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首页> 外文期刊>Experimental Thermal and Fluid Science: International Journal of Experimental Heat Transfer, Thermodynamics, and Fluid Mechanics >Experimental investigation of side force control on cone-cylinder slender bodies with flexible micro balloon actuators
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Experimental investigation of side force control on cone-cylinder slender bodies with flexible micro balloon actuators

机译：带有柔性微球致动器的锥形圆柱细长体侧向力控制的实验研究

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Side forces on slender bodies of revolution at medium to high angles of attack (AOA > 30 degrees) has been known from a large number of investigations. Asymmetric vortex pairs over a slender body are believed to be the principle cause of the side forces. Under some flight conditions, this side force may be as large as the normal force acting on the slender body. In this paper, experimental results are presented for side force control on a cone-cylinder slender body by using microfabricated balloon actuators. The micro balloon actuators are made of polydimethylsiloxane (PDMS) elastomer by using micro molding techniques. They can be packaged on curve surfaces of a cone-cylinder slender body. As actuator is actuated, the micro balloon actuator inflates about 1.2 mm vertically, which is about 2.4% of the cylinder diameter D (=50 mm) of the cone-cylinder slender body. Micro balloon actuators are actuated at different roll angles of a cone-cylinder slender body. Aerodynamic force measurement results indicate the effects of micro balloon actuators vary at different actuation locations on the cone-cylinder slender body. The side forces can be significantly reduced if the actuators are actuated in the weak vortex side (the side corresponding to the asymmetric vortex which is far from the surface) and actuation angles are located at about 50-60 degrees (the actuation angle here is measured from stagnation line of the incidence plane toward weak vortex side direction). Significant changes are noticed from the surface pressure, as well as leeside vortex flow field, measurement. Micro balloon actuators change nose shapes of the slender body which decide adverse-pressure-gradient values and directly influence the origin of the separation lines and characteristics of the separated vortices over the leeside surface. (c) 2005 Elsevier Inc. All rights reserved.
机译：从大量研究中可以知道，在中等至高攻角（AOA> 30度）下，细长旋转体上的侧向力。细长体上的不对称涡流对被认为是产生侧向力的主要原因。在某些飞行条件下，此侧向力可能与作用在细长主体上的法向力一样大。在本文中，通过使用微型制造的球囊致动器，对锥形圆柱体细长体的侧向力控制提供了实验结果。微球致动器通过使用微成型技术由聚二甲基硅氧烷（PDMS）弹性体制成。它们可以包装在圆锥形圆柱体的弯曲表面上。当致动器被致动时，微型气囊致动器在垂直方向上膨胀约1.2mm，这是圆锥形细长体的圆筒直径D（= 50mm）的约2.4％。微型气球致动器以锥形圆柱体细长体的不同侧倾角致动。空气动力测量结果表明，微气球致动器的作用在锥形圆柱体上的不同致动位置上有所不同。如果在弱涡旋侧（与远离表面的非对称涡旋相对应的一侧）进行致动器致动，并且致动角位于大约50-60度（此处测量致动角，则可大大降低侧向力）从入射平面的停滞线向弱涡旋侧方向）。从表面压力以及背风涡流场的测量中可以看到明显的变化。微型气球致动器改变细长主体的鼻形，决定了负压梯度值，并直接影响分离线的起源和背风表面上分离涡流的特性。 （c）2005 Elsevier Inc.保留所有权利。

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