Flight control system comprising a hydraulic servo actuator
AssigneeLiebherr-Aerospace Lindenberg GmbH
InventorsTobias Roeben, Thomas Sauterleute, Anton Gaile
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Abstract
The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.
Claims11
A control system of an aircraft, wherein the system includes a control unit that is configured to generate a control current in response to a control signal, and wherein the system furthermore includes a hydraulic servo actuator for translating the control current into a movement of a control surface of the aircraft, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and comprises a power stage in which a valve slide is moved in response to the control pressure in order to adjust a throughflow direction and a throughflow cross-section of the valve,
- wherein
- the control unit is arranged on the aircraft decentrally and at a distance from a central flight control computer, and that the servo valve includes an electric feedback.
Dependencies are inferred from the claim text.