US 12,392,360 B2
Method and apparatus for generating hydraulic power in an aircraft
Lars Hoffmann, Stuhr (DE); Rolf Goessing, Bremen (DE); and Martin Hamm, Bremen (DE)
Assigned to Airbus Operations GmbH, Hamburg (DE)
Filed by Airbus Operations GmbH, Hamburg (DE)
Filed on Mar. 29, 2024, as Appl. No. 18/622,719.
Claims priority of application No. 23165763 (EP), filed on Mar. 31, 2023.
Prior Publication US 2024/0328436 A1, Oct. 3, 2024
Int. Cl. F15B 11/17 (2006.01); B64C 13/42 (2006.01); B64D 41/00 (2006.01); F04B 23/04 (2006.01); F04B 49/06 (2006.01); F15B 13/06 (2006.01)
CPC F15B 11/17 (2013.01) [B64C 13/42 (2013.01); B64D 41/00 (2013.01); F04B 23/04 (2013.01); F04B 49/06 (2013.01); F15B 13/06 (2013.01); F15B 2211/20515 (2013.01)] 11 Claims
OG exemplary drawing
 
1. An aircraft, comprising:
a hydraulic system,
at least one component,
a hydraulic power generation apparatus for hydraulically powering the at least one component, the hydraulic system of the aircraft, comprising:
a first electrical power source and a first electrically driven motor pump (MPU1) electrically powered by the first electrical power source,
a second electrical power source and a second electrically driven motor pump (MPU2) electrically powered by the second electrical power source,
a hydraulic power generation control which controls a supply of electrical energy from the first and second electrical power sources to the first and second motor pumps (MPU1, MPU2),
wherein the hydraulic power generation control is configured to determine an actual available electrical power (APA, APB) of each of the first and second electrical power sources and to set a load factor (UPA, UPB) of each motor pump (MPU1, MPU2) in order to share a load to generate hydraulic power demanded from the at least one component between the first and second motor pumps (MPU1, MPU2),
wherein each load factor is set depending from the actual available electrical power (APA, APB), and
wherein the hydraulic power generation control is integrated with the aircraft hydraulic system, the aircraft hydraulic power generation apparatus is incorporated into an aircraft, and the aircraft hydraulic power generation apparatus supplies hydraulic power to at least one hydraulic actuator for driving movement of the at least one aircraft component.
 
7. A method of operating a hydraulic system of an aircraft, the hydraulic system comprising:
providing at least one aircraft component,
providing a hydraulic power generation apparatus for hydraulically powering the at least one aircraft component,
a first electrical power source (A) and a first electrically driven motor pump (MPU1) electrically powered by the first electrical power source (A),
a second electrical power source (B) and a second electrically driven motor pump (MPU2) electrically powered by the second electrical power source (B), and
at least one component to be powered hydraulically, the method comprising the steps:
a) determining an actual available electrical power (APA, APB) of each of the first and second electrical power sources and
b) setting a load factor (UPA, UPB) of each motor pump (MPU1, MPU2) in order to share a load to generate hydraulic power demanded from the at least one consumer between the first and second motor pumps (MPU1, MPU2), wherein each load factor (UPA, UPB) is set depending from the actual available electrical power (APA, APB),
wherein a hydraulic power generation control is integrated with the aircraft hydraulic system, the aircraft hydraulic power generation apparatus is incorporated into the aircraft, and the aircraft hydraulic power generation apparatus supplies hydraulic power to at least one hydraulic actuator for driving movement of the at least one aircraft component.