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Investigation of Aeroelastic Effects of a Circulation Controlled Wing

机译：循环控制机翼的气动弹性效应研究

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摘要

The aeroelastic behavior of the wing of a 100-passenger aircraft under investigation in the Coordinated Research Center SFB 880 is studied. A compressed air jet upstream of the high-lift devices called the Coand jet enables boundary layer control with delayed flow separation and consequently high lift. Aeroelastic instabilities caused by boundary layer control systems are critical to the aircraft performance. The understanding of cause and effect of these instabilities is of great importance. For analyses, a multilevel approach is pursued using full-scale three-dimensional models and reduced-order models. Both model types use fluid-structure interaction techniques. The full-scale models are used to generate a sized wing structure with realistic mass and stiffness distributions using computational fluid dynamics loads of cruise and landing configuration load cases. A reduced-order model is derived by modal reduction for computationally efficient investigations of multiple flight states. To study local aeroelastic effects and to develop three-dimensional corrections for the reduced-order model, full-scale three-dimensional coupled fluid-structure analyses are investigated. The results show that especially the dynamic behavior of wings with active circulation control may differ significantly from that of conventional wings due to the different aerodynamic behavior caused by the Coand jet.
机译：在SFB 880协调研究中心研究的100名乘客的飞机机翼的气动弹性行为得到了研究。在高升力设备上游的压缩空气射流称为Coand射流，可实现边界层控制，并延迟了气流分离，从而实现了高升力。边界层控制系统引起的气动弹性不稳定性对于飞机性能至关重要。了解这些不稳定性的因果关系非常重要。为了进行分析，使用全尺寸三维模型和降阶模型来追求多层次方法。两种模型都使用流体-结构相互作用技术。使用巡航和着陆配置载荷工况的计算流体动力学载荷，将全尺寸模型用于生成具有实际质量和刚度分布的大型机翼结构。降阶模型是通过模态归约导出的，可以有效地计算多种飞行状态。为了研究局部空气弹性效应并开发降阶模型的三维校正，对全尺寸三维耦合流体结构分析进行了研究。结果表明，由于Coand射流引起的空气动力学特性的不同，尤其是具有主动循环控制功能的机翼的动态性能可能与常规机翼显着不同。

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  • 来源
    《Journal of Aircraft》 |2016年第6期|1746-1756|共11页
  • 作者

    Sommerwerk Kay; Krukow Ian; Haupt Matthias C.; Dinkler Dieter;

  • 作者单位

    Tech Univ Carolo Wilhelmina Braunschweig, Inst Flugzeugbau & Leichtbau, Hermann Blenk Str 35, D-38108 Braunschweig, Germany;

    Tech Univ Carolo Wilhelmina Braunschweig, Inst Stat, Beethovenstr 51, D-38106 Braunschweig, Germany;

    Tech Univ Carolo Wilhelmina Braunschweig, Inst Flugzeugbau & Leichtbau, Grp Multiphys, Hermann Blenk Str 35, D-38108 Braunschweig, Germany;

    Tech Univ Carolo Wilhelmina Braunschweig, Inst Stat, Inst, Beethovenstr 51, D-38106 Braunschweig, Germany;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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