UNMANNED AIRCRAFT SYSTEM WITH SWAPPABLE COMPONENTS

• US 20190135403A1
• Filed: 07/31/2018
• Published: 05/09/2019
• Est. Priority Date: 08/01/2017
• Status: Active Grant

• Current Assignee: Zipline International Inc.
• Original Assignee: Zipline International Inc.
• Inventors: Perry, Paul, Laszlo, Zoltan, Parker, Scott, Goldsberry, Nathan, Wade, Bryan, Wyrobek, Keenan, Boomgaard, Brian, Li, Zhefei, Blaser, Sven
• Granted Patent: US 10,988,253 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 1/061 Frames
• CPC Class Codes: B64C 1/068 Fuselage sections
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 17/00 Parachutes non canopied parachutes B64D19/00
• CPC Class Codes: B64D 47/00 Equipment not otherwise provided for
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

An unmanned aerial vehicle may include a fuselage and an anchor structure coupled to the fuselage and including a wing retention structure and a power module retention structure. The unmanned aerial vehicle may also include a wing releasably coupled to the wing retention structure, thereby coupling the wing to the fuselage, and a power module releasably coupled to the power module retention structure, thereby coupling the power module to the fuselage.

Claims

1. An unmanned aerial vehicle, comprising:

a fuselage;

an anchor structure coupled to the fuselage and comprising;

a wing retention structure; and

a power module retention structure;

a wing releasably coupled to the wing retention structure, thereby coupling the wing to the fuselage; and

a power module releasably coupled to the power module retention structure, thereby coupling the power module to the fuselage.

2. The unmanned aerial vehicle of claim 1, wherein:

the anchor structure comprises a monolithic metal frame that defines at least a portion of both the wing retention structure and the power module retention structure;

the fuselage defines a cavity configured to receive the power module therein; and

the monolithic metal frame is mounted to the fuselage adjacent the cavity.

3. The unmanned aerial vehicle of claim 2, wherein:

the wing retention structure comprises a retention pin; and

the wing comprises a mounting bracket defining a retention slot configured to slidably engage the retention pin.

4. The unmanned aerial vehicle of claim 3, wherein

the retention pin is a first retention pin;

the power module retention structure comprises a second retention pin; and

the power module is configured to slidably engage the second retention pin.

5. The unmanned aerial vehicle of claim 4, wherein when the power module is received within the cavity the power module prevents the mounting bracket of the wing from disengaging from the first retention pin.

6. The unmanned aerial vehicle of claim 1, further comprising:

a circuit board attached to the anchor structure; and

a processor attached to the circuit board and configured to control flight operations of the unmanned aerial vehicle.

7. The unmanned aerial vehicle of claim 1, wherein the coupling between the wing and the wing retention structure is the exclusive lift-transferring connection between the wing and the fuselage.

8. The unmanned aerial vehicle of claim 1, wherein:

the fuselage comprises;

a load bearing frame; and

a closed-cell polymer foam body attached to the load bearing frame; and

the anchor structure is attached to the load bearing frame.

9. An unmanned aerial vehicle, comprising:

a fuselage;

an integrated coupling and control unit coupled to the fuselage and comprising;

a frame member;

a circuit board coupled to the frame member;

a processor attached to the circuit board;

a first wing electrical connector; and

a first power module electrical connector;

a wing comprising a second wing electrical connector configured to be removably coupled to the first wing electrical connector; and

a power module comprising a second power module electrical connector configured to be removably coupled to the first power module electrical connector.

10. The unmanned aerial vehicle of claim 9, wherein:

the wing comprises;

a movable flight control surface; and

an actuator coupled to the flight control surface and configured to move the movable flight control surface; and

the processor is configured to send a signal to the actuator, via the first and second wing electrical connectors, to cause movement of the movable flight control surface.

11. The unmanned aerial vehicle of claim 9, wherein:

the frame member comprises a wing retention structure; and

the wing further comprises a bracket configured to mechanically engage the wing retention structure.

12. The unmanned aerial vehicle of claim 11, wherein the second wing electrical connector is coupled to the wing in a fixed positional relationship to the bracket, thereby causing the first wing electrical connector to be electrically engaged with the second wing electrical connector when the bracket is at least partially mechanically engaged with the wing retention structure.

13. The unmanned aerial vehicle of claim 12, wherein:

the bracket is a first bracket;

the frame member further comprises a power module retention structure; and

the power module comprises a second bracket configured to mechanically engage the power module retention structure.

14. The unmanned aerial vehicle of claim 13, wherein the second power module electrical connector is coupled to the power module in a fixed positional relationship to the second bracket, thereby causing the first power module electrical connector to be electrically engaged with the second power module electrical connector when the second bracket is at least partially mechanically engaged with the power module retention structure.

15. The unmanned aerial vehicle of claim 14, wherein the power module further comprises a locking mechanism configured to retain the power module to the fuselage, thereby maintaining the mechanical engagement between the first bracket and the wing retention structure and between the second bracket and the power module retention structure.

16. The unmanned aerial vehicle of claim 15, wherein the locking mechanism comprises a sliding cam mechanism.

17. The unmanned aerial vehicle of claim 13, wherein:

the power module comprises;

a handle movable between an open position and a locked position; and

a sliding cam coupled to the handle; and

the sliding cam engages a locking pin as the handle is moved from the open position to the locked position.

18. The unmanned aerial vehicle of claim 17, wherein:

the wing defines a channel on a top side of the wing;

the handle is received in the channel when the handle is in the locked position; and

an exposed portion of the handle and a portion of the wing adjacent the channel define a substantially continuous exterior surface of the fuselage.

19. An unmanned aerial vehicle, comprising:

a fuselage comprising;

a substantially rigid frame; and

a polymer material attached to at least a portion of the substantially rigid frame to define an exterior surface of the fuselage;

an anchor structure attached to the fuselage via the substantially rigid frame;

a wing releasably coupled to the fuselage via a mechanical engagement with the anchor structure; and

a power module releasably coupled to the fuselage via a mechanical engagement with the anchor structure.

20. The unmanned aerial vehicle of claim 19, wherein the mechanical engagement between the wing and the anchor structure is substantially the only connection for transferring lift forces from the wing to the fuselage.

21. The unmanned aerial vehicle of claim 20, wherein:

the anchor structure comprises a wing retention structure; and

the wing comprises a mounting bracket configured to engage the wing retention structure by translating the wing along an installation path.

22. The unmanned aerial vehicle of claim 21, wherein, when the wing and the power module are releasably coupled to the fuselage, the power module prevents translation of the wing in a removal path that is opposite the installation path.

23. The unmanned aerial vehicle of claim 19, wherein:

the fuselage defines;

a nose portion of the unmanned aerial vehicle; and

a cavity between the nose portion and the wing; and

the power module is received in the cavity.

24. The unmanned aerial vehicle of claim 19, further comprising a deployable parachute coupled to the anchor structure via a cord.