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首页> 外文期刊>Journal of Spacecraft and Rockets >Aeroelastic Analysis of Pinched Panels in Supersonic Flow Changing with Altitude
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Aeroelastic Analysis of Pinched Panels in Supersonic Flow Changing with Altitude

机译：超音速随高度变化的挤压面板的气动弹性分析。

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摘要

An analysis of panel flutter phenomena for panels supported by a fixed number of pinched points and exposed to flow conditions that vary with altitude is reported in this paper. This is the case of so-called thermal insulation panels attached to space launcher tanks for which no results have been found in the open literature. Because piston theory has been used for the flow, attention has been limited to supersonic flows. The structural model is based on a refined one-dimensional variable kinematic theory, which has been recently proposed by the authors. The aeroelastic governing equations have been written in matrix form by employing finite element methods. These methods are very appropriated for pinched boundary conditions considered herein. Various numbers of attachment points have been considered as well as simply supported cases. A flutter boundary has been established for various flat panels and flow conditions.
机译：本文报道了对固定夹点支撑并暴露于随高度变化的流动条件的面板的面板颤振现象的分析。所谓的隔热板就是这种情况，该隔热板安装在空间发射舱上，在公开文献中未发现结果。由于已将活塞理论用于流动，因此注意力仅限于超声速流动。结构模型基于改进的一维变量运动学理论，这是作者最近提出的。气动弹性控制方程采用有限元方法以矩阵形式编写。这些方法非常适合此处考虑的挤压边界条件。已经考虑了各种数量的连接点以及简单支持的案例。已经针对各种平板和流动条件建立了颤动边界。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2014年第1期|187-199|共13页
  • 作者

    E. Carrera; E. Zappino;

  • 作者单位

    Politecnico di Torino, 10129 Torino, Italy;

    Politecnico di Torino, 10129 Torino, Italy;

  • 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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