Patent ID: 9242720
Filing Date: 2016-01-26
CPC Classification: B64C,Y02T

Claim Text:
1. A wing structure for aircraft, comprising: a primary wing structure defining a leading edge, a trailing edge, and upper and lower surfaces extending between the leading and trailing edges to define a first airfoil element; a leading-edge slat movably interconnected with the primary wing structure for movement between a retracted position wherein the leading edge slat is positioned adjacent the leading edge of the primary wing structure to reduce aerodynamic drag, and a deployed position wherein the leading-edge slat is shifted relative to the retracted position to thereby provide a multi-element airfoil, and wherein the leading-edge slat includes a leading surface whereby, in use, airflow splits and flows over an upper surface of the leading-edge slat that extends rearwardly from the leading surface to a trailing edge, and a lower surface extending rearwardly from the leading surface to a cusp; a slat cove filler comprising a flexible material connected to the trailing edge and the cusp, wherein the slat cove filler defines a first shape when the leading edge slat is in its deployed position, and a second shape when the leading edge slat is in its retracted position, and wherein at least a portion of the slat cove filler comprises a superelastic shape memory alloy that transforms from an austenitic phase to a martensite phase when the slat cove filler changes from the first shape to the second shape; and a torsion spring that rotatably biases the slat cove filler about a hinge and causes the slat cove filler to change from the second shape to the first shape as the slat moves from its retracted position to its deployed position; wherein the slat cove filler is connected to the cusp of the slat by the hinge.