MOBILE AIRFOIL DEVICE FOR AN AIRCRAFT WING
The invention concerns a mobile airfoil device that can locally modify the lift of an aircraft wing, including an upper panel and a lower panel and at least one actuator per panel in order to move the panels independently of one another between a first position, called rest, in which the outer surface of each of the panels forms a continuous surface with the upper surface and the lower surface of the wing, respectively, and a second position in which one of the two panels is deployed to form an angle with the corresponding surface of the wing, the actuators being positioned between the upper and lower panels in a recess of the wing.
1 . A mobile airfoil device ( 1 ) that can locally modify the lift of an aircraft wing, characterized in that said device comprises an upper panel ( 8 ) and a lower panel ( 9 ), and at least one actuator ( 19 , 20 ) per panel in order to move said panels independently from one another between a first position, called rest, in which the outer surface ( 11 , 12 ) of each of said panels ( 8 , 9 ) forms a continuous surface with upper surface ( 2 ) and lower surface ( 3 ), respectively, of the wing, and a second position in which one of the two panels is deployed to form an angle with the corresponding surface of the wing, said actuators ( 19 , 20 ) being positioned between said upper and lower panels ( 8 , 9 ) in a recess of the wing.
2 . The device according to claim 1 , further characterized in that said recess designed to receive said actuators ( 19 , 20 ) is a recess ( 35 ) enclosed by said upper panel ( 8 ) and lower panel ( 9 ) of said device ( 1 ).
3 . The device according to claim 2 , further characterized in that each panel ( 8 , 9 ) comprises a rotation axis ( 13 , 14 ) at one end, connecting said panel via a panel fastening support ( 4 ) to a first structural element of the wing, and at its other opposite end, at least one attachment point ( 15 , 16 ) in order to connect said panel to one end of said at least one corresponding actuator ( 19 , 20 ).
4 . The device according to claim 3 , further characterized in that the other end of said at least one actuator ( 19 , 20 ) is fastened via an actuator fastening support ( 5 ) to a second structural element of the wing.
5 . The device according to claim 3 , further characterized in that said first structural element and said second structural element of the wing are front spar ( 7 ) and rear spar ( 6 ) of the wing, respectively.
6 . The device according to claim 1 , further characterized in that said recess designed to receive said actuators ( 19 , 20 ) is a recess ( 36 ) delimited by rear spar ( 6 ) of the wing and upper surface ( 2 ) and lower surface ( 3 ) of the wing, said recess being situated on the trailing edge of the wing.
7 . The device according to claim 6 , further characterized in that said wing has at least one airtight box ( 21 ) delimited by front spar ( 7 ) and rear spar ( 6 ), enclosed by upper surface ( 2 ) and lower surface ( 3 ) of the wing, said box being contiguous with said recess ( 36 ).
8 . The device according to claim 6 , further characterized in that the outer upper wall and the outer lower wall of said box ( 21 ) each have an indentation ( 17 ) of dimensions suited to receive said corresponding panel ( 8 , 9 ).
9 . The device according to claim 6 , further characterized in that one end of panel ( 8 , 9 ) is fastened via a panel fastening support ( 37 ) to lateral edge ( 18 ) generated by said indentation ( 17 ).
10 . The device according to claim 1 , further characterized in that said at least one actuator ( 19 , 20 ) is placed obliquely relative to corresponding panel ( 8 , 9 ), so as to create a lever arm between rotation axis ( 13 , 14 ) and attachment point ( 15 , 16 ).
11 . The device according to claim 1 , further characterized in that said device has an abutment ( 38 ) designed to hold said panels ( 8 , 9 ) in the rest position.
12 . The device according to claim 1 , further characterized in that said panels ( 8 , 9 ) are of composite or metal materials or a combination of the two materials.
13 . The device according to claim 1 , further characterized in that the outer surfaces of said upper panel ( 8 ) and lower panel ( 9 ) are designed so as to be able to create an aerodynamic continuity with the wing when the panels are not deployed.
14 . The device according to claim 1 , further characterized in that the actuators are hydraulic, pneumatic or electrical actuators, or a combination of said actuators.
15 . An aircraft having a mobile airfoil device according to claim 1 .
16 . The aircraft according to claim 15 , further characterized in that said aircraft comprises a control means situated at the level of the cockpit, said control means being connected to mobile airfoil device ( 1 ) by a logic unit so as to be able to control the movements of said panels ( 8 , 9 ).