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UAV WING DESIGN - A NEW CHALLENGE

机译：无人机机翼设计-新挑战

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Advanced airfoil design concepts and modern wing design methodology allow development of mission-tailored, customized wing for any new aerodynamic configuration. This is especially relevant for UAV wing design, where variety of mission specifications, multi-point design requirements and imposed non-aerodynamic constraints make it unpractical the use of existing wings in configuration evaluation process. The development efforts on UAV wing design should concentrate on the radical improvement of aircraft performance, provide improved pavload carriage capabilities, ensure flight safety of air vehicles, their maneuverability, capability to perform in unfavorable weather conditions and comply with structural and internal volume constraints. IAI initiated development of in-house capabilities on UAV wing design in mid 80 's, recognizing the principal differences between requirements for UAV operation and known types of air vehicles such as sailplanes and general aviation aircrafts. It was acknowledged, that for most cases, design of a new UAV wing is a practically unavoidable choice, that should be supported by the adequate engineering capabilities. The build-up of technological infrastructures at IAI included adoption of CFD tools, promotion of advanced design concepts and WT testing of airfoils and complete configurations. The first designs targeted subsonic, long endurance UAV. concentrating on development of thick, high-lift NLF sections. This was followed by variety of subsonic and transonic designs, including wings development for high altitude flight, application of swept NLF wing technology to design of subsonic/transonic wings, promotion of the concept of hybrid transonic/subsonic airfoils, design of transonic unswept NLF wings, development in the field of low Reynolds number aerodynamics and evaluation of Mini/Micro UA V wings. IAI experience on UAV wing design is outlined in this paper by presenting a number of specialized designs and discussing the rationale of their development. This is followed by definition of future development directions that might be considered for continuation efforts on development of UAV wings.
机译：先进的机翼设计概念和现代机翼设计方法，可以针对任何新的空气动力学配置开发按任务量身定制的机翼。这对无人机机翼设计尤为重要，因为其各种任务规格，多点设计要求和强加的非空气动力约束使得在构型评估过程中使用现有机翼不切实际。无人机机翼设计的开发工作应集中于飞机性能的根本改善，提供有效载荷载运能力，确保航空器的飞行安全，机动性，在不利的天气条件下运行的能力以及遵守结构和内部体积限制。 IAI在80年代中期开始开发无人机翼型设计的内部能力，因为认识到无人机操作要求与已知类型的飞行器（例如，水手飞机和通用飞机）之间的主要区别。公认的是，在大多数情况下，设计新的无人机机翼实际上是不可避免的选择，应由适当的工程能力予以支持。 IAI的技术基础设施建设包括采用CFD工具，推广高级设计概念以及机翼和完整配置的WT测试。第一批设计针对亚音速，长寿命无人机。专注于开发厚的高升程NLF型材。其次是各种亚音速和跨音速设计，包括用于高空飞行的机翼开发，后掠NLF机翼技术在亚音速/跨音速机翼的设计中的应用，推广跨音速/亚音速机翼的概念，跨音速未扫频NLF机翼的设计，低雷诺数空气动力学领域的发展以及Mini / Micro UA V机翼的评估。本文通过介绍一些专门的设计并讨论其发展的原理，概述了IAI在无人机机翼设计方面的经验。其次是定义未来的发展方向，可以考虑继续为无人机机翼的开发做出努力。

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