.

17. The UAV of claim 16, further comprising a magnetometer at a distance of at least 3 cm from the one or more electrical components.

18. The UAV of claim 17, wherein the magnetometer is at a distance of no more than 0.5 m away from the one or more electrical components.

19. The UAV of claim 17, wherein the magnetometer is secured to an extension member extending away from the central body.

20. The UAV of claim 19, wherein the extension member is a landing stand configured to bear weight of the UAV when the UAV is not airborne.

21. The UAV of claim 16, wherein the actuator of 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.

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.