Testing of a Hinged Wingtip Device for Gust Loads Alleviation
Testing of a Hinged Wingtip Device for Gust Loads Alleviation
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DOI：
10.2514/1.c034811
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发表时间：
2018-09-01
影响因子：
2.2
通讯作者：
Wilson, Thomas
中科院分区：
文献类型：
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作者：
Cheung, Ronald C. M.;Rezgui, Djamel;Wilson, Thomas
最近的飞机设计已经考虑了更高的展弦比机翼，以减少诱导阻力，提高燃油效率;然而，为了保持符合机场登机口的要求，折叠翼尖已经被引入作为增加翼展的解决方案。最近的数值研究表明，折叠翼尖方案可以与弹簧装置结合，以提供飞行中额外的阵风载荷减缓能力。在这项工作中，一系列低速定常和动态风洞试验进行了使用这样的概念的原型。有人发现，折叠铰链轴线的非零相对角度的折叠翼尖流向方向可以提供阵风载荷缓解。载荷缓解水平随铰链弹簧刚度和提升条件而变化，最佳性能可使峰值载荷降低56%。
Recent aircraft designs have considered higher-aspect-ratio wings to reduce induced drag for improved fuel efficiency; however, to remain compliant with airport gate requirements, folding wingtips have been introduced as a solution to the increased wingspan. Recent numerical studies suggest that a folding wingtip solution may be incorporated with spring devices to provide an additional gust loads alleviation ability in flight as well. In this work, a series of low-speed steady and dynamic wind tunnel tests was conducted using a prototype of such a concept. It was found that a folding wingtip with a nonzero relative angle of the folding hinge axis to the streamwise direction could provide gust loads alleviation. The level of load alleviation varied with hinge spring stiffness and lifting condition, with the best performance achieving a 56% reduction in peak loading.