Method and apparatus for generating hydraulic power in an aircraft

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.