Aircraft having hybrid-electric propulsion system with electric storage located in fuselage

Patent metadata

Field	Value
Publication number	US-11807371-B2
Application number	US-202016900681-A
Country	US
Kind code	B2
Filing date	Jun 12, 2020
Priority date	Jun 14, 2019
Publication date	Nov 7, 2023
Grant date	Nov 7, 2023

Abstract

An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage defining a longitudinal axis between a forward end and an aft end;
an airfoil extending laterally from the fuselage; and
an electrical system configured to power an electric motor of a hybrid electric propulsion system, the electrical system including:
an electric storage and an electric-motor controller electrically connected to the electric storage, wherein the electric-motor controller is positioned on or in the fuselage and wherein the electric storage is positioned within the fuselage; and
at least one conductor configured to extend from the electric storage to the electric motor to electrically connect the electric storage and the electric motor, wherein the at least one conductor follows a circumferential curvature of the fuselage, wherein at least one conductor of the at least one conductor extends from the electric storage up a first side of a cabin wall circumferentially about the longitudinal axis of the fuselage to the electric motor controller, wherein at least one conductor of the at least one conductor extends from the electric motor controller to the electric motor in a direction perpendicular to the longitudinal axis.

2. The aircraft as recited in claim 1 , wherein the electric-motor controller is positioned in a wing space above the fuselage.

3. The aircraft as recited in claim 1 , wherein the at least one conductor is part of a DC circuit.

4. The aircraft as recited in claim 1 , wherein the airfoil extends laterally from the fuselage in a direction opposite from the first side of the cabin wall, and further comprising a nacelle mounted to the airfoil, wherein the electric motor is positioned in at least one of the airfoil or the nacelle.

5. The aircraft as recited in claim 4 , wherein the electrical system is electrically coupled to the electric motor by way of a power bus extending from the electric-motor controller through the airfoil.

6. The aircraft as recited in claim 5 , wherein the power bus include five conductors.

7. The aircraft as recited in claim 5 , wherein the power bus is part of an AC circuit.

8. The aircraft as recited in claim 4 , further comprising the hybrid electric propulsion system, wherein the hybrid electric propulsion system includes a heat engine and the electric motor, wherein the electric storage is operatively connected to the electric motor for receiving power therefrom or for supplying power thereto, and wherein the heat engine and the electric motor are positioned within the nacelle.

9. The aircraft as recited in claim 1 , further comprising, the hybrid electric propulsion system including the electric motor, wherein the electrical system is electrically coupled to the electric motor by way of a 1000-volt power bus.

10. The aircraft as recited in claim 1 , further comprising the hybrid electric propulsion system including the electric motor, wherein the electrical system is electrically coupled to the electric motor by way of a high voltage power bus.

11. The aircraft as recited in claim 1 , further comprising the hybrid electric propulsion system including the electric motor, wherein the electrical system and the electric storage are operatively connected to the electric motor for receiving power therefrom or for supplying power thereto.

12. The aircraft as recited in claim 1 , wherein the fuselage includes an electrical compartment in which the electric storage is positioned, wherein the electrical compartment includes a lining that is at least one of fire proof or fire resistant.

13. The aircraft as recited in claim 1 , wherein the electric storage includes a plurality of batteries, wherein the fuselage includes an electrical compartment in which the plurality of batteries are stored.

14. The aircraft as recited in claim 1 , wherein the electric storage includes a liquid cooling circuit.

15. The aircraft as recited in claim 1 , further comprising the hybrid electric propulsion system, wherein the hybrid electric propulsion system includes a heat engine and the electric motor, the aircraft further comprising a 28V aircraft power system connected to the hybrid electric propulsion system for generating 28V of aircraft power supply for aircraft systems.

16. The aircraft as recited in claim 1 , wherein the electrical system includes a battery management unit connected by a power bus to the electric storage.

17. The aircraft as recited in claim 16 , wherein the battery management unit is positioned in the wing box or other space above the fuselage.

18. The aircraft as recited in claim 1 , wherein the fuselage includes at least one opening for providing fluid communication between an area outside of the fuselage and an electrical compartment in which the electric storage is positioned.

19. An aircraft comprising:
a fuselage defining:
a longitudinal axis between a forward end and an aft end; and
an interior cabin space including a cabin wall and a cabin floor on a lower surface of the cabin;
an electrical system configured to power an electric motor of a hybrid electric propulsion system, the electrical system including:
an electric storage and an electric-motor controller electrically connected to the electric storage, wherein the electric-motor controller and the electric storage are positioned within the interior cabin space; and
at least one conductor configured to extend from the electric storage to the electric motor to electrically connect the electric storage and the electric motor, wherein the electrical system includes a plurality of batteries, wherein the plurality of batteries are mounted to the top surface of the cabin floor and are at least partially contained within an electrical compartment in a passenger section of the interior cabin space.

20. The aircraft as recited in claim 19 , wherein the fuselage includes at least one opening for providing fluid communication between an area outside of the fuselage and the electrical compartment in which the batteries are mounted.

21. The aircraft as recited in claim 19 , wherein the fuselage includes a venting line for fluid communication between an area outside of the fuselage and the electrical compartment in which the batteries are mounted.

22. An aircraft having a hybrid electric propulsion system comprising, an electric motor and a heat engine, the aircraft comprising a fuselage defining:
a longitudinal axis between a forward end and an aft end; and
an electrical system of the hybrid electric propulsion system having an electric storage and an electric-motor controller electrically connected to the electric storage, wherein the electric-motor controller is positioned on a top portion of the aircraft, wherein the electric storage is positioned on a bottom side of the cabin of the aircraft opposite from the electric-motor controller, wherein the electrical system includes at least one conductor extending form the electric storage, up a first side of the cabin wall of the aircraft to the electric-motor controller.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Becker Frank
• Abruzzese Frank
• Linteau Patrick
• Wang Xi
• Pizzi Antonio
• Lents Charles E
• Buzzard John N

Classifications

• B64D27/31

  within, or attached to, wings · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64C1/18 Primary

  Floors · CPC title