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Preliminary investigation of use of flexible folding wing tips for static and dynamic load alleviation

机译：使用柔性折叠翼尖减轻静态和动态载荷的初步研究

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摘要

A recent consideration in aircraft design is the use of folding wing-tips with the aim of enabling higher aspect ratio aircraft with less induced drag while also meeting airport gate limitations. This study investigates the effect of exploiting folding wing-tips in flight as a device to reduce both static and dynamic loads. A representative civil jet aircraft aeroelastic model was used to explore the effect of introducing a wing-tip device, connected to the wings with an elastic hinge, on the load behaviour. For the dynamic cases, vertical discrete gusts and continuous turbulence were considered. The effects of hinge orientation, stiffitess, damping and wing-tip weight on the static and dynamic response were investigated. It was found that significant reductions in both the static and dynamic loads were possible. For the case considered, a 25% increase in span using folding wing-tips resulted in almost no increase in loads.
机译：飞机设计中最近的一项考虑是使用折叠式翼梢，目的是使高长宽比的飞机具有较小的诱导阻力，同时还满足机场登机门的限制。这项研究调查了在飞行中利用折叠式翼梢作为减少静态和动态载荷的装置的效果。使用代表性的民航飞机气动弹性模型来研究引入采用弹性铰链连接至机翼的翼尖装置对载荷行为的影响。对于动态情况，考虑了垂直离散阵风和连续湍流。研究了铰链方向，刚度，阻尼和翼尖重量对静态和动态响应的影响。发现可以显着降低静态和动态负载。对于所考虑的情况，使用折叠式翼梢将翼展增加25％，几乎不会增加载荷。

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