US 6,981,676 B2
Method and spoiler system for ensuring the aerodynamic continuity of the upper surface of an aircraft
Jérôme Milliere, Leguevin (France)
Assigned to Airbus France, Toulouse (France)
Filed on Sep. 21, 2004, as Appl. No. 10/945,101.
Claims priority of application No. 03 11076 (FR), filed on Sep. 22, 2003.
Prior Publication US 2005/0061922 A1, Mar. 24, 2005
Int. Cl. B64C 9/14 (2006.01)
U.S. Cl. 244—213 9 Claims
OG exemplary drawing
 
1. A method for ensuring aerodynamic continuity of an upper surface of an aircraft wing between a spoiler in a spoiler retracted position and a trailing edge flap in at least one flag deployed position,
said spoiler being able to assume either (i) said spoiler retracted position in which said spoiler is housed in said upper surface thereby ensuring the aerodynamic continuity of said upper surface or (ii) at least one spoiler deployed position in which said spoiler protrudes with respect to said upper surface by being inclined with respect to said upper surface,
said trailing edge flag being able to assume either (i) a flap retracted position in which said trailing edge flag is in aerodynamic continuity with said upper surface and with a lower surface of said wing of which said trailing edge flag forms a part of the trailing edge or (ii) said at least one flag deployed position, deflected with respect to retracted position, causing a protrusion on the upper surface and a hollow on the lower surface of said wing;
the disposition of said spoiler and of said trailing edge flap being such that the trailing edge of said spoiler in the spoiler retracted position bears on said trailing edge flap in the flap retracted position, wherein, when said trailing edge flap is in said at least one flag deployed position whilst said spoiler is in the spoiler retracted position, the length of said spoiler is increased in a direction parallel with its chord in such a way that the trailing edge of said spoiler advances toward said trailing edge flap and comes to bear on the upper surface of the latter, in order to compensate for the break in aerodynamic continuity caused by the deployment of said trailing edge flap.