Systems and methods for power distribution in electric aircraft

Patent metadata

Field	Value
Publication number	US-12522352-B2
Application number	US-202318303032-A
Country	US
Kind code	B2
Filing date	Apr 19, 2023
Priority date	Jul 8, 2020
Publication date	Jan 13, 2026
Grant date	Jan 13, 2026

Abstract

The present disclosure relates generally to electric aircraft, and more specifically to electric power distribution for electric aircraft. In one embodiment, an electric aircraft is disclosed, comprising: a fuselage; two wings mounted on opposite sides of the fuselage; a plurality of first electric propulsion units, arranged on both sides of the fuselage, aft of the wings during forward flight; a plurality of second electric propulsion units arranged on both sides of the fuselage, forward of the wings during forward flight; and a plurality of battery packs, each battery pack configured to power at least: a portion of one of the first electric propulsion units on one side of the fuselage, and a portion of one of the second electric propulsion units on the other side of the fuselage.

First claim

The invention claimed is:

1 . An electric aircraft, comprising:
a fuselage; two wings mounted on opposite sides of the fuselage; a plurality of first electric propulsion units, arranged on both sides of the fuselage, aft of the wings during forward flight; a plurality of second electric propulsion units arranged on both sides of the fuselage, forward of the wings during forward flight; and a plurality of battery packs, each battery pack configured to power:
a partial motor of one of the first electric propulsion units on one side of the fuselage, and
a partial motor of one of the second electric propulsion units on the other side of the fuselage.

2 . The electric aircraft of claim 1 , wherein one of the battery packs is configured to power:
a partial motor of one of the first electric propulsion units arranged farthest from and on one side of the fuselage; and a partial motor of one of the second electric propulsion units arranged farthest from and on the other side of the fuselage.

3 . The electric aircraft of claim 1 , wherein one of the battery packs is configured to power:
a partial motor of one of the first electric propulsion units arranged nearest to the fuselage to one of the wings; and a partial motor of one of the second electric propulsion units arranged nearest to the fuselage to the other wing.

4 . The electric aircraft of claim 2 , wherein the one of the battery packs is configured to power the respective partial motor of one of the first electric propulsion units, and the respective partial motor of one of the second electric propulsion units via a dedicated electric power bus for that battery pack.

5 . The electric aircraft of claim 4 , wherein dedicated electric power buses for each battery pack are electrically isolated from each other.

6 . The electric aircraft of claim 1 ,
wherein a number of first electric propulsion units is six, three of the first electric propulsion units adjacent to one of the wings and the other three first electric propulsion units adjacent to the other wing; wherein a number of second electric propulsion units is six, three of the second electric propulsion units adjacent to one of the wings and the other three second electric propulsion units adjacent to the other wing; wherein one of the battery packs is configured to power:
a partial motor of one of the first electric propulsion units arranged between the other two first electric propulsion units adjacent to one of the wings; and
a partial motor of one of the second electric propulsion units arranged between the other two second electric propulsion units adjacent to the other wing.

7 . The electric aircraft of claim 6 , wherein the one of the battery packs is configured to power at least a partial motor of one of the first electric propulsion units arranged between the other two first electric propulsion units adjacent to one of the wings, and a partial motor of one of the second electric propulsion units arranged between the other two second electric propulsion units adjacent to the other wing, via a dedicated electric power bus for that battery pack.

8 . The electric aircraft of claim 1 , wherein each battery pack is configured to power a partial motor of one of the first electric propulsion units adjacent to one of the wings, and a partial motor of one of the second electric propulsion units adjacent to the other wing, via a dedicated electric power bus for that battery pack.

9 . The electric aircraft of claim 1 , wherein no two of the battery packs power the same partial motor of any of the first electric propulsion units.

10 . The electric aircraft of claim 1 , wherein no two of the battery packs power the same partial motor of any of the second electric propulsion units.

11 . The electric aircraft of claim 1 , wherein no two of the battery packs power the same partial motor of any of the first electric propulsion units or the second electric propulsion units.

12 . The electric aircraft of claim 9 , wherein at least two of the battery packs power different partial motors of one of the first electric propulsion units.

13 . The electric aircraft of claim 10 , wherein at least two of the battery packs power different partial motors of one of the second electric propulsion units.

14 . The electric aircraft of claim 11 , wherein at least two of the battery packs power different partial motors of one of the first electric propulsion units and one of the second electric propulsion units.

15 . The electric aircraft of claim 1 , wherein each first electric propulsion unit is powered by only one of the battery packs.

16 . The electric aircraft of claim 1 , wherein each second electric propulsion unit is powered by only one of the battery packs.

17 . The electric aircraft of claim 1 , further comprising:
a plurality of contactors, each contactor configured to electrically isolate one of the battery packs from at least the partial motor of one of the first electric propulsion units adjacent to one of the wings and the partial motor of one of the second electric propulsion units adjacent to the other wing that the battery pack is configured to power.

18 . The electric aircraft of claim 17 , wherein each contactor is electrically coupled to a positive terminal of its associated battery pack.

19 . The electric aircraft of claim 17 , wherein each contactor is electrically coupled to a negative terminal of its associated battery pack.

20 . The electric aircraft of claim 1 , further comprising:
a plurality of fuses, each fuse configured to electrically isolate one of the battery packs from at least the partial motor of one of the first electric propulsion units adjacent to one of the wings and the partial motor of one of the second electric propulsion units adjacent to the other wing that the battery pack is configured to power.

21 . The electric aircraft of claim 1 , wherein each fuse is electrically coupled to a positive terminal of its associated battery pack.

22 . The electric aircraft of claim 1 , wherein the first electric propulsion units, the second electric propulsion units, or the first electric propulsion units and the second electric propulsion units are mounted to the wings via booms.

23 . The electric aircraft of claim 1 , wherein the plurality of first electric propulsion units are configured to provide lift.

24 . The electric aircraft of claim 1 , wherein the plurality of second electric propulsion units are tiltable between vertical lift and forward propulsion configurations.

Assignees

• Archer Aviation Inc

Inventors

• Bower Geoffrey C
• Greek Benjamin M
• Depenbusch Nathan T
• Melack John

Classifications

• H02J7/855

  with circuits adapted for supplying loads from the battery · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/357 Primary

  using batteries · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64D27/30

  Aircraft characterised by electric power plants · CPC title