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首页> 外文会议>Conference on industrial and commercial applications of smart structures technologies; 20090309-10; San Diego, CA(US) >Design and Aerodynamic Characteristics of a Span Morphing Wing
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Design and Aerodynamic Characteristics of a Span Morphing Wing

机译：跨距变形翼的设计和空气动力特性

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Flight vehicles are often designed to function around a primary operating point such as an efficient cruise or a high maneuverability mode. Performance and efficiency deteriorate rapidly as the airplane moves towards other portions of the flight envelope. One solution to this quandary is to radically change the shape of the aircraft. This yields both improved efficiency and a larger flight envelope. This global shape change is an example of morphing aircraft . One concept of morphing is the span morphing wing in which the wingspan is varied to accommodate multiple flight regimes. This type of design allows for at least two discreet modes of the aircraft. The original configuration, in which the extensible portion of the wing is fully retracted, yields a high speed dash mode. Fully extending the wing provides the aircraft with a low speed mode tailored for fine tracking and loiter tasks. This paper discusses the design of a span morphing wing that permits a change in the aspect ratio while simultaneously supporting structural wing loads. The wing cross section is maintained by NACA 4412 rib sections . The span morphing wing was investigated in different configurations. The wing area and the aspect ratio of the span morphing wing increase as the wings pan increases. Computational aerodynamics are used to estimate the performance and dynamic characteristics of each wing shape of this span morphing wing as its wingspan is changed. Results show that in order to obtain the same lift, the conventional wing requires a larger angle of attach(AOA) than that of the span morphing wing.The lift of the span morphing wing increases as the wing span ,Mach number and AOA increases.
机译：飞行器通常被设计成在主要操作点附近起作用，例如有效的巡航或高机动性模式。随着飞机移向飞行包线的其他部分，性能和效率迅速下降。解决这一难题的一种方法是从根本上改变飞机的形状。这样既提高了效率，又扩大了飞行范围。这种整体形状变化是飞机变形的一个例子。变形的概念之一是翼展变形机翼，其中翼展变化以适应多种飞行状态。这种类型的设计至少允许飞机采用两种谨慎的模式。机翼的可伸展部分完全缩回的原始配置产生了高速冲刺模式。机翼完全伸展，为飞机提供了低速模式，适合精细跟踪和游荡任务。本文讨论了翼展变形机翼的设计，该翼型可以在改变长宽比的同时支持结构机翼的载荷。机翼的横截面由NACA 4412肋骨部分保持。研究了跨翼变形机翼的不同配置。随着翼展的增加，翼展变形翼的翼面积和长宽比也会增加。当改变翼展时，使用计算空气动力学来估计该翼展形变翼的每个翼形的性能和动力特性。结果表明，为了获得相同的升力，常规翼需要比翼展变形翼更大的附着角（AOA）。翼展变形翼的升力随着翼展，马赫数和AOA的增加而增加。

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