UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF

• US 20160075431A1
• Filed: 11/20/2015
• Published: 03/17/2016
• 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 9,321,530 B2
• 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:

one or more electrical components disposed in a body of the UAV and adapted to facilitate operation of the UAV, said one or more electrical components selected from a group comprising a power source, flight control module, inertial measurement unit (IMU), and GPS receiver; and

a magnetometer attached onto a landing stand at a position sufficiently distal from the one or more electrical components to effect a reduction of interference from said one or more electrical components, wherein the landing stand extends away from the body of the UAV and is configured to bear weight of the UAV when the UAV is not airborne.

2. The UAV of claim 1, wherein the magnetometer is a compass.

3. The UAV of claim 1, further comprising a plurality of rotor blades.

4. The UAV of claim 1, further comprising a carrier for supporting a payload device.

5. The UAV of claim 4, wherein the payload device is a camera.

6. The UAV of claim 4, wherein the payload device is located between a pair of landing stands.

7. The UAV of claim 1, wherein the one or more electrical components comprises the GPS receiver, and wherein magnetometer is at least 3 cm away from the GPS receiver.

8. The UAV of claim 1, wherein the body of the UAV comprises an upper housing member and a lower housing member that are removably coupled to form a cavity of the body, within which the one or more electrical components are disposed.

9. The UAV of claim 1, wherein the body is connected to one or more branch housing members.

10. The UAV of claim 9, wherein the one or more branch housing members comprise one or more branch cavities.

11. The UAV of claim 9, wherein the body is integrally formed with the one or more branch housing members.

12. The UAV of claim 1, wherein the landing stand comprises a substantially vertical portion and the magnetometer is secured to the substantially vertical portion.

13. The UAV of claim 12, wherein the landing stand to which the magnetometer is secured extends downward from the body of the UAV.

14. The UAV of claim 1, wherein the landing stand comprises a substantially horizontal portion and the magnetometer is secured to the substantially horizontal portion.

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.

16. A multi-rotor unmanned aerial vehicle (UAV), comprising:

a housing forming a 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 within the cavity of the body and adapted to facilitate operation of the UAV, said one or more electrical components selected from a group comprising a power source, flight control module, inertial measurement unit (IMU), and GPS receiver; and

a magnetometer attached onto a landing stand at a distance of at least about 3 cm from the one or more electrical components, wherein the landing stand extends away from the housing and is configured to bear weight of the UAV when the UAV is not airborne.

17. The UAV of claim 16, wherein the magnetometer is at a distance of no more than 0.5 m away from the one or more electrical components.

18. The UAV of claim 16, wherein the magnetometer is a compass.

19. The UAV of claim 16, further comprising a plurality of rotor blades.

20. The UAV of claim 16, further comprising a carrier for supporting a payload device.

21. The UAV of claim 20, wherein the payload device is a camera.

22. The UAV of claim 16, wherein the one or more electrical components comprises the GPS receiver, and wherein the magnetometer is at least 3 cm away from the GPS receiver.

23. The UAV of claim 16, wherein the body of the UAV comprises an upper housing member and a lower housing member that are removably coupled to form a cavity of the body, within which the one or more electrical components are disposed.

24. The UAV of claim 16, wherein the body is connected to one or more branch housing members.

25. The UAV of claim 24, wherein the one or more branch housing members comprise one or more branch cavities.

26. The UAV of claim 24, wherein the body is integrally formed with the one or more branch housing members.

27. The UAV of claim 16, wherein the landing stand comprises a substantially vertical portion and the magnetometer is secured to the substantially vertical portion.

28. The UAV of claim 27, wherein the landing stand to which the magnetometer is secured extends downward from the body of the UAV.

29. The UAV of claim 16, wherein the landing stand comprises a substantially horizontal portion and the magnetometer is secured to the substantially horizontal portion.

30. 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 16, thereby reducing said interference.