Unmanned aerial vehicle configuration for extended flight

• US 9,868,524 B2
• Filed: 11/11/2014
• Issued: 01/16/2018
• Est. Priority Date: 11/11/2014
• Status: Active Grant

• Current Assignee: Amazon Technologies, Inc. (Amazon.com, Inc.)
• Original Assignee: Amazon Technologies, Inc. (Amazon.com, Inc.)
• Inventors: Welsh, Ricky Dean, Buchmueller, Daniel, Hensel, Fabian, Kimchi, Gur, LeGrand, III, Louis LeRoi, Porter, Brandon William, Robb, Walker Chamberlain, Traube, Joshua White
• Primary Examiner(s): Green, Richard R
• Application Number:
  US14/538,570
• Publication Number:
  US 20160129998A1
• Time in Patent Office: 1,162 Days
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• CPC Class Codes: B64C 27/24 with rotor blades fixed in flight to act as lifting surfaces
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/13 using external fans or propellers

Abstract

This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pushing motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor may be engaged and the pushing propeller will aid in the horizontal propulsion of the UAV.

Claims

1. An unmanned aerial vehicle (UAV), comprising:

a frame;

a first lifting motor coupled to the frame;

a second lifting motor coupled to the frame;

a pushing motor coupled to the frame;

a fuselage coupled to the frame and extending downward from the frame, wherein the fuselage encompasses a plurality of components of the UAV and is configured to reduce aerodynamic resistance of the UAV when the UAV is flown in a direction including a horizontal component;

a first power supply container coupled to the frame at a first position;

a second power supply container coupled to the frame at a second position; and

an unmanned aerial vehicle control system configured to send control signals to the first lifting motor, the second lifting motor and the pushing motor in response to signals received from a remote location; and

wherein;

the frame includes a payload receiving area between the first power supply container and the second power supply container that receives a payload;

the fuselage includes a downward-facing gap or opening within which the payload, when received, is at least partially contained; and

the payload includes an item to be delivered to a user.

2. The UAV of claim 1, further comprising:

a wing coupled to the frame, wherein the wing is configured to provide lift as the UAV is flown in a direction including a horizontal component.

3. The UAV of claim 1, further comprising:

a first motor housing coupled to the frame and the first lifting motor, the first motor housing having a tapered shape to reduce an aerodynamic resistance of the first lifting motor.

4. The UAV of claim 1, further comprising:

a first lifting propeller coupled to the first lifting motor; and

a first pushing propeller coupled to the pushing motor.

5. The UAV of claim 4, wherein:

the first lifting propeller has a first dimension;

the first pushing propeller has a second dimension; and

the first dimension is larger than the second dimension.

6. The UAV of claim 1, wherein:

the pushing motor is a different motor size than at least one of the first lifting motor or the second lifting motor.

7. The UAV of claim 1, wherein:

the frame is configured to dissipate heat from the first power supply container and the second power supply container; and

at least one component of the unmanned aerial vehicle control system is thermally coupled to the frame with at least one of a thermal grease or thermal pad positioned between the at least one component and the frame such that the thermal grease or the thermal pad improves a thermal transfer between the at least one component and the frame.

8. The UAV of claim 1, wherein the unmanned aerial vehicle control system is further configured to send control signals to at least one of the first lifting motor, the second lifting motor, or the pushing motor in response to signals received from a device of the UAV.

9. An unmanned aerial vehicle (UAV), comprising:

a frame;

a first motor arm having a first end and a second end, the first motor arm coupled to the frame;

a second motor arm having a third end and a fourth end, the second motor arm coupled to the frame;

a first lifting motor coupled to the first end of the first motor arm;

a second lifting motor coupled to the second end of the first motor arm;

a third lifting motor coupled to the third end of the second motor arm;

a fourth lifting motor coupled to the fourth end of the second motor arm;

a pushing motor coupled to a fifth end of the frame and configured to provide horizontal propulsion to the UAV;

a first power supply container coupled to the frame at a first position;

a second power supply container coupled to the frame at a second position; and

an unmanned aerial vehicle control system for controlling a rotational speed of at least one of the first lifting motor, the second lifting motor, the third lifting motor, the fourth lifting motor or the pushing motor, wherein;

the frame includes a payload receiving area including a downward-facing gap or opening within which a payload, when received, is at least partially contained, the payload receiving area being positioned between the first power supply container and the second power supply container; and

the payload includes an item to be delivered to a user.

10. The UAV of claim 9,

wherein the first power supply container and the second power supply container are each removably coupled to the frame and configured to house at least one power supply for providing power to the UAV.

11. The UAV of claim 10, further comprising:

a fuselage coupled to the frame and extending downward from the frame, wherein;

the fuselage encompasses at least a portion of the first power supply container and the second power supply container; and

the fuselage is configured to reduce aerodynamic resistance of the UAV when flown in a direction including a horizontal component.

12. The UAV of claim 10, wherein the first power supply container and the second power supply container each includes a removable shelf configured to support at least one power supply or a component of a control system of the UAV.

13. The UAV of claim 9, further comprising:

a wing coupled to the frame, wherein the wing is configured to provide lift as the UAV is flown in a direction including a horizontal component.

14. The UAV of claim 9, further comprising:

a fuselage coupled to the frame and extending downward from the frame, wherein the fuselage encompasses a plurality of components of the UAV and is configured to reduce aerodynamic resistance of the UAV when the UAV is flown in a direction including a horizontal component; and

the fuselage includes the downward-facing gap or opening within which the payload, when received, is at least partially contained.

15. The UAV of claim 9, further comprising:

a first lifting motor housing coupled to the first end of the first motor arm and formed around the first lifting motor, the first lifting motor housing having a tapered shape to reduce an aerodynamic resistance of the first lifting motor.

16. An unmanned aerial vehicle (UAV), comprising:

a frame;

a first lifting motor coupled to the frame;

a pushing motor coupled to the frame;

a first power supply container coupled to the frame at a first position;

a second power supply container coupled to the frame at a second position;

a wing coupled to the frame and configured to provide lift when the UAV is moving in a direction that includes a horizontal component;

a fuselage coupled to the frame and extending downward from the frame, wherein the fuselage encompasses a plurality of components of the UAV and is configured to reduce aerodynamic resistance of the UAV when the UAV is flown in a direction including a horizontal component; and

wherein;

the frame includes a payload receiving area between the first power supply container and the second power supply container that receives a payload;

the fuselage includes a downward-facing gap or opening within which the payload, when received, is at least partially contained; and

the payload includes an item to be delivered to a user.

17. The UAV of claim 16, wherein the wing is positioned between the first lifting motor and a second lifting motor.

18. The UAV of claim 16, further comprising:

an unmanned aerial vehicle control system; and

wherein;

at least one component of the unmanned aerial vehicle control system is thermally coupled to the frame with at least one of a thermal grease or thermal pad positioned between the at least one component and the frame such that the thermal grease or the thermal pad improves a thermal transfer between the at least one component and the frame; and

the frame dissipates heat generated by the at least one component of the unmanned aerial vehicle control system.

19. The UAV of claim 18, wherein the at least one component includes an electronic speed control component.

20. The UAV of claim 16, further comprising:

a protection circuit configured to operate as a spark suppression circuit for protecting at least a portion of the UAV when power is applied and a kill switch for removing power from at least a portion of the UAV.

21. The UAV of claim 16, further comprising:

a payload engagement controller that communicates with at least one component of the UAV to control an engagement and disengagement of the payload.