Abstract:
The present disclosure relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a tranverse pivot in order to partially close off the air stream so as to guide it forwards, further including locks for locking the flaps in an intermediate opening position, between the closed position and the open position.
Abstract:
A tertiary locking assembly for a thrust reverser includes a tertiary lock, a primary control line associated with the tertiary lock, and a secondary control line. The primary control line includes a primary electromechanical valve and a primary power supply line connected to the primary electromechanical valve. In addition, the secondary control line has a secondary electromechanical control valve and a secondary power supply line connected to the secondary electromechanical control valve. In particular, the secondary control line is provided with at least one manually controlled switch.
Abstract:
An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.
Abstract:
A tertiary locking assembly for a thrust reverser includes a tertiary lock, a primary control line associated with the tertiary lock, and a secondary control line. The primary control line includes a primary electromechanical valve and a primary power supply line connected to the primary electromechanical valve. In addition, the secondary control line has a secondary electromechanical control valve and a secondary power supply line connected to the secondary electromechanical control valve. In particular, the secondary control line is provided with at least one manually controlled switch.
Abstract:
An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.