Aircraft power system

Patent metadata

Field	Value
Publication number	US-11713777-B2
Application number	US-202117515319-A
Country	US
Kind code	B2
Filing date	Oct 29, 2021
Priority date	Nov 27, 2020
Publication date	Aug 1, 2023
Grant date	Aug 1, 2023

Abstract

Aircraft power system is disclosed having a hydraulic reservoir, a bi-directional hydraulic pump for pumping hydraulic fluid to and from the reservoir, and an electric motor. The electric motor is connectable to a first driveable component of the aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft. The hydraulic pump is connectable to the first driveable component of the aircraft such that the hydraulic pump is arranged to pump hydraulic fluid from the reservoir to drive the first driveable component of an aircraft. Thus, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the hydraulic pump.

First claim

The invention claimed is:

1. An aircraft power system, comprising:
i) a hydraulic reservoir,
ii) a bi-directional hydraulic pump for pumping hydraulic fluid to and from the hydraulic reservoir, and
iii) an electric motor,
wherein the electric motor is connectable to a first driveable component of aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft, and
wherein the bi-directional hydraulic pump is connectable to the first driveable component of the aircraft such that the bi-directional hydraulic pump is arranged to drive the first driveable component, such that, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the bi-directional hydraulic pump,
wherein the electric motor and bi-directional hydraulic pump are connected in parallel such that, in the first driveable mode of operation, both are arranged to supply power to the driveable component independently of the other, and
wherein the electric motor is connectable to the bi-directional hydraulic pump such that, during a replenishing mode of operation, the electric motor is arranged to drive the bi-directional hydraulic pump to pump hydraulic fluid into the hydraulic reservoir.

2. The aircraft power system of claim 1 , wherein the electric motor and bi-directional hydraulic pump are connected to a transfer unit and wherein the transfer unit is connectable to the driveable component.

3. The aircraft power system of claim 1 , wherein the electric motor also functions as a generator such that, in a regenerating mode of operation, the electric motor is externally driven by a moveable component of the aircraft to generate electricity.

4. The aircraft power system of claim 1 , wherein the bi-directional hydraulic pump is also connectable to other driveable components of the aircraft.

5. The aircraft power system of claim 1 , wherein the electric motor is connectable to the bi-directional hydraulic pump such that the electric motor is arranged to drive the bi-directional hydraulic pump to pump hydraulic fluid out of the hydraulic reservoir.

6. The aircraft power system of claim 1 , wherein the first driveable component comprises one or more landing gear wheels.

7. The aircraft power system of claim 1 , wherein:
the electric motor also functions as a generator such that, in a regenerating mode of operation, the electric motor is externally driven by the first driveable component to generate electricity;
the bi-directional hydraulic pump is arranged such that, in the regenerating mode of operation, the bi-directional hydraulic pump is externally driven by the first driveable component to pump hydraulic fluid into the hydraulic reservoir.

8. An aircraft landing gear drive system comprising the aircraft power system of claim 1 , wherein the first driveable component comprises one or more landing gear wheels of the landing gear drive system, and wherein the electric motor and the bi-directional hydraulic pump are both connected to the one or more landing gear wheels, such that the electric motor and the bi-directional hydraulic pump are both able to drive the one or more landing gear wheels.

9. An aircraft having a power system, the power system comprising:
i) a hydraulic reservoir,
ii) a bi-directional hydraulic pump arranged to drive a first driveable component of the aircraft and for pumping hydraulic fluid to and from the hydraulic reservoir,
iii) an electric motor arranged to drive the first driveable component of the aircraft,
the power system being arranged such that in a first driveable mode of operation, the electric motor and bi-directional hydraulic pump are connected in parallel such that both supply power to and drive the driveable component independently of the other, and
during a replenishing mode of operation, the electric motor is arranged to drive the bi-directional hydraulic pump to pump hydraulic fluid into the hydraulic reservoir.

10. A method of operating the aircraft of claim 9 , wherein, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the bi-directional hydraulic pump.

11. The method of claim 10 , wherein in a replenishing mode of operation, the electric motor drives the hydraulic pump to pump hydraulic fluid into the hydraulic reservoir.

12. The method of claim 10 , wherein in a second driveable mode of operation, the bi-directional hydraulic pump provides hydraulic power to one or more other driveable components.

13. The method of claim 12 , wherein, in the second driveable mode of operation, the electric motor drives the bi-directional hydraulic pump to provide hydraulic power to the other driveable components.

14. The method of claim 9 , wherein, in a first driveable mode of operation, one only of the electric motor and hydraulic pump provides power to and drives the driveable component, as a result of a failure in the capability of the other of the electric motor and hydraulic pump to provide such power.

15. The aircraft power system of claim 1 , wherein the connection of the electric motor and hydraulic pump in parallel is such that if one of the electric motor and hydraulic pump should fail when operating in the first driveable mode of operation, power is still provided to the driveable component by the other of the electric motor and hydraulic pump.

16. An aircraft power system, comprising:
i) a hydraulic reservoir,
ii) a bi-directional hydraulic pump for pumping hydraulic fluid to and from the hydraulic reservoir, and
iii) an electric motor,
wherein the electric motor is connectable to a first driveable component of an aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft,
wherein the bi-directional hydraulic pump is connectable to the first driveable component of the aircraft such that the bi-directional hydraulic pump is arranged to drive the first driveable component, such that, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the bi-directional hydraulic pump, and
in a regenerating mode of operation each of the electric motor and the hydraulic pump are connectable to a moveable component of the aircraft such that each of the electric motor and the hydraulic pump can function as a generator to recover kinetic energy from the moveable component, as a result of being driven by the moveable component, and
wherein in the regenerating mode, the operation comprises prioritizing energy recovery by the hydraulic pump over energy recovery by the electric motor.

17. The aircraft power system of claim 16 , wherein in the regenerating mode of operation
the electric motor is externally driven using the kinetic energy from the moveable component of the aircraft to generate electricity, and
the hydraulic pump is driven using the kinetic energy from the moveable component to pump hydraulic fluid into the hydraulic fluid reservoir.

18. The aircraft power system of claim 16 , wherein the electric motor and bi-directional hydraulic pump are connectable in parallel to the driveable component such that, in the first driveable mode of operation, both are arranged to supply power to the driveable component independently of the other.

19. The aircraft power system of claim 16 , wherein the electric motor is connectable to the bi-directional hydraulic pump such that, during a replenishing mode of operation, the electric motor is arranged to drive the bi-directional hydraulic pump to

Assignees

• Airbus Operations Ltd

Inventors

• Sadler Andrew David

Classifications

• F15B15/18 Primary

  Combined units comprising both motor and pump · CPC title

• B64C25/22

  fluid · CPC title

• B64C25/24

  electric · CPC title

• F15B13/0444

  with rotary electric motor · CPC title

• F15B2211/20515

  Electric motor · CPC title