Non-linear aeroelasticity and health monitoring of anisotropic curved structures

各向异性弯曲结构的非线性气动弹性和健康监测

• 批准号: RGPIN-2015-03800
• 负责人: Lakis, AouniA
• 金额: $ 2.11万
• 依托单位: École Polytechnique de Montréal
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2016
• 资助国家: 加拿大
• 起止时间: 2016-01-01 至 2017-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=612578
• 关键词: Non; linear; aeroelasticity; health; monitoring

The proposed work involves both fundamental and applied research. It is a continuation of the aforementioned research study by integrating more realistic and complex aspects of structure and flow, in which nonlinear aspects of structure as well as fluid nonlinearity and non-proportional damping will be considered. PROGRESS OF RESEARCH. In recent years, our team has studied two major areas: numerical analysis of fluid structure systems and signal processing methods for vibration. These studies led to the publication of numerous scientific articles and our results were used by companies such as IREQ, Spar Aerospace/EMS Technologies, CAE Electronics the NRC aerospace research institute’s structure, materials and propulsion group, Bombardier and P&WC. These studies produced the following results: Numerical simulation of vibration of cylindrical and conical shells subjected to compressible or incompressible fluid flow. Since these shell elements are used widely in aerospace structures, predicting the dynamic instability of shells subjected to flow is a challenging subject that aeronautical engineers are confronted with. For such a problem that contains complex structures, boundary conditions, materials and loading, an analytical model becomes very complicated when undergoing a change of factors affecting the flutter boundaries. Therefore, a numerical package based on a hybrid finite element method has been developed to describe the aeroelastic behavior of curved shells. It provides very fast and precise convergence compared to existing commercial FEM software at less computational time and cost. The results of these works have been presented at an international conference and published in international journals [1, 2]. The linear theory developed is adequate to predict the onset of flutter, however nonlinear shell theory required to capture the actual limit cycle amplitude of the flutter is left for this proposed research.   OBJECTIVES. The main goal of this research is to provide new insights on the subject of flutter of curved structures such as cylindrical and conical shells. Particular attention is paid to the influence of parameters such as dynamic pressure, flow angles and panel curvature on aeroelastic behavior. Consistent nonlinear hybrid finite element formulations and efficient solution procedures are developed and presented. The short-term objectives will address the following points: A) Bifurcation and nonlinear dynamic analysis of curved structures. B) Nonlinear aeroelastic analysis of shells of revolution subjected to supersonic flow. C) Sloshing effect on the aeroelastic stability of curved structures. D) Development of a nonlinear method to predict the response of anisotropic curved structures subjected to a turbulent boundary-layer-induced random pressure field.

拟议的工作涉及基础研究和应用研究。这是相关研究的延续，通过整合结构和流动的更现实和复杂的方面，其中将考虑结构的非线性方面以及流体非线性和非比例阻尼。研究进展。近年来，我们的团队研究了两个主要领域：流体结构系统的数值分析和振动的信号处理方法。这些研究导致发表了许多科学文章，我们的结果是由IREQ，SPAR Aerospace/EMS技术，CAE电子等公司使用的，NRC航空航天研究所的结构，材料和推进小组，Bombardier和P＆WC。这些研究产生了以下结果：圆柱和化学壳的振动的数值模拟，受到可压缩或不可压缩的流体流量。由于这些壳体元素在航空航天结构中广泛使用，因此预测经过流动的壳的动态不稳定性是航空工程师面临的挑战主题。对于包含复杂结构，边界条件，材料和载荷的问题，分析模型在发生影响颤动边界的因素的变化时变得非常复杂。因此，与现有的计算时间和成本相比，基于混合有限元方法的数值软件包具有非常快速，精确的收敛性。这些作品的结果已在国际会议上提出，并在国际期刊上发表[1，2]。所开发的线性理论足以预测扑动的发作，但是捕获弹力的实际极限周期放大器所需的非线性壳理论是为了进行这项拟议的研究。   目标。这项研究的主要目标是就曲面结构（例如圆柱形和圆锥形壳）的颤动提供新的见解。特别注意参数的影响，例如动态压力，流动角和面板曲率对航空弹性行为的影响。一致的非线性混合有限元公式和有效的解决方案程序得以开发和呈现。短期目标将解决以下几点：a）弯曲结构的分叉和非线性动态分析。 b）受超音速流的革命壳的非线性航空弹性分析。 c）对弯曲结构的气弹性稳定性的晃动作用。 d）开发一种非线性方法，以预测受湍流边界层诱导的随机压力场的各向异性弯曲结构的响应。