Patent ID: 6206329
Filing Date: 2001-03-27
Classification: B64C,G05D,Y02T

Abstract:
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.