Patent ID: 9062627
Filing Date: 2015-06-23
Classification: F02K,F05D,Y02T

Abstract:
1. In a thrust reverser comprising at least one movable hood that can be moved between a deployed position in which said movable hood opens a passageway in a nacelle designed for a diverted flow and a retracted position in which said movable hood closes the passageway, said movable hood being actuated by at least one electromechanical actuator associated with at least one electric motor connected to a control interface that operates said motor according to a method comprising: actuating said movable hood fitted to the thrust reverser for a turbojet; determining a state of operation of the electric motor by testing its speed of rotation during the step of actuating the movable hood; disconnecting power to the electric motor if the electric motor does not operate for a certain time; and reactivating the electric motor after a rest period of the electric motor and repeating the preceding steps or permanently shutting down the power to the electric motor and its power electronics if the preceding steps have already been repeated a predefined number of times, in an aborted landing, in order to overcome the aerodynamic stresses, closing the movable hood after triggering the electric motor by operating the motor intermittently according to the preceding steps above until the aerodynamic stresses are reduced; and in an aborted takeoff, opening the movable hood after triggering the electric motor by operating the motor.