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1. (WO2019041004) RETRACTABLE LEADING EDGE WING SLATS HAVING AUTONOMOUSLY CURVABLE AIRFLOW SHIELD FOR NOISE-ABATEMENT
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WHAT IS CLAIMED IS:

1. A leading edge wing slat having upper and lower surfaces with upper and lower trailing edges, respectively, and a noise-abatement airflow shield integral with the lower trailing edge of the slat, wherein the shield is reciprocally autonomously curvable from a substantially planar configuration when the slat is in a retracted position thereof and into a convexly curved configuration when the slat is in a deployed position thereof.

2. The leading edge wing slat according to claim 1, wherein the shield comprises a shape memory material which exhibits a spring-biasing property to allow the shield to assume the convexly curved configuration when the slat is in the deployed position yet return to the substantially planar configuration when the slat is moved into the retracted position thereof.

3. The leading edge wing slat according to claim 2, wherein the shield further comprises at least one guide element which is fixed to and extends outwardly from a terminal end of the shield.

4. The leading edge wing slat according to claim 1 , wherein the shield comprises a sheet of shape-memory material to thereby induce convex curvature of the shield in response to application of an external stimulus when the slat is moved into the deployed condition thereof.

5. The leading edge wing slat according to claim 4, wherein the sheet of shape memory material is embedded in a layer of elastomeric material.

6. The leading edge wing slat according to claim 1 , wherein the shield comprises a band of shape-memory material fixed to an inner surface of the shield to thereby induce convex curvature of the shield in response to application of an external stimulus when the slat is moved into the deployed condition thereof.

7. An aircraft which comprises the leading edge wing slat according to claim 1.