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The dynamic interaction between a hypersonic flow and a flexible panel

高超声速流与柔性面板之间的动态相互作用

基本信息

批准号：
1913587
负责人：
Noel Clemens
金额：
$ 55.89万
依托单位：
University of Texas at Austin
依托单位国家：
美国
项目类别：
Standard Grant
财政年份：
2019
资助国家：
美国
起止时间：
2019-09-15 至 2023-08-31
项目状态：
已结题

来源：
https://www.nsf.gov/awardsearch/showAward?AWD_ID=1913587&HistoricalAwards=false
关键词：
dynamic interaction between hypersonic flow

项目摘要

A major challenge in hypersonic flight is the presence of large aerodynamic forces and high heating rates that combine to cause dynamic deformation and thermal-induced buckling of aircraft structures. The interaction between a shock wave and the boundary layer can cause high heating, vibrations and structural instabilities such as flutter. These effects can lead to fatigue of thin panel structures with potentially catastrophic implications for a flight vehicle. To address these issues, this project will investigate the flow near a compliant panel under hypersonic conditions. It will also lead to an educational partnership between University of Texas-Austin and Huston-Tillotson University - small private historically black university.The goal of the proposed work is to investigate the interaction between a thin compliant panel underneath hypersonic separated flows which are generated by single- and double-sharp fins at an angle of attack. Combined kilo Hertz-rate optical diagnostics will be used to make simultaneous measurements of the panel displacement, surface pressures, and near-wall velocity fields. A range of panel thicknesses will be used to vary the vibrational frequencies and amplitudes. An important innovation will be the use a new inverse method to compute the fluctuating pressure field that causes the dynamic deformation. Tailoring the elastic and inertial properties of the panels will enable the investigation of passive control of the separated flow unsteadiness and, thus, potentially reduce the deleterious effects of the separated flow by purposeful design. The educational plan will focus on a robust effort to engage under-represented minority undergraduate students in the research.The project is co-funded by the Air Force Office of Scientific Research.This award reflects NSF's statutory mission and has been deemed worthy of support through evaluation using the Foundation's intellectual merit and broader impacts review criteria.

高超音速飞行的一个主要挑战是存在巨大的气动力和高加热速率，这两者结合起来会导致飞机结构的动态变形和热致屈曲。冲击波和边界层之间的相互作用会导致高热、振动和结构不稳定（例如颤振）。这些影响可能会导致薄板结构疲劳，从而对飞行器产生潜在的灾难性影响。为了解决这些问题，该项目将研究高超音速条件下兼容面板附近的流动。它还将促成德克萨斯大学奥斯汀分校和休斯顿蒂洛森大学（历史上规模较小的私立黑人大学）之间的教育合作伙伴关系。拟议工作的目标是研究高超音速分离流下方薄柔顺面板之间的相互作用，这些高超音速分离流是由单锋利翅片和双锋利翅片以攻角产生的。组合千赫兹速率光学诊断将用于同时测量面板位移、表面压力和近壁速度场。一系列面板厚度将用于改变振动频率和振幅。一项重要的创新是使用一种新的反演方法来计算引起动态变形的脉动压力场。定制面板的弹性和惯性特性将使研究分离流不稳定性的被动控制成为可能，从而通过有目的的设计潜在地减少分离流的有害影响。该教育计划将侧重于大力吸引少数族裔本科生参与研究。该项目由空军科学研究办公室共同资助。该奖项反映了 NSF 的法定使命，并通过使用基金会的智力优点和更广泛的影响审查标准进行评估，被认为值得支持。

项目成果

期刊论文数量（7）

专著数量（0）

科研奖励数量（0）

会议论文数量（0）

专利数量（0）

Effect of Structural Modifications on Vibratory Response of Panel under Ramp-Induced Shock Wave Boundary Layer Interaction

DOI：
10.2514/6.2022-2486
发表时间：
2022-01
期刊：
AIAA SCITECH 2022 Forum
影响因子：
0
作者：
M. Eitner;Yoo-Jin Ahn;M. Musta;J. Sirohi;N. Clemens
通讯作者：
M. Eitner;Yoo-Jin Ahn;M. Musta;J. Sirohi;N. Clemens

Experimental Investigation of Flow-Structure Interaction for a Compliant Panel under a Mach 2 Compression-Ramp

马赫 2 压缩斜坡下顺应面板流-结构相互作用的实验研究

DOI：
10.2514/6.2022-0293
发表时间：
2022
期刊：
AIAA Scitech Meeting
影响因子：
0
作者：
Ahn, Yoo-Jin;Musta, Mustafa N.;Eitner, Marc A.;Sirohi, Jayant;Clemens, Noel T.
通讯作者：
Clemens, Noel T.

Experimental Investigation of Fluid-Structure Interaction in Mach 2 Flow Using Simultaneous High-Speed PIV and DIC

使用同时高速 PIV 和 DIC 进行 2 马赫流中流固耦合的实验研究

DOI：
发表时间：
2022
期刊：
20th International Symposium on Application of Laser and Imaging Techniques to Fluid Mechanics
影响因子：
0
作者：
Ahn, Y.-J.;Eitner, M.A.;Rafati, S.;Musta, M.N.;Sirohi, J.;Clemens, N.T.
通讯作者：
Clemens, N.T.

Effect of Shock Wave Boundary Layer Interaction on Vibratory Response of a Compliant Panel

冲击波边界层相互作用对柔性面板振动响应的影响