Aerial vehicle with frame assemblies

• US 9,493,225 B2
• Filed: 02/01/2016
• Issued: 11/15/2016
• Est. Priority Date: 01/10/2013
• 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, Du, Hao, Wang, Mingxi
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): KREINER, MICHAEL B
• Application Number:
  US15/012,068
• Publication Number:
  US 20160152316A1
• Time in Patent Office: 288 Days
• US Class Current: 1/1
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64C 1/00 Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• CPC Class Codes: B64C 1/061 Frames
• CPC Class Codes: B64C 1/063 Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 25/12 sideways
• CPC Class Codes: B64C 25/32 characterised by elements which contact the ground or similar surface arrester hooks B64C25/68
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/028 Micro-sized aircraft
• CPC Class Codes: B64D 47/00 Equipment not otherwise provided for
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• 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 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/00 UAVs characterised by their flight controls
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 50/13 : using external fans or propellers
• CPC Class Codes: B64U 50/19 : using electrically powered motors
• CPC Class Codes: G05D 1/042 : specially adapted for aircraft

Abstract

Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

Claims

1. An aerial vehicle comprising:

a central body;

a plurality of frame assemblies coupled to the central body;

an actuation assembly coupled to the plurality of frame assemblies, wherein the actuation assembly comprises a linear actuator, wherein each frame assembly of the plurality of frame assemblies comprises a portion coupled to the linear actuator, and wherein the actuation assembly is configured to actuate the plurality of frame assemblies to a plurality of different angles between the plurality of frame assemblies with respect to a vertical axis; and

a plurality of propulsion units operable to move the aerial vehicle, wherein each frame assembly of the plurality of frame assemblies supports at least one propulsion unit,

wherein a linear motion of the linear actuator is substantially parallel to a yaw axis of the aerial vehicle.

2. The vehicle of claim 1, wherein the aerial vehicle is an unmanned aerial vehicle.

3. The vehicle of claim 1, wherein each frame assembly of the plurality of frame assemblies comprises a proximal portion directly coupled to the central body and a distal portion coupled to a cross bar.

4. The vehicle of claim 1, wherein the plurality of frame assemblies are configured to move between a first configuration where the plurality of propulsion units is positioned below the central body and a second configuration where the plurality of propulsion units is positioned above the central body.

5. The vehicle of claim 1, wherein the actuation assembly is configured to actuate the plurality of frame assemblies to a plurality of different vertical angles relative to the central body.

6. The vehicle of claim 1, further comprising a receiver configured to receive user commands for controlling the aerial vehicle.

15. The vehicle of claim 1, wherein the linear motion of the linear actuator remains substantially parallel to the yaw axis of the aerial vehicle when the plurality of frame assemblies are at the plurality of different angles.

7. An aerial vehicle comprising:

a central body;

a plurality of frame assemblies coupled to the central body;

an actuation assembly comprising a linear actuator, wherein each frame assembly of the plurality of frame assemblies comprises a portion coupled to the linear actuator, wherein the actuation assembly is configured to transform the plurality of frame assemblies between a first configuration and a second configuration, and wherein the first configuration permits the plurality of frame assemblies to support the aerial vehicle resting on a surface; and

a plurality of propulsion units mounted on the plurality of frame assemblies and operable to move the aerial vehicle,

wherein a linear motion of the linear actuator is substantially parallel to a yaw axis of the aerial vehicle.

8. The vehicle of claim 7, wherein the aerial vehicle is an unmanned aerial vehicle.

9. The vehicle of claim 7, wherein each frame assembly of the plurality of frame assemblies comprises a proximal portion directly coupled to the central body and a distal portion coupled to a cross bar.

10. The vehicle of claim 7, wherein the first configuration includes the plurality of propulsion units being positioned below the central body and the second configuration includes the plurality of propulsion units being positioned above the central body.

11. The vehicle of claim 7, further comprising a receiver configured to receive user commands for controlling the aerial vehicle.

12. The vehicle of claim 7, wherein the actuation assembly is configured to transform the plurality of frame assemblies into the first configuration during a first phase of operation of the aerial vehicle and into the second configuration during a second phase of operation of the aerial vehicle.

13. The vehicle of claim 12, wherein the first phase of operation comprises one or more of the aerial vehicle taking off from a surface or landing on the surface, and the second phase of operation comprises the aerial vehicle flying in air.

14. The vehicle of claim 7, wherein the linear motion of the linear actuator remains substantially parallel to the yaw axis of the aerial vehicle when the plurality of frame assemblies are at the first configuration and the second configuration.

16. An aerial vehicle comprising:

a central body coupled to a payload;

a plurality of frame assemblies coupled to the central body;

an actuation assembly comprising a linear actuator, wherein each frame assembly of the plurality of frame assemblies comprises a portion coupled to the linear actuator, wherein the actuation assembly is configured to transform the plurality of frame assemblies between a first configuration and a second configuration, and wherein the second configuration increases a functional space of the payload; and

a plurality of propulsion units mounted on the plurality of frame assemblies and operable to move the aerial vehicle,

wherein a linear motion of the linear actuator is substantially parallel to a yaw axis of the aerial vehicle.

17. The vehicle of claim 16, wherein the aerial vehicle is an unmanned aerial vehicle.

18. The vehicle of claim 16, wherein each frame assembly of the plurality of frame assemblies comprises a proximal portion directly coupled to the central body and a distal portion coupled to a cross bar.

19. The vehicle of claim 16, wherein the actuation assembly is configured to transform the plurality of frame assemblies into the first configuration during a first phase of operation of the aerial vehicle and into the second configuration during a second phase of operation of the aerial vehicle.

20. The vehicle of claim 16, wherein the first phase of operation comprises one or more of the aerial vehicle taking off from a surface or landing on the surface, and the second phase of operation comprises the aerial vehicle flying in air.

21. The vehicle of claim 16, wherein the payload comprises an image capturing device, and the functional space comprises an unobstructed field of view of the image capturing device.

22. The vehicle of claim 16, wherein each frame assembly of the plurality of frame assemblies comprises a support member configured to support the aerial vehicle resting on a surface.

23. The vehicle of claim 16, wherein the linear motion of the linear actuator remains substantially parallel to the yaw axis of the aerial vehicle when the plurality of frame assemblies are at the first configuration and the second configuration.