Power distribution circuits for electrically powered aircraft

Patent metadata

Field	Value
Publication number	US-12227290-B2
Application number	US-202117202855-A
Country	US
Kind code	B2
Filing date	Mar 16, 2021
Priority date	Oct 27, 2020
Publication date	Feb 18, 2025
Grant date	Feb 18, 2025

Abstract

A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of isolated power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.

First claim

What is claimed is:

1. An electrically powered aircraft comprising:
a plurality of batteries comprising a first battery and a second battery;
a first electric propulsion assembly, a second electric propulsion assembly, a third electric propulsion assembly, and a fourth electric propulsion assembly, wherein the first electric propulsion assembly and the second electric propulsion assembly are disposed diametrically opposed and equal distant relative to a center of gravity of the aircraft, and wherein the third electric propulsion assembly and the fourth electric propulsion assembly are disposed diametrically opposed and equal distant relative to the center of gravity of the aircraft;
a first power distribution system coupling the first battery with each of the first electric propulsion assembly and the second electric propulsion assembly and isolating the first battery from each of the third electric propulsion assembly and the fourth electric propulsion assembly; and
a second power distribution system coupling the second battery with each of the third electric propulsion assembly and the fourth electric propulsion assembly and isolating the second battery from each of the first electric propulsion assembly and the second electric propulsion assembly.

2. The electrically powered aircraft of claim 1 further comprising:
a first contactor coupled between the first battery and the first electric propulsion assembly and between the first battery and the second electric propulsion assembly; and
a second contactor coupled between the second battery and the third electric propulsion assembly and between the second battery and the fourth electric propulsion assembly.

3. The electrically powered aircraft of claim 1 , wherein at least one of:
the first electric propulsion assembly comprises a first electric propulsion assembly propeller, a first electric propulsion assembly shaft configured for rotating the first electric propulsion assembly propeller, a first electric propulsion assembly primary winding configured for rotating the first electric propulsion assembly shaft, a first electric propulsion assembly primary controller configured for controlling delivery of electrical current from the first battery to the first electric propulsion assembly primary winding, a first electric propulsion assembly redundant winding configured for rotating the first electric propulsion assembly shaft, a first electric propulsion assembly redundant controller configured for controlling delivery of electrical current to the first electric propulsion assembly redundant winding from one of the plurality of batteries other than the first battery;
the second electric propulsion assembly comprises a second electric propulsion assembly propeller, a second electric propulsion assembly shaft configured for rotating the second electric propulsion assembly propeller, a second electric propulsion assembly primary winding configured for rotating the second electric propulsion assembly shaft, a second electric propulsion assembly primary controller configured for controlling delivery of electrical current from the first battery to the second electric propulsion assembly primary winding, a second electric propulsion assembly redundant winding configured for rotating the second electric propulsion assembly shaft, a second electric propulsion assembly redundant controller configured for controlling delivery of electrical current to the second electric propulsion assembly redundant winding from one of the plurality of batteries other than the first battery;
the third electric propulsion assembly comprises a third electric propulsion assembly propeller, a third electric propulsion assembly shaft configured for rotating the third electric propulsion assembly propeller, a third electric propulsion assembly primary winding configured for rotating the third electric propulsion assembly shaft, a third electric propulsion assembly primary controller configured for controlling delivery of electrical current from the second battery to the third electric propulsion assembly primary winding, a third electric propulsion assembly redundant winding configured for rotating the third electric propulsion assembly shaft, a third electric propulsion assembly redundant controller configured for controlling delivery of electrical current to the third electric propulsion assembly redundant winding from one of the plurality of batteries other than the second battery; or
the fourth electric propulsion assembly comprises a fourth electric propulsion assembly propeller, a fourth electric propulsion assembly shaft configured for rotating the fourth electric propulsion assembly propeller, a fourth electric propulsion assembly primary winding configured for rotating the fourth electric propulsion assembly shaft, a fourth electric propulsion assembly primary controller configured for controlling delivery of electrical current from the second battery to the fourth electric propulsion assembly primary winding, a fourth electric propulsion assembly redundant winding configured for rotating the fourth electric propulsion assembly shaft, a fourth electric propulsion assembly redundant controller configured for controlling delivery of electrical current to the fourth electric propulsion assembly redundant winding from one of the plurality of batteries other than the second battery.

4. The electrically powered aircraft of claim 3 , wherein at least one of:
the first electric propulsion assembly redundant controller is configured for controlling delivery of electrical current to the first electric propulsion assembly redundant winding from the second battery;
the second electric propulsion assembly redundant controller is configured for controlling delivery of electrical current to the second electric propulsion assembly redundant winding from the second battery;
the third electric propulsion assembly redundant controller is configured for controlling delivery of electrical current to the third electric propulsion assembly redundant winding from the first battery; or
the fourth electric propulsion assembly redundant controller is configured for controlling delivery of electrical current to the fourth electric propulsion assembly redundant winding from the first battery.

5. An electrically powered aircraft comprising:
a plurality of batteries comprising a first battery and a second battery;
a first electric propulsion assembly, a second electric propulsion assembly, a third electric propulsion assembly, and a fourth electric propulsion assembly, wherein the first electric propulsion assembly and the second electric propulsion assembly are disposed diametrically opposed and equal distant relative to a center of gravity of the aircraft, and wherein the third electric propulsion assembly and the fourth electric propulsion assembly are disposed diametrically opposed and equal distant relative to the center of gravity of the aircraft;
a first power distribution system coupling the first battery with each of the first electric propulsion assembly and the second electric propulsion assembly;
a second power distribution system coupling the second battery with each of the second electric propulsion assembly and the fourth electric propulsion assembly; and
a fuse coupling the first battery with each of the third electric propulsion assembly and the fourth electric propulsion assembly and the second battery with each of the first electric propulsion assembly and the second electric propulsion assembly, wherein the fuse is configured to blow in response to an electrical failure to isolate the first battery from each of the third electric propulsion assembly and the fourth electric propulsion assembly and isolate the second battery from each of the first electric propulsion assembly and the second electric

Assignees

• Wisk Aero Llc

Inventors

• Long Geoffrey Alan
• Hom Lewis Romeo

Classifications

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• H02J2105/32

  for aircrafts · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title