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Nonlinear Modeling and Aeroelastic Analysis of an Adaptive Camber Wing

机译:自适应弧形机翼的非线性建模和气弹性分析

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摘要

Static aeroelastic analysis of an adaptive camber wing subjected to low-speed subsonic flow is presented. In finitenelement modeling follower forces, geometric nonlinearity, and contact definitions are included to accuratelynintegrate a previously designed hingeless control surface into thewing.Camber variation is controlled at six spanwisenstations using actuators for which actuation force magnitudes are determined iteratively using linearized influencencoefficients. Flow solutions are obtained using a high-order panel method, and aeroelastic coupling is performednusing the in-house code SAMOA. For morphed-wing configurations, induced drag is reduced by creating washout.nBy conducting static aeroelastic analysis actuation, force magnitudes are determined and favorable aerodynamicneffects are identified. Results indicate that use of a nonlinear structural model is essential in capturing the stiffeningnbehavior observed during application of spanwise variable camber.
机译:提出了一种适应性外倾翼在低速亚音速流作用下的静态气动弹性分析。在基础模型中,从动力,几何非线性和接触定义被包括在内,以将先前设计的无铰链控制面准确地整合到机翼中。使用六个执行器来控制弯度变化,这些执行器使用线性化的影响系数来迭代地确定驱动力的大小。使用高阶面板方法获得流动解,并使用内部代码SAMOA进行气动弹性耦合。对于变形机翼配置,通过产生冲蚀来减少诱导阻力。通过进行静态气动弹性分析致动,可以确定力的大小并识别出有利的气动效果。结果表明,非线性结构模型的使用对于捕获在应用翼展方向可变弯度时观察到的加强行为至关重要。

著录项

  • 来源
    《Journal of Aircraft》 |2010年第6期|p.2067-2074|共8页
  • 作者单位

    Middle East Technical University, Ankara 06531, Turkey;

  • 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
  • 中图分类
  • 关键词

  • 入库时间 2022-08-17 23:06:13

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