A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.

The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

A thrust reverser of a turbofan pod is provided that includes movable cowlings that retract relative to stationary front structure to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section connected to the movable cowlings by guiding means enabling movement controlled by actuators engaged with the front structure to apply an axial thrust. The actuators are directly connected to the secondary nozzle, and in that the thrust reverser comprises latches connected to the movable cowlings, having two positions providing, alternately, latching onto the front structure or latching onto the control of the secondary nozzle.

An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.