Propulsion system with downstream section having deformable shape-memory material and actuators extending in different consecutive angular sectors
The invention relates to a propulsion system ( 1, 1 ) for an aircraft, comprising a rotor ( 2 ) and a nacelle failing ( 3 ) that extends around said rotor in relation to an axis (X) and includes an upstream portion ( 10 ) forming an inlet section (BA) of the nacelle fairing ( 3 ) as well as a downstream portion ( 20 ), a downstream end ( 21 ) of which forms an outlet section (BF) of the nacelle fairing ( 3 ); and characterized in that the downstream portion ( 20 ) has a radially inner wall ( 20 a ) and a radially outer wall ( 20 b ), both of which are made of a deformable shape memory material, and in that the downstream end ( 21 ) includes pneumatic or hydraulic actuators ( 23, 23 ′) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.
1. A propulsion system for an aircraft, comprising:
at least one rotor and a nacelle fairing extending around said at least one rotor with respect to an axis of rotation of said rotor, the nacelle fairing comprising an upstream section forming an inlet cross-section of the nacelle fairing and a downstream section, a downstream end of which forms an outlet cross-section of the nacelle fairing; and
wherein the downstream section comprises a radially internal wall and a radially external wall made of a deformable shape-memory material and in that the downstream end forming the outlet cross-section comprises a plurality of pneumatic or hydraulic actuators, each actuator of the plurality of actuators being independently actuatable and extending in different consecutive angular sectors about said axis of rotation, and configured to deform in a direction which is radial with respect to the axis of rotation and which is angularly centered with respect to the angular sector over which each said actuator extends under a predetermined command pressure, and
wherein each actuator comprises a bladder in a general form of a toroidal segment of flexible material encased in a spiral spring.
2. The propulsion system according to claim 1 , wherein each actuator has a general shape of a toroidal segment, the actuators extending in different consecutive angular sectors about said axis of rotation so that a set of actuators of the plurality of actuators has a general torus shape.
3. The propulsion system according to claim 1 , wherein each actuator is made of radially stiffened elastic material including fibres.
4. The propulsion system of claim 1 , wherein each actuator is embedded at one end in a rigid support.
5. The propulsion system according to claim 1 , wherein each bladder comprises an inlet valve configured to receive the predetermined command pressure.
6. The propulsion system according to claim 5 , wherein said inlet valve is a solenoid valve.
7. The propulsion system according to claim 1 , wherein the plurality of actuators comprises at least two actuators having a general semi-toroidal shape.
8. The propulsion system according to claim 1 , further comprising stiffening bridges connecting the radially internal and radially external walls of the downstream section.
9. The propulsion system according to claim 1 , wherein the nacelle fairing further comprises an intermediate section connecting the upstream and downstream sections, and wherein the intermediate section is rigid and is connected by at least one mast to an engine of the propulsion system.