Replaceable power modules on aerial vehicles

• US 10,017,265 B1
• Filed: 06/13/2016
• Issued: 07/10/2018
• Est. Priority Date: 06/13/2016
• Status: Expired due to Fees

• Current Assignee: Amazon Technologies, Inc. (Amazon.com, Inc.)
• Original Assignee: Amazon Technologies, Inc. (Amazon.com, Inc.)
• Inventors: Larsen, Glen C.
• Primary Examiner(s): Green, Richard R
• Application Number:
  US15/181,254
• Time in Patent Office: 757 Days
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64F 5/50 Handling or transporting aircraft components
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/34 In-flight charging photovoltaics B64U50/31
• CPC Class Codes: B64U 50/39 Battery swapping

Abstract

An aerial vehicle may receive electrical power from power modules that may be installed into or removed from the aerial vehicle during flight operations. Such power modules may be inserted into a chamber from below the aerial vehicle and may come into contact with one or more terminals or leads for powering propulsion motors or other electrical loads. Such power modules may also be removed from above the aerial vehicle, thereby uncoupling the power modules from the electrical loads. Power modules may be installed into or removed from a chamber using tension members that are guided into the chamber from lateral slots extending between a perimeter of the aerial vehicle and the chamber. The tension members may be used to not only engage and remove a power module within the chamber but also to install a power module into the chamber.

Claims

1. An unmanned aerial vehicle comprising:

a frame having a power module chamber, wherein the power module chamber defines a first substantially square cross section bounded by a first front side, a first rear side, a first left side and a first right side, wherein the power module chamber has an upper opening and a lower opening, and wherein one of the first front side, the first rear side, the first left side or the first right side comprises a first positive terminal and a first negative terminal for powering an electrical circuit;

at least one electric propulsion motor configured to receive power from the electrical circuit; and

a power module releasably installed within the power module chamber, wherein the power module comprises a housing defining a second substantially square cross section bounded by a second front side, a second rear side, a second left side and a second right side, wherein the second substantially square cross section corresponds to the first substantially square cross section, wherein one of the second front side, the second rear side, the second left side or the second right side comprises a second positive terminal extending through the housing and a second negative terminal extending through the housing, wherein the one of the second front side, the second rear side, the second left side or the second right side is aligned in contact with the one of the first front side, the first rear side, the first left side or the first right side, wherein the power module chamber is configured to receive the power module via the lower opening of the power module chamber, and wherein the power module chamber is configured to release the power module via the upper opening of the power module chamber,

wherein the second positive terminal is in contact with the first positive terminal when the power module is releasably installed within the power module chamber, and

wherein the second negative terminal is in contact with the first negative terminal when the power module is releasably installed within the power module chamber.

2. The unmanned aerial vehicle of claim 1, wherein the frame further comprises a first lateral slot extending laterally between a perimeter of the frame and the power module chamber, and

wherein the power module comprises a second lateral slot aligned with the first lateral slot when the power module is releasably installed within the power module chamber.

3. The unmanned aerial vehicle of claim 1, wherein the power module comprises at least one cathode electrically coupled to the second positive terminal and at least one anode electrically coupled to the second negative terminal.

4. The unmanned aerial vehicle of claim 1, wherein the housing comprises a retractable latch, and wherein the power module chamber comprises an opening for accommodating the retractable latch when the power module is releasably installed within the power module chamber.

5. An aerial vehicle comprising:

a frame having an upper surface and a lower surface, wherein the upper surface comprises a first opening and wherein the lower surface comprises a second opening;

an electrical circuit for powering at least one electrical load;

a first chamber having a first vertical slot extending between the first opening in the upper surface of the frame and the second opening in the lower surface of the frame; and

a first power module comprising a housing having at least a positive cell and at least one negative cell disposed therein, wherein the first power module is releasably installed within the first chamber,

wherein the first chamber is configured to receive at least the first power module via the second opening,

wherein the first chamber is configured to release at least the first power module via the first opening, and

wherein the first power module is electrically coupled to the electrical circuit when the first power module is releasably installed within the first chamber.

6. The aerial vehicle of claim 5, further comprising at least one of a propulsion motor or a control surface,

wherein the at least one electrical load includes the at least one of the propulsion motor or the control surface.

7. The aerial vehicle of claim 5, wherein the first vertical slot extends laterally between the first chamber and a perimeter of the frame.

