Process and device for the control of the rudder of an aircraft
OwnerJean-Pierre Gautier, Jean-Marc Ortegainventors
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Abstract
A device for the control of a control surface of an aircraft has at least two actuators (110, 112, 114), each having at least one electric control input (111a, 113a, 115a). At least one of the actuators (115), called the mixed actuator, also has a mechanical control input (115b), and an electric control system for the actuators is able to occupy a state corresponding to a fault of an engine in which at least two of the actuators simultaneously operate the control surface and a state corresponding to an electric fault, in which the mixed actuator (115) operates the control surface from the mechanical control input.
Claims6
Device for control of an inclination or pitch control surface (116) of an aircraft, having at least two actuators (110, 112, 114), each actuator having at least one electric control input (111a, 113a, 115a), and an electric control system (127) for the actuators able to occupy a first state, the normal flight state, in which at least one of the actuators is controlled so as to actuate the control surface, characterized in that at least one of the actuators (114), referred to as the mixed actuator, also has a mechanical control input (115b), and in that the electric control system of the actuators is able to occupy a second state, the manoeuvre state, in which at least two of the actuators are controlled so as to simultaneously actuate the control surface (116), and a third state, called electric control failure state, in which the mixed actuator (114) is controlled from the mechanical control input in order to actuate the control surface.
Process for controlling a control system of an aircraft inclination or pitch control surface (116), the control system comprising at least two actuators (110) with an electric control input, whereof at least one of the actuators, referred to as the mixed actuator (114), also has a mechanical control input (115b), and the control system further comprising an electric control system (127) for the actuators, wherein, for actuating the control surface, at least one of the actuators is electrically controlled in a normal flight state, at least two actuators can be electrically and simultaneously controlled in a manoeuvre state, and the mixed actuator (114) is mechanically controlled in a breakdown state of the actuators electric control system (127).
Dependencies are inferred from the claim text.