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

Patent metadata

Field	Value
Publication number	US-11738874-B2
Application number	US-201916706996-A
Country	US
Kind code	B2
Filing date	Dec 9, 2019
Priority date	Mar 1, 2019
Publication date	Aug 29, 2023
Grant date	Aug 29, 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 electrical system having an electric storage, wherein the electric storage is positioned within the fuselage;
at least one airfoil extending laterally from the fuselage; and
a liquid fuel tank positioned within the at least one airfoil, wherein the aircraft is a fixed-wing, parallel hybrid aircraft, wherein the fuselage defines an interior cabin space, wherein the interior cabin space includes a cabin floor having at least one seat mounted thereon, wherein the electrical system includes a plurality of batteries, wherein the plurality of batteries are mounted on an opposite side of the cabin floor from the at least one seat, wherein the cabin floor defines a lower surface, wherein the electric motor controller is mounted to at least one of the plurality of batteries, on a side of the batteries that is opposite from the lower surface of the cabin floor.

2. The aircraft as recited in claim 1 , further comprising a hybrid electric propulsion system, wherein the electrical system is part of the hybrid electric propulsion system, wherein the hybrid electric propulsion system includes a heat engine.

3. The aircraft as recited in claim 2 , wherein the hybrid electric propulsion system includes an electric motor, wherein the electrical system is electrically coupled to the electric motor by way of a 1000-volt power bus.

4. The aircraft as recited in claim 2 , wherein the hybrid electric propulsion system includes an electric motor, wherein the electrical system is electrically coupled to the electric motor by way of a 500-volt or greater power bus.

5. The aircraft as recited in claim 2 , wherein the hybrid electric propulsion system includes an 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.

6. The aircraft as recited in claim 1 , further comprising a nacelle mounted to the airfoil.

7. The aircraft as recited in claim 6 , further comprising an electric motor mounted within the nacelle, wherein the electrical system is electrically coupled to the electric motor by way of a 1000-volt power bus.

8. The aircraft as recited in claim 6 , further comprising a hybrid electric propulsion system, wherein the electrical system is part of the hybrid electric propulsion system, wherein the hybrid electric propulsion system includes a heat engine and an 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 6 , wherein the liquid fuel tank is positioned at least one of inboard of or outboard of the nacelle.

10. 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.

11. The aircraft as recited in claim 1 , wherein the fuselage includes a venting line for fluid communication between an area outside of the fuselage and an electrical compartment in which the electric storage is positioned.

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 electrical system includes an electric-motor controller, wherein the fuselage includes an electrical system compartment in which the electric-motor controller and the electric storage are positioned.

14. 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.

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

16. The aircraft as recited in claim 1 , further comprising a hybrid electric propulsion system, wherein the electrical system is part of the hybrid electric propulsion system, wherein the hybrid electric propulsion system includes a heat engine and an 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.

17. The aircraft as recited in claim 1 , wherein the plurality of batteries are mounted to the lower surface of the cabin floor.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Becker Frank
• Wang Xi
• Pizzi Antonio
• Lents Charles E

Classifications

• B64D31/06

  actuated automatically · CPC title

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/357

  using batteries · CPC title