Emergency energy reserve solution for battery electrified aircraft

Patent metadata

Field	Value
Publication number	US-12552543-B2
Application number	US-202418414676-A
Country	US
Kind code	B2
Filing date	Jan 17, 2024
Priority date	Jan 17, 2023
Publication date	Feb 17, 2026
Grant date	Feb 17, 2026

Abstract

A power distribution control approach employs power distribution buses that are controllably energized and de-energized to control which aerial vehicle systems received power based on the applicable operational mode. A method of controlling power distribution in an electrically powered vertical takeoff and landing aircraft includes receiving an operational mode indication that identifies an operational mode. The operational mode is one of predetermined operational modes for the aircraft. Power distribution buses of the aircraft are controlled, based on the operational mode indication, to control each of the power distribution buses to be energized or de-energized.

First claim

What is claimed is:

1 . A method of controlling power distribution in an electrically powered vertical takeoff and landing aircraft, the method comprising:
receiving an operational mode indication that identifies an operational mode, wherein the operational mode is one of predetermined operational modes for an aircraft; controlling power distribution buses of the aircraft, based on the operational mode indication, to control each of the power distribution buses to be energized or de-energized; and supplying high-voltage power to a propulsion power bus and an air-conditioning power bus, and supplying low-voltage power to at least two subsystems via a direct-current-to-direct-current (DC-DC) converter that electrically isolates the low-voltage power from the high-voltage power; wherein the controlling the power distribution buses comprises, responsive to the operational mode indication corresponding to a transition from a flight mode to an emergency flight mode with an initiation of an emergency landing procedure, de-energizing the air-conditioning power bus and a subset of the at least two subsystems while continuing to supply the low-voltage power to at least one subsystem of the at least two subsystems via the DC-DC converter.

2 . The method of claim 1 , wherein:
the power distribution buses comprise at least one subsystems bus; the propulsion power bus is configured to supply power to propulsion system motors of the aircraft; the air-conditioning power bus is configured to supply power to an air-conditioning system of the aircraft; and the at least one subsystems bus is configured to supply power to subsystems of the aircraft.

3 . The method of claim 2 , wherein:
the at least one subsystems bus comprises a first subsystems bus and a second subsystems bus; and each of the first subsystems bus and the second subsystems bus is configured to supply power to the subsystems of the aircraft to provide redundancy.

4 . The method of claim 2 , wherein:
the predetermined operational modes comprise a normal flight mode and the emergency flight mode; in the normal flight mode, each of the propulsion power bus, the air-conditioning power bus, and the at least one subsystems bus is energized; and in the emergency flight mode, the air-conditioning power bus is de-energized and each of the propulsion power bus and the at least one subsystems bus is energized.

5 . The method of claim 4 , wherein the predetermined operational modes further comprise an emergency landing mode in which the at least one subsystems bus is energized and each of the propulsion power bus and the air-conditioning power bus is de-energized.

6 . The method of claim 2 , wherein:
the predetermined operational modes comprise at least one of a maintenance lockout mode, a maintenance accessory mode, or a hot maintenance mode; in the maintenance lockout mode, each of the propulsion power bus, the air-conditioning power bus, and the at least one subsystems bus is de-energized; in the maintenance accessory mode, the propulsion power bus is de-energized and each of the air-conditioning power bus and the at least one subsystems bus is energized; and in the hot maintenance mode, each of the air-conditioning power bus and the at least one subsystems bus is energized, and the propulsion power bus can be selectively energized or de-energized.

7 . The method of claim 2 , wherein:
the predetermined operational modes comprise one or more passenger transfer modes for use during ingress and/or egress of passengers; the one or more passenger transfer modes comprise one or more of a power off mode, a standby mode, or a battery charging mode; in the power off mode, each of the propulsion power bus and the air-conditioning power bus is deenergized; in the standby mode, the propulsion power bus is de-energized and each of the air-conditioning power bus and the at least one subsystems bus is energized; and in the battery charging mode, the propulsion power bus is de-energized, and the air-conditioning power bus is energized.

8 . The method of claim 2 , wherein:
the predetermined operational modes comprise one or more mission modes; the one or more mission modes comprise one or more of an armed mode and a normal flight mode; in the armed mode, the propulsion power bus is de-energized and each of the air-conditioning power bus and the at least one subsystems bus is energized; and in the normal flight mode, each of the propulsion power bus, the air-conditioning power bus, and the at least one subsystems bus is energized.

9 . The method of claim 2 , wherein:
the aircraft comprises a high-voltage battery that supplies the high-voltage power to at least one of the propulsion power bus or the air-conditioning power bus; and the aircraft comprises a low-voltage tap via which the high-voltage battery supplies the low-voltage power to the at least one subsystems bus.

10 . The method of claim 9 , wherein the low-voltage tap comprises the DC-DC converter that regulates a voltage of the low-voltage power supplied to the at least one subsystems bus.

11 . The method of claim 10 , wherein the voltage of the low-voltage power is less than 25 percent of a voltage of the high-voltage power.

12 . The method of claim 2 , wherein:
the aircraft comprises high-voltage batteries that supply the high-voltage power to the propulsion power bus and the air-conditioning power bus; and the aircraft comprises low-voltage taps via which the high-voltage batteries supply the low-voltage power to the at least one subsystems bus.

13 . The method of claim 12 , wherein each of the low-voltage taps comprises a DC-DC converter that regulates a voltage of the low-voltage power supplied to the at least one subsystems bus.

14 . The method of claim 13 , wherein the voltage of the low-voltage power is less than 25 percent of a voltage of the high-voltage power.

15 . An aerial vehicle comprising:
propulsion units that are electrically powered; an air-conditioning system; subsystems that are electrically powered; a propulsion power bus configured to supply electrical power to the propulsion units; an air-conditioning power bus configured to supply electrical power to the air-conditioning system; at least one subsystems bus configured to supply electrical power to the subsystems; a control unit comprising at least one processor; and a memory device storing non-transitory instructions executable by the at least one processor to cause the at least one processor to control each of the propulsion power bus, the air-conditioning power bus, and the at least one subsystems bus, based on an operational mode indication, to be energized or de-energized, wherein the operational mode indication indicates one of predetermined operational modes for the aerial vehicle; wherein the aerial vehicle is configured to supply high-voltage power to the propulsion power bus and an air-conditioning power bus and supply low-voltage power to at least two subsystems via a direct-current-to-direct-current (DC-DC) converter that electrically isolates the low-voltage power from the high-voltage power; and wherein the controlling comprises, responsive to the operational mode indication corresponding to a transition from a flight mode to an emergency flight mode with an initiation of an emergency landing procedure, de-energizing the air-conditioning power bus and a subset of the at least two subsystems while continuing to supply the low-voltage power to at least one subsystem of the at least two subsystems via the DC-DC converter.

16 . The aerial vehicle o

Assignees

• Wisk Aero Llc

Inventors

• Gao Rui
• Burgart Michael John
• Long Geoffrey Alan

Classifications

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64C29/0008

  having its flight directional axis horizontal when grounded · CPC title

• B60L2200/10

  Air crafts · CPC title

• B60L2210/00

  Converter types · CPC title

• B60L50/60

  using power supplied by batteries (in combination with fuel cells B60L50/75) · CPC title