Patent ID: 6241182
Filing Date: 2001-06-05
Classification: B64C

Abstract:
A system for controlling an aerodynamic surface (1) of an aircraft comprising a deliberate-actuation member (6) available to a pilot and a hydraulic servocontrol (2, 5) controlled by said deliberate-actuation member (6), which additionally comprises:an electric machine (8) which can operate either as a motor or as a generator, the output of which is connected mechanically to said aerodynamic surface (1);an electrical power supply (11), which can power said electric machine (8) under the dependency of said deliberate-actuation member (6);a resistive load (15) into which said electric machine (8) can output;a switching device (14, 16) intended to electrically connect said electric machine (8) either to said electrical power supply (11) or to said resistive load (15);a device (18, 19) for controlling the supply of hydraulic fluid to said servocontrol (2, 5); anda logic device (17, 17A, 17B, 17C) receiving information about the operating status of said electrical power supply (11) and of said hydraulic servocontrol (2, 5) and controlling the status of said switching device (14, 16) and of said device (18, 19) for controlling the hydraulic supply.