Aircraft with distributed hydraulic system

Patent metadata

Field	Value
Publication number	US-2018178902-A1
Application number	US-201615737922-A
Country	US
Kind code	A1
Filing date	Jun 23, 2016
Priority date	Jun 30, 2015
Publication date	Jun 28, 2018
Grant date	—

Abstract

An aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

First claim

1 . An aircraft comprising:
an aircraft structure; a flight control surface attached to the aircraft structure; and a local hydraulic power pack disposed proximal to the flight control surface and configured to provide pressurized hydraulic fluid for actuating the flight control surface, the local hydraulic power pack comprising a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

2 . The aircraft as defined in claim 1 , wherein the flight control surface is configured to be actuated exclusively using the pressurized hydraulic fluid from the local hydraulic power pack.

3 . The aircraft as defined in claim 1 , wherein the local hydraulic power pack is configured to combine the hydraulic fluid pressurized by both of the hydraulic pumps.

4 . The aircraft as defined in claim 1 , wherein the reservoir is a common reservoir that supplies both of the hydraulic pumps.

5 . The aircraft as defined in claim 1 , wherein the hydraulic pumps are configured to be driven by different power sources.

6 . The aircraft as defined in claim 5 , wherein each hydraulic pump is configured to be controlled using power from a respective one of the different power sources.

7 . The aircraft as defined in claim 1 , wherein the hydraulic pumps are configured to be electrically driven by respective motors powered by different electrical power busses.

8 . The aircraft as defined in claim 7 , comprising two power and control modules where each power and control module is associated with a respective one of the motors and is powered by a respective one of the different electrical power busses.

9 . The aircraft as defined in claim 1 , comprising:
a plurality of hydraulic actuators for actuating the flight control surface; and a manifold configured to receive pressurized hydraulic fluid from both hydraulic pumps and distribute the pressurized hydraulic fluid to the hydraulic actuators.

10 . The aircraft as defined in claim 9 , wherein none of the plurality of hydraulic actuators of the flight control surface is coupled to a central hydraulic system of the aircraft.

11 . The aircraft as defined in claim 1 , wherein the aircraft structure comprises a wing and the local hydraulic power pack is disposed inside of the wing.

12 . The aircraft as defined in claim 1 , wherein the flight control surface is an aileron.

13 . The aircraft as defined in claim 1 , wherein the aircraft structure comprises an empennage.

14 . The aircraft as defined in claim 13 , wherein the local hydraulic power pack is disposed in an aft portion of the aircraft.

15 . The aircraft as defined in claim 13 , wherein the flight control surface is an elevator.

16 . The aircraft as defined in claim 13 , wherein the flight control surface is a rudder.

17 . An aircraft comprising:
an aircraft structure comprises an empennage; a plurality of flight control surfaces attached to the empennage; and a plurality of local hydraulic power packs disposed proximal to the flight control surfaces and configured to provide pressurized hydraulic fluid for actuating the flight control surfaces, each local hydraulic power pack comprising a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

18 . The aircraft as defined in claim 17 , wherein:
the aircraft comprises a plurality of hydraulic actuators for actuating the flight control surfaces; the plurality of flight control surfaces comprise two elevators and a rudder; and a first hydraulic actuator of a first elevator and a first hydraulic actuator of the rudder are configured to be actuated via a first local hydraulic power pack; a second hydraulic actuator of the first elevator, a second hydraulic actuator of the rudder and a first hydraulic actuator of a second elevator are configured to be actuated via a second local hydraulic power pack; and a second hydraulic actuator of the second elevator and a third hydraulic actuator of the rudder are configured to be actuated via a third local hydraulic power pack.

19 . The aircraft as defined in claim 18 , wherein:
the aircraft structure comprises a wing; the plurality of flight control surfaces comprise an aileron; and the a plurality of local hydraulic power packs comprise a fourth local hydraulic power pack configured to provide pressurized hydraulic fluid for actuating the aileron, the fourth local hydraulic power pack being disposed inside of the wing.

20 . The aircraft as defined in claim 18 , wherein the first, second and third local hydraulic power packs are disposed in an aft portion of the aircraft.

21 . The aircraft as defined in claim 18 , wherein none of the plurality of hydraulic actuators is coupled to a central hydraulic system of the aircraft.

22 . The aircraft as defined in claim 17 , wherein each local hydraulic power pack is configured to combine the hydraulic fluid pressurized by both of its hydraulic pumps.

23 . The aircraft as defined in claim 17 , wherein the two hydraulic pumps of each local hydraulic power pack are driven by different power sources.

24 . The aircraft as defined in claim 23 , wherein each of the two hydraulic pumps is configured to be controlled using power from a respective one of the different power sources.

25 . The aircraft as defined in claim 17 , wherein the two hydraulic pumps of each local hydraulic power pack are configured to be electrically driven by different motors powered by different electrical power busses.

26 . The aircraft as defined in claim 25 , comprising a power and control module associated with each of the motors and powered by a respective one of the different electrical power busses.

Assignees

• Bombardier Inc

Inventors

• Nfonguem Gustave
• Iliescu Vlad
• Ardman Avraham

Classifications

• B64C13/504 Primary

  using electro-hydrostatic actuators [EHA's] · CPC title

• B64C2009/005

  Ailerons · CPC title

• B64C9/00 Primary

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• B64C13/42 Primary

  having duplication or stand-by provisions · CPC title

• B64C5/10

  adjustable · CPC title