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Lift-to-drag ratio and laminar flow control of a morphing laminar wing in a wind tunnel

机译：风洞中变形层流机翼的升阻比和层流控制

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A new hardware-in-the-loop control strategy to enhance the aerodynamic performance of a two-dimensional morphing laminar wing prototype was developed and tested. The testing was performed in a wind tunnel under cruise flight flow conditions: Mach number ranging from 0.2 to 0.3 and angle of attack from - 1° to 0.5°. For each set of flow conditions, the shape of the upper surface of the wing was modified using two independent shape memory alloy actuators. The wing shape was morphed in two sequential steps. The initial morphed shape was controlled using open-loop architecture and the results of an anterior aero-structural numerical optimization study. The final morphed shape was closed-loop controlled using either the wind tunnel balance or an infrared camera as hardware-in-the-loop to give an instantaneous lift-to-drag ratio (L/D) or a laminar flow extension (x_(tr)/c) over the upper surface of the prototype. In respect to the aerodynamic performance of the unactuated wing profile, the L/D gain varies from 10.6 to 15% for the closed-loop control strategy compared to 10.0 to 13.7% for the open-loop control strategy. Laminar flow extension gains, Δx_(tr)/c, measured by infrared camera, were situated in the 29-33% range for both control strategies. However, the results obtained showed that the closed-loop controller could be hindered by the noise of the hardware-in-the-loop signal.
机译：开发并测试了一种新的硬件在环控制策略，以增强二维变形层流机翼原型的空气动力学性能。测试是在风洞中的巡航飞行流动条件下进行的：马赫数为0.2到0.3，迎角为-1°到0.5°。对于每组流动条件，使用两个独立的形状记忆合金致动器来修改机翼上表面的形状。机翼形状在两个连续步骤中变形。初始变形形状使用开环结构进行控制，并且通过前部航空结构数值优化研究获得结果。使用风洞天平或红外摄像头作为硬件在环，对最终变形的形状进行闭环控制，以提供瞬时的升阻比（L / D）或层流扩展（x_（ tr）/ c）在原型的上表面上。关于未驱动机翼轮廓的空气动力学性能，闭环控制策略的L / D增益从10.6％到15％不等，而开环控制策略的L / D增益从10.0％到13.7％。对于两种控制策略，通过红外热像仪测量的层流扩展增益Δx_（tr）/ c位于29-33％的范围内。但是，获得的结果表明，闭环控制器可能会受到硬件在环信号的噪声的阻碍。

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