Aircraft hybrid cooling system

Patent metadata

Field	Value
Publication number	US-10903535-B2
Application number	US-201816201832-A
Country	US
Kind code	B2
Filing date	Nov 27, 2018
Priority date	Aug 11, 2017
Publication date	Jan 26, 2021
Grant date	Jan 26, 2021

Abstract

An aircraft hybrid cooling system is disclosed. The aircraft hybrid cooling system includes a conduit through an aircraft that is configured to allow airflow through the conduit. The aircraft hybrid cooling system additionally includes a battery assembly positioned in the conduit, configured to provide for airflow past a battery in the battery assembly in a first mode of operation and configured to provide flow of a cooling medium past the battery in a second mode of operation. In some embodiments, the battery in the battery assembly is cooled via airflow in the event the aircraft is in flight and is cooled via an applied cooling medium in the event the aircraft is grounded.

First claim

What is claimed is:

1. An aircraft hybrid cooling system, comprising:
a conduit through an aircraft fuselage of an aircraft, configured to allow airflow through the conduit, the conduit including a first end positioned at or adjacent to an underside of the aircraft fuselage and a second end positioned at or adjacent to a top side of the aircraft fuselage; and
a battery assembly positioned in the conduit, configured to provide for airflow past a battery in the battery assembly in a first mode of operation in which airflow enters the conduit at the first end and exits at the second end and configured to provide flow of a cooling medium past the battery in a second mode of operation in which the cooling medium enters the conduit at the second end, flows through the conduit at least in part due to the force of gravity, and exists at the first end;
wherein an opening at the second end of the conduit is aligned with and configured to receive a quantity of the cooling medium from a source of the cooling medium in the second mode of operation, and
wherein, during at least a first phase of the second mode of operation, the system further comprises a stopper positioned to prevent the cooling medium from exiting the conduit at the first end.

2. The system of claim 1 , wherein the aircraft is in flight in the first mode of operation.

3. The system of claim 1 , wherein the aircraft is on land in the second mode of operation.

4. The system of claim 1 , wherein the conduit is configured to enable airflow through the conduit to cool the battery in the battery assembly during forward flight.

5. The system of claim 1 , wherein the cooling medium comprises water.

6. The system of claim 1 , wherein the cooling medium comprises oil.

7. The system of claim 1 , wherein the cooling medium comprises a chilled liquid.

8. The system of claim 1 , wherein the conduit comprises a continuous, unobstructed upward slope from the battery to an outlet positioned at an end of the conduit.

9. The system of claim 1 , wherein the battery assembly includes structures that allow gas and liquid to pass through the battery assembly and access one or more batteries stored in the battery assembly.

10. The system of claim 1 , wherein the quantity of the cooling medium is sufficient relative to a volume of the conduit and a position of the battery assembly within the conduit to immerse the battery assembly in the cooling medium.

11. A method to cool a battery assembly using an aircraft hybrid cooling system comprising a conduit through an aircraft fuselage, configured to allow airflow through the conduit, the conduit including a first end positioned at or adjacent to an underside of the aircraft fuselage and a second end positioned at or adjacent to a top side of the aircraft fuselage, and a battery assembly positioned in the conduit, configured to provide for airflow past a battery in the battery assembly in a first mode of operation in which airflow enters the conduit at the first end and exits at the second end and configured to provide flow of a cooling medium past the battery in a second mode of operation, the method comprising:
positioning a stopper to prevent the cooling medium from exiting the conduit at the first end;
aligning a source of the cooling medium with an opening at the second end of the conduit; and
supplying a quantity of the cooling medium into the conduit via the opening at the second end of the conduit.

12. The method of claim 11 , wherein the cooling medium comprises water.

13. The method of claim 11 , wherein the cooling medium comprises oil.

14. The method of claim 11 , wherein the cooling medium comprises a chilled liquid.

15. The method of claim 11 , further comprising determining the battery assembly has been cooled sufficiently.

16. The method of claim 15 , further comprising removing the stopper.

17. The method of claim 16 , wherein removal of the stopper allows the quantity of the cooling medium to flow out of the conduit via the first end.

18. The method of claim 11 , wherein the conduit comprises a continuous, unobstructed upward slope from the battery to an outlet positioned at an end of the conduit.

19. The method of claim 11 , wherein the battery assembly includes structures that allow gas and liquid to pass through the battery assembly and access one or more batteries stored in the battery assembly.

20. The method of claim 11 , wherein the quantity of the cooling medium is sufficient relative to a volume of the conduit and a position of the battery assembly within the conduit to immerse the battery assembly in the cooling medium.

Assignees

• Wisk Aero Llc

Inventors

• Melack John
• Muniz Thomas P
• Allison Eric

Classifications

• H01M10/486

  for measuring temperature · CPC title

• H01M50/222

  Inorganic material · CPC title

• H01M50/224

  Metals · CPC title

• H01M50/204

  Racks, modules or packs for multiple batteries or multiple cells · CPC title

• H01M10/6564

  using compressed gas · CPC title