METHOD AND APPARATUS FOR GENERATING HYDRAULIC POWER IN AN AIRCRAFT

An apparatus and method for hydraulically powering at least one consumer of a hydraulic system of an aircraft is disclosed including 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...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	GÖESSING, Rolf, HAMM, Martin, HOFFMANN, Lars
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLUID-PRESSURE ACTUATORS FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS FLYING SUITS HEATING HYDRAULICS OR PNEUMATICS IN GENERAL LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An apparatus and method for hydraulically powering at least one consumer of a hydraulic system of an aircraft is disclosed including 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 (B), and 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). A method is disclosed for determining the 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 in order to share a load to generate hydraulic power demanded from the at least one consumer between the first and second motor pumps.