Closed-Loop Control Validation of a Morphing Wing Using Wind Tunnel Tests

摘要

In this paper a rectangular finite aspect ratio wing, having a wing trailing edge airfoil reference airfoil crossnsection, was considered. The wing upper surface was made of a flexible composite material and instrumented withnKulite pressure sensors and two smart memory alloys actuators. Unsteady pressure signals were recorded andnvisualized in real time while the morphing wing was being deformed to reproduce various airfoil shapes byncontrolling the two actuators displacements. The controlling procedurewas performed using twomethodswhich arendescribed in the paper. Several wind-tunnel test runs were performed for various angles of attack and Reynoldsnnumbers in the 6 u0001 9 foot wind tunnel at the Institute for Aerospace Research at the National Research CouncilnCanada. TheMach number was varied from 0.2 to 0.3, the Reynolds numbers varied between 2.29 and 3:36 u0001 106n,nand the angle-of-attack range was within u00021 to 2 degrees. Wind-tunnel measurements are presented for airflownboundary layer transition detection using high sampling rate pressure sensors.