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Integrated modeling and control of flexible aircraft wings.

机译:柔性飞机机翼的集成建模和控制。

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摘要

Structural control for vibration reduction has important applications in many research areas, including the effect of earthquakes on buildings and aerodynamic forces on aircraft stability and performance. Both passive and active control techniques have been implemented, with the best solution usually involving a passive approach followed by an active one. This thesis presents an integrated modeling and controller design approach. Modal Cost Analysis (MCA) and Output Covariance Constraint (OCC) control are used to reduce a high-order aeroelastic wing model to establish the best controller for the reduced-order model, with a constraint on the covariance of the vibration outputs. MCA seeks to keep the modes that have the highest contribution to a given cost function. Using iterations on the two processes will allow a lower-order controller to be designed and result in the same performance.;The OCC and MCA methods and their respective algorithms are presented, and an approach to integrate the two procedures is given. NASA's model used in this thesis is applied to the MCA and OCC algorithms using MATLAB. A 40 th-order wing model is derived. The model reduction technique initially reduces the system to a 12th order one. A simulation of the OCC algorithm is performed on the reduced-order model and applied to the full-order model. The controller resulting in the best closed-loop performance is shown to significantly reduce the vibrations due to wind. A corresponding weighting matrix used in OCC is then used for a second round of MCA to further reduce the model to an 8th order model. A lower-order controller designed for this second model is shown to similarly reduce the output vibrations.
机译:减振的结构控制在许多研究领域都有重要的应用,包括地震对建筑物的影响以及空气动力对飞机稳定性和性能的影响。被动和主动控制技术均已实现,最佳解决方案通常包括被动方法和主动方法。本文提出了一种集成的建模与控制器设计方法。模态成本分析(MCA)和输出协方差约束(OCC)控制用于减少高阶气动弹性机翼模型,从而为降阶模型建立最佳控制器,并限制振动输出的协方差。 MCA致力于保持对给定成本函数贡献最大的模式。在这两个过程上使用迭代将允许设计一个低阶控制器,并产生相同的性能。;提出了OCC和MCA方法以及它们各自的算法,并给出了集成这两个过程的方法。本文使用的NASA模型已通过MATLAB应用于MCA和OCC算法。推导了40阶机翼模型。模型简化技术最初将系统简化为12阶系统。在降阶模型上执行OCC算法的仿真,并将其应用于全阶模型。控制器具有最佳的闭环性能,可显着降低风引起的振动。然后将OCC中使用的相应加权矩阵用于第二轮MCA,以将模型进一步简化为8阶模型。所示为该第二个模型设计的低阶控制器可以类似地减少输出振动。

著录项

  • 作者

    Wehr, Dagmara Anna.;

  • 作者单位

    Michigan State University.;

  • 授予单位 Michigan State University.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.;Engineering Electronics and Electrical.
  • 学位 M.S.
  • 年度 2014
  • 页码 48 p.
  • 总页数 48
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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