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Unsteady aerodynamics of adaptive elasto-flexible membrane wing

自适应弹性柔性膜翼的非定常空气动力学

基本信息

批准号：
392164975
负责人：
Professor Dr.-Ing. Christian Breitsamter
金额：
--
依托单位：
Lehrstuhl für Aerodynamik und Strömungsmechanik
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2018
资助国家：
德国
起止时间：
2017-12-31 至 2021-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/392164975?language=en
关键词：
Unsteady aerodynamics adaptive elasto flexible

项目摘要

Revolutionary concepts for unmanned aerial vehicles are aimed at mission scenarios that include both proportions of efficient loiter and endurance flight and high maneuverability flight. Such scenarios require aircraft which can optimally adapt their aerodynamic properties to the respective application conditions. This project is therefore concerned with new, technically feasible solutions for such versatile aircraft, based on an adaptive flying wing configuration with an adjustable aero-elastic flexible wing. Membrane wing configurations provide the possibilities to continuously alter one or more geometric parameters such as sweep, planform or airfoil and offers performance improvement potential for complex mission profiles. However, the inherent flexibility associated with the membrane creates strong coupling between unsteady aerodynamic loads and the airframe structural response giving rise to highly coupled, multidisciplinary physics. This nonlinear Fluid-Structure-Interaction causes aeroelastic instabilities which can be investigated using sophisticated experimental tools with good accuracy. This proposed research effort is aimed at such investigations which would analyze the effects of design variables involved and consequently would result in determination of aerodynamic and structural properties and configurations to achieve optimal flight conditions by various morphing states. The considered wind tunnel model consists of a beam structure with joints for varying aspect ratio, sweep and local incidence and a flexible lifting surface. Due to the anisotropic membrane design, the deformation of the wing under aerodynamic loads leads to passive flow control with respect to the airfoil shape. Up to now, a first understanding of these mechanisms and the related aerodynamic properties was gained by means of previous wind tunnel experiments and complementary numerical simulations. The current project is now aimed to link the aerodynamic characteristics to specific aerodynamic design variables and to exploit the concept with respect to overall unsteady aerodynamic problems resulting from stall behavior and gust impact. The basic concept of the massive form adaption as well as the use of a flexible lifting surface and its technical implementation combines fundamentally new approaches in the sense of aircraft aerodynamics.

无人驾驶飞行器的革命性概念是针对包括高效游荡和耐力飞行以及高机动性飞行的任务场景。这样的场景要求飞机能够根据各自的应用条件最佳地调整其空气动力学特性。因此，该项目关注的是这种多功能飞机的新的、技术上可行的解决方案，该方案基于一种带有可调节气动弹性柔性机翼的自适应飞翼配置。膜翼结构提供了连续改变一个或多个几何参数的可能性，如后掠翼、平面翼或翼型，并为复杂的任务剖面提供了性能改进的潜力。然而，与薄膜相关的固有灵活性在非定常气动载荷和机身结构响应之间产生了强烈的耦合，从而导致了高度耦合的多学科物理学。这种流体-结构-结构的非线性相互作用导致了气动弹性不稳定，这可以用复杂的实验工具来研究，而且精度很高。这项拟议的研究工作旨在进行这样的调查，分析所涉及的设计变量的影响，从而确定气动和结构特性以及构型，以通过各种变形状态来实现最佳飞行条件。所考虑的风洞模型由一个梁结构和一个弹性升力面组成，梁结构具有不同的展弦比、后掠角和局部入射。由于各向异性的薄膜设计，机翼在气动载荷作用下的变形导致了相对于翼型形状的被动流动控制。到目前为止，通过风洞实验和补充的数值模拟，对这些机理和相关的气动特性有了初步的了解。目前的项目旨在将气动特性与特定的气动设计变量联系起来，并利用这一概念来研究由失速行为和阵风影响引起的整体非定常气动问题。大质量外形适应的基本概念以及灵活升力面的使用及其技术实现从根本上结合了飞机空气动力学意义上的新方法。