A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.

A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.

A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.

A thrust reverser for an aircraft propulsion assembly, this reverser including a lower door and an upper door defining, in thrust reversal configuration, a deflection opening, through which a portion of the fluid not serving to produce the thrust reversal of the aircraft can exit the reverser downstream. The downstream edge of the lower door is offset towards the rear with respect to the downstream edge of the upper door so as to orient the fluid flow passing through the deflection opening vertically upwards. When the propulsion assembly is mounted at the rear portion of the fuselage of the aircraft, this makes it possible in particular to improve the supply of the control surface of the aircraft in the landing phase, in particular in crosswind conditions.

A thrust unit for a propulsion device includes a thrust engine, arranged to provide a thrust force oriented in a direction so as to provide substantially vertical take-off and landing capability, and a deflector assembly comprising a pair of deflecting elements arranged to selectively divert the ejected fluid and movably mounted in the fluid outlet path. In order to reduce the bulk of the thrust unit and improve reliability and responsiveness, the invention relates more particularly to the positioning of the deflecting elements opposite the ejected fluid.

A thrust unit for a propulsion device includes a thrust engine, arranged to provide a thrust force oriented in a direction so as to provide substantially vertical take-off and landing capability, and a deflector assembly comprising a pair of deflecting elements arranged to selectively divert the ejected fluid and movably mounted in the fluid outlet path. In order to reduce the bulk of the thrust unit and improve reliability and responsiveness, the invention relates more particularly to the positioning of the deflecting elements opposite the ejected fluid.

A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.

A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.

A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.

A thrust reverser door includes a backskin including an interior surface and an exterior loft surface. The thrust reverser door further includes a cover plate including a cover plate body having a first side and a second side opposite the first side. The thrust reverser door further includes a grid structure mounted to the second side of the cover plate body and the interior surface of the backskin.