초록 ▼

A system for controlling the tab (6) of an aircraft control surface (3) having a pair of position sensors (12 and 15) that supply information regarding the turning of the control surface (3) and the position of a jack (13), respectively, on the basis of signals generated by the sensors (12 and 15) a

A system for controlling the tab (6) of an aircraft control surface (3) having a pair of position sensors (12 and 15) that supply information regarding the turning of the control surface (3) and the position of a jack (13), respectively, on the basis of signals generated by the sensors (12 and 15) as well as possibly on the basis of at least one parameter (p) originating from the aircraft, such as airspeed, positions of lift-augmenting devices, forces exerted by the pilot on a control, etc., and which formulates a command for the jack (13).

대표청구항 ▼

[ We claim:] [1.] A system for controlling a tab (6) of an aircraft, said tab (6) being articulated so that said tab (6) can rotate on a trailing edge side of an aerodynamic surface (3) of said aircraft, said aerodynamic surface (3) being mounted to rotate on a structure (5) of said aircraft, said a

[ We claim:] [1.] A system for controlling a tab (6) of an aircraft, said tab (6) being articulated so that said tab (6) can rotate on a trailing edge side of an aerodynamic surface (3) of said aircraft, said aerodynamic surface (3) being mounted to rotate on a structure (5) of said aircraft, said aircraft having a control device (1) adapted to be controlled by a pilot of said aircraft, said control device (1) being mechanically connected to said aerodynamic surface (3) so as to be capable of turning said aerodynamic surface (3), said aircraft having a mechanical linkage (10) that connects said tab (6) to said aircraft structure (5) so that for each angle through which said aerodynamic surface (3) is turned with respect to said aircraft structure (5) there corresponds, according to a determined relationship, a value of an angle through which said tab (6) is turned with respect to said aerodynamic surface (3), said system comprising:a first sensor (12) that detects an angle through which said aerodynamic surface (3) is turned with respect to said aircraft structure (5);a movable and controllable actuating member (13) connected to said aircraft structure (5), said actuating member being capable of acting on said mechanical linkage (10) to alter said determined relationship between said values of said angles through which said aerodynamic surface (3) and said tab (6) are turned;a second sensor (15) that detects the position of said actuating member (13); anda control device (16, 27) that receives information from said first and second sensors and, on the basis of said information, formulates a command for said actuating member (13).