AIRCRAFT WING WITH AN ADAPTIVE SHOCK CONTROL BUMP

摘要

Provided is an aircraft wing (100) with an upper surface element (101) and a first actuator powered mechanism (102) for varying the shape of the upper surface element (101), wherein the surface element (101) is comprising: an upstream segment SEG 1 with a stiffness S 1 , a downstream segment SEG 2 with a stiffness S 2 , an interconnecting segment SEG 3 with a stiffness S 3 , the interconnecting segment SEG 3 is interconnecting a downstream edge of SEG 1 with an upstream edge of SEG 2 , wherein the interconnecting segment SEG 3 is extending along the whole downstream edge of SEG 1 and the whole upstream edge of SEG 2 , or at least along a major part of the downstream edge of SEG 1 and a major part of the upstream edge of SEG 2 , and the interconnecting segment SEG 3 exhibits a mechanical pretension causing a convex shape of the upper surface element with: S 3 S 1 , S 2 , a link element LNK, the link element LNK is interconnecting an upstream edge of SEG 1 with an upper surface (103) of the aircraft wing, and the first actuator powered mechanism (102) is interconnecting a contact C1 on a lower side of the upper surface element (101) with a contact C2 on an inner structure of the airfoil, wherein the first actuator powered mechanism (102) controls the shape of the upper surface element (101) by controlling the distance between C1 and C2.