The use of actuated flexible plates for adaptive shock control bumps
The use of actuated flexible plates for adaptive shock control bumps
复制标题
使用驱动柔性板实现自适应冲击控制凸块
DOI：
10.2514/6.2015-1241
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发表时间：
2015
影响因子：
3.3
通讯作者：
M. Santer
中科院分区：
文献类型：
--
作者：
E. Jinks;P. Bruce;M. Santer
自适应激波控制凸块（SCB）的目的是保持静态SCV的性能并改善由于流场不稳定和飞机巡航条件变化引起的激波位置变化所引起的非设计性能。自适应SCB需要柔性变形和刚度承受复杂的压力场，是目前在跨音速飞机机翼上表面。本研究使用准定常气动结构求解器来设计自适应SCB。柔性板和驱动板都已在马赫数1.4的泄放式风洞中进行了试验。使用高速纹影成像在两个板（t=0.4mm）上捕获了激波结构。实验结果表明，柔性板和驱动板对激波都有稳定作用，使非定常激波的振幅分别从30 mm减小到20 mm和10 mm。此外，致动板使休克的平均流向位置变化高达26毫米的致动器位移仅为3毫米。休克保持特性归因于如何在表面曲率的变化所造成的空腔压力和致动影响的外部流动结构和休克结构。柔性板下的空腔压力被证明是一个重要的设计变量，板的几何形状从一个凹陷移动到一个突起，只有0.1巴的变化。
Adaptive shock control bumps (SCB) aim to retain the performance of static SCV and improve off-design performance caused by variations in shock position due to flowfield unsteadiness and changes in aircraft cruise conditions. An adaptive SCB requires the flexibility to deform and the stiffness to withstand the complex pressure field that is present on the upper surface of a transonic aircraft wing. This study uses a quasi-steady aerostructural solver to design adaptive SCB. Both flexible and actuated plates have been tested in a Mach 1.4 blowdown wind tunnel. The shock structure has been captured over both plates (t=0.4mm) using high speed Schlieren Imaging. Experimental results show that the flexible and actuated plates both have a stabilising effect on the shock, reducing the amplitude of unsteady shock motion from 30 mm to 20 mm and 10 mm respectively. In addition, the actuated plate enabled the shock’s mean stream wise position to be varied by up to 26 mm for an actuator displacement of just 3 mm. The shock holding characteristics were attributed to how changes in surface curvature caused by the cavity pressure and actuation affected the external flow structure and shock structure. The cavity pressure beneath a flexible plate is shown to be a significant design variable with the plate geometry moving from a depression to a protrusion with just 0.1 bar variation.