Abstract: The present disclosure relates to a valve, preferably a continuous valve comprising a spool and a spool sleeve, wherein the spool comprises a control surface and the spool sleeve comprises an opening, wherein the valve is configured in such a way that the control surface can cover the opening, wherein the spool can be positioned such that the control surface at least partially does not cover the opening, wherein the spool sleeve comprises a further opening, wherein the control surface can cover the further opening, wherein the spool can be positioned such that the control surface at least partially does not cover each of the opening and the further opening.

Abstract: The present disclosure relates to a valve, preferably a continuous valve or a proportional valve, wherein the valve comprises means configured to control and/or regulate a pressure and/or flow of a fluid, wherein the means are further configured to effect at least one further function or to participate in the function.

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.

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.