8. The aerial vehicle of claim 7, wherein the housing further comprising a second chamber and a second vertical slot extending laterally between the second chamber and a perimeter of the housing, and

wherein the first vertical slot is aligned with the second vertical slot when the first power module is releasably installed within the first chamber.

9. The aerial vehicle of claim 8, wherein the housing comprises a replaceable battery releasably installed therein,

wherein the replaceable battery comprises the positive cell and the negative cell.

10. The aerial vehicle of claim 8, wherein an underside of the housing comprises a first surface having a shape corresponding to a second surface of an engagement device for removing the first power module from the first chamber via the first opening.

11. The aerial vehicle of claim 10, further comprising at least one angled retainer pivotably mounted below the first chamber at the lower surface,

wherein the at least one angled retainer is configured to pivot open upon contact with the second surface of the engagement device.

12. The aerial vehicle of claim 5, further comprising a first positive terminal of the electrical circuit on at least one inner surface of the first chamber and a first negative terminal of the electrical circuit on the at least one inner surface of the first chamber,

wherein the first power module comprises a second positive terminal of the at least one positive cell on at least one outer surface of the first power module and a second negative terminal of the at least one negative cell on the at least one outer surface of the first power module,

wherein the first positive terminal is in contact with the second positive terminal when the first power module is releasably installed within the first chamber, and

wherein the first negative terminal is in contact with the second negative terminal when the first power module is releasably installed within the first chamber.

13. The aerial vehicle of claim 12,

wherein the first power module further comprises at least one radial extension,

wherein the first chamber further comprises at least one spiraling channel extending between the lower surface of the frame and the upper surface of the frame about the first vertical opening,

wherein the at least one spiraling channel is configured to receive the at least one radial extension, and

wherein the first power module is releasably installed within the first chamber with the at least one radial extension inserted into the at least one spiraling channel.

14. The aerial vehicle of claim 5, further comprising a notch on at least one inner surface of the first chamber,

wherein the first power module further comprises a retractable latch on at least one outer surface of the housing, and

wherein the retractable latch extends into the notch when the first power module is releasably installed within the first chamber.

15. The aerial vehicle of claim 5, wherein the first chamber defines an inner cross section having a first shape,

wherein the first power module defines an outer cross section having a second shape, and

wherein the second shape corresponds to the first shape.

16. The aerial vehicle of claim 15, wherein the first shape is one of a first circle, a first oval, a first triangle, a first hexagon or a first octagon, and

wherein the second shape is a corresponding one of a second circle, a second oval, a second triangle, a second hexagon or a second octagon.

17. The aerial vehicle of claim 5, further comprising a second power module electrically coupled to the electrical circuit,

wherein the second power module is at least one of releasably installed within a second chamber or permanently installed within the frame.

18. An aerial vehicle comprising:

a frame having a chamber, wherein the chamber extends between a first opening in an upper surface of the frame and a second opening in a lower surface of the frame, wherein the chamber has a substantially constant cross section defined by at least one internal surface, wherein the at least one internal surface comprises at least one positive terminal and at least one negative terminal for powering an electrical circuit;

at least one electrical load, wherein the at least one electrical load is configured to receive power from the electrical circuit; and

a first power module releasably installed within the chamber, wherein the first power module comprises a first housing having a first cross section that is consistent with the substantially constant cross section of the chamber, a first positive terminal disposed on an outer surface of the first housing and a first negative terminal disposed on the outer surface of the first housing,

wherein the first positive terminal is in contact with the at least one positive terminal of the chamber when the first power module is releasably installed within the chamber,

wherein the aerial vehicle is configured to release the first power module from the chamber via the first opening, and

wherein the aerial vehicle is configured to receive a second power module comprising a second housing having a second cross section that is consistent with the substantially constant cross section of the chamber, a second positive terminal disposed on an outer surface of the second housing and a second negative terminal disposed on the outer surface of the second housing within the chamber via the second opening.

19. The aerial vehicle of claim 18, wherein the substantially constant cross section of the chamber has a shape of one of a circle, an oval, a triangle, a hexagon or an octagon, and

wherein each of the first cross section and the second cross section has a shape in the one of the circle, the oval, the triangle, the hexagon or the octagon.

20. The aerial vehicle of claim 18, wherein the at least one electrical load comprises at least one of:

a control surface;

a control system;

or

a propulsion motor.