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Investigation of a sliding alula for control augmentation of lifting surfaces at high angles of attack

机译：用于控制迎角较大的提升面的滑动滑轨的研究

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摘要

The ability to generate useful control forces on lifting surfaces at high angles of attack is particularly challenging due to boundary layer separation. A miniature collection of feathers on birds termed the alula, appears an intriguing solution to this control problem. Using surface-oil visualizations and direct force and moment measurements, we experimentally investigate the aerodynamics of a model alula(e) affixed to a thin, flat-plate, AR = 1.5 rectangular wing. A critical parameter of the deflected alula considered, is not its orientation relative to the incoming flow, but rather its spanwise distance from the wing tip to which it is oriented. Control forces (lift and rolling moment) are proportional to this distance over a wide range of angles of attack. When centered on the stalled wing, a single alula generates a rolling moment of magnitude comparable to that produced by a conventional trailing-edge flap aileron in an attached-flow condition. Importantly, the wetted area of the alula is one order of magnitude less than the reference flap aileron. The uncharacteristically large control force of the alula stems from its ability to induce and stabilize a vortex that sweeps outboard across the span of the wing towards the wing tip. Changing the distance of the alula from the wing tip, varies the length of this 'sweeping vortex' and its associated interactions with the wing. A novel high-angle-of-attack control solution is proposed, the sliding alula, which entails coordinated shifting of two alulae to manipulate the length and asymmetry of stabilized 'sweeping vortices' on stalled wings. Results regarding control authority in cross-flow and the gust mitigation potential of the sliding alula are also discussed. Published by Elsevier Masson SAS.
机译：由于边界层的分离，在高攻角的提升面上产生有用控制力的能力尤其具有挑战性。鸟类的微型羽毛被称为alula，似乎是解决这种控制问题的一种有趣方法。使用表面油的可视化效果以及直接的力和力矩测量，我们通过实验研究了固定在薄的平板AR = 1.5矩形机翼上的模型alula（e）的空气动力学特性。所考虑的偏导角的关键参数不是其相对于进入流的方向，而是其距翼向的翼展方向的距离。在很大的迎角范围内，控制力（升力和横滚力矩）与该距离成正比。当以失速机翼为中心时，单个桨叶产生的侧倾力矩可与常规后缘襟翼副翼在附着气流条件下产生的力矩相媲美。重要的是，先知的湿润区域比参考襟翼副翼小一个数量级。旋翼的异常大的控制力源于其诱发和稳定涡旋的能力，该旋涡从机翼的整个翼展向机翼尖端扫出舷外。改变距翼尖距离的距离，会改变这种“掠过涡旋”的长度以及与翼相关的相互作用。提出了一种新颖的高攻角控制解决方案，即滑动式算盘，它需要两个算子的协调移动来控制失速机翼上稳定的“扫掠涡旋”的长度和不对称性。还讨论了关于横流控制权和滑动式防风措施的结果。由Elsevier Masson SAS发布。

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  • 来源
    《Aerospace science and technology》 |2019年第4期|73-88|共16页
  • 作者

    Linehan Thomas; Mohseni Kamran;

  • 作者单位

    Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA;

    Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA|Univ Florida, Dept Elect & Comp Engn, Gainesville, FL 32611 USA;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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