Unmanned aerial vehicle and operations thereof

• US 10,155,584 B2
• Filed: 06/07/2016
• Issued: 12/18/2018
• 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
• Primary Examiner(s): O'Hara, Brian M
• Assistant Examiner(s): Kreiner, Michael B.
• Application Number:
  US15/175,473
• Publication Number:
  US 20170121016A1
• Time in Patent Office: 924 Days
• 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 configured to house at least one electrical component for controlling operation of the UAV;

a branch housing member configured to extend from the central body, wherein the branch housing member comprises a branch cavity, and wherein the branch housing member is configured to be foldable relative to the central body to transform the UAV between a folded configuration and an expanded configuration; and

an actuator assembly coupled to the branch housing member, wherein the actuator assembly comprises an actuator configured to effect movement of the UAV,

wherein at least a portion of the branch housing member extends beneath the actuator; and

wherein the actuator is partially within the branch cavity of the branch housing member and partially extending from the branch cavity of the branch housing member.

2. The UAV of claim 1, wherein a thrust of the actuator assembly is oriented in a vertical direction relative to the central body.

3. The UAV of claim 1, wherein the branch housing member comprises a plurality of members which form the branch cavity.

4. The UAV of claim 1, further comprising an electronic speed control (ESC) configured to be electrically coupled to the actuator assembly, wherein the ESC is disposed in the central cavity.

5. The UAV of claim 1, further comprising an electronic speed control (ESC) configured to be electrically coupled to the actuator assembly, wherein the ESC is not disposed in the central cavity.

6. The UAV of claim 1, further comprising a plurality of branch housing members.

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

8. The UAV of claim 7, wherein the magnetometer is at a distance of no more than 0.5 m away from the at least one electrical components.

9. The UAV of claim 7, wherein the magnetometer is secured to an extension member extending away from the central body.

10. The UAV of claim 9, wherein the extension member is a landing stand configured to bear weight of the UAV when the UAV is not airborne.

11. 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 configured to house at least one electrical component for controlling operation of the UAV;

a plurality of branch housing members configured to extend from the central body, wherein each of the plurality of branch housing members comprises a branch cavity, and wherein the plurality of branch housing members is configured to be foldable relative to the central body to transform the UAV between a folded configuration and an expanded configuration;

a plurality of actuator assemblies each coupled to one branch housing member of the plurality of branch housing members, wherein the plurality of actuator assemblies is configured to effect movement of the UAV; and

a plurality of electronic speed control (ESC) modules each configured to be electrically coupled to one actuator assembly of the plurality of branch housing members to control actuation of the actuator assemblies,

wherein each ESC module of the plurality of ESC modules are located within a respective branch cavity.

12. The UAV of claim 11, wherein each ESC module of the plurality of ESC modules are operably coupled to a flight control module to permit two-way communication between the flight control module and each ESC module.

13. The UAV of claim 11, wherein the central cavity comprises at least one interior structure formed therein configured to accommodate the at least one electrical components.

14. The UAV of claim 13, wherein the at least one interior structure comprises slots, grids, or housings that accommodate the at least one electrical components.

15. The UAV of claim 11, further comprising an energy source configured to provide electrical energy to the plurality of actuator assemblies, wherein the central body is configured to receive the energy source.

16. The UAV of claim 15, wherein the energy source is within the central cavity.

17. The UAV of claim 11, wherein each of the plurality of branch housing members comprise a plurality of members which form the branch cavity.

18. The UAV of claim 11, further comprising a magnetometer at a distance of at least 3 cm from the 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.