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An efficient fluid-structure interaction method for conceptual design of flexible micro air vehicle wings: Development, comparison, and application .

机译：一种用于柔性微型航空器机翼概念设计的有效流固耦合方法：开发，比较和应用。

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摘要

This thesis summarizes the development, comparison, and applications of an efficient fluid-structure interaction method capable of simulating the effects that wing flexibility has on micro air vehicle (MAV) performance. Micro air vehicles wing designs often incorporate flexible wing structures that mimic the skeleton / membrane designs found in natural flyers such as bats and insects. However, accurate performance prediction for these wings requires the coupling of the simulation of the fluid physics around the wing and the simulation of the structural deformation. These fluid-structure interaction (FSI) simulations are often accomplished using high fidelity, computationally expensive techniques such as computational fluid dynamics (CFD) for the fluid physics and nonlinear finite element analysis (FEA) for the structural simulation. The main drawback of these methods, especially for use simulating vehicles that are able to be manufactured relatively quickly, is that the computational cost required to perform relevant trade studies on the design is prohibitively large and time-consuming. The main goal of this research is the development of a coupled fluid-structure interaction method computationally efficient and accurate enough to be used for conceptual design of micro air vehicles. An advanced potential flow model is used to calculate aerodynamic performance and loading, while a simplified finite element structural model using frame and shell elements calculates the wing deflection due to aerodynamic loading. The contents of this thesis include a literature survey of current approaches, an introduction to the efficient FSI formulation, comparison of the presented FSI method with higher-fidelity simulation methods, demonstrations of the method's capability for tradeoff and optimization studies, and an overview of contributions to a nonlinear dynamic algorithm for the simulation of flapping flight.
机译：本文总结了一种有效的流固耦合方法的发展，比较和应用，该方法能够模拟机翼柔性对微型飞行器（MAV）性能的影响。微型飞行器的机翼设计通常包含可弯曲的机翼结构，该结构模仿了蝙蝠和昆虫等自然飞行器中的骨架/膜设计。但是，要准确预测这些机翼的性能，就需要将机翼周围的流体物理模拟与结构变形的模拟结合起来。这些流固耦合（FSI）仿真通常使用高保真，计算成本高的技术​​来完成，例如用于流体物理的计算流体动力学（CFD）和用于结构仿真的非线性有限元分析（FEA）。这些方法的主要缺点，特别是对于能够相对快速地制造的仿真车辆而言，是对设计进行相关贸易研究所需的计算成本过大且费时。这项研究的主要目的是开发一种计算效率高且精确到足以用于微型飞行器概念设计的流固耦合方法。先进的势流模型用于计算空气动力性能和载荷，而简化的有限元结构模型使用框架和壳单元计算由于空气动力载荷引起的机翼挠度。本文的内容包括对当前方法的文献综述，有效FSI公式的介绍，所提出的FSI方法与高保真模拟方法的比较，方法的折衷和优化研究能力的证明以及贡献概述非线性动力学算法来模拟扑翼飞行。

著录项

  • 作者

    Combes, Thomas P.;

  • 作者单位

    Saint Louis University.;

  • 授予单位 Saint Louis University.;
  • 学科 Engineering Aerospace.
  • 学位 M.S.
  • 年度 2012
  • 页码 136 p.
  • 总页数 136
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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