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首页> 外文会议>54th Israel annual conference on aerospace sciences : program >Aeroelastic and Aerothermoelastic Behavior of a Hypersonic Vehicle Control Surface
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Aeroelastic and Aerothermoelastic Behavior of a Hypersonic Vehicle Control Surface

机译：高超音速飞行器控制面的气动弹性和气动热弹性行为

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摘要

A framework for aerothermoelastic stability boundary calculation forrnhypersonic confgurations using CFD combined is developed. Applica-rntion of CFD enables one to consider diu000berent turbulence conditions,rnlaminar or turbulent, and diu000berent models of the air mixture, in par-rnticular real gas model which accounts for dissociation of molecules atrnhigh temperature. The eu000bect of transition on the rutter margin of thernheated structure is also considered. A new version of piston theory isrnformulated which is both more accurate and convenient to use for hy-rnpersonic aeroelasticity than conventional third order piston theory. Thernaerothermoelastic stability margin of a three-dimensional low aspect ra-rntio wing, representative of a control surface of a hypersonic vehicle isrnexamined for various right conditions. The system is found to be sen-rnsitive to turbulence modeling as well as the location of the transitionrnfrom laminar to turbulent row. Real gas eu000bects play a minor role forrnthe right conditions considered. This study emphasizes the importantrnrelation between transition from laminar to turbulent, thermal stressesrnand stability margins of hypersonic vehicles.
机译：建立了结合CFD的人身配置的气弹弹性稳定边界计算框架。 CFD的应用使人们可以在特定的真实气体模型中考虑高温下分子解离的双重湍流条件，层流或湍流以及空气混合物的双重模型。还考虑了转变对加热结构的车辙边缘的影响。公式化了新版本的活塞理论，它比常规的三阶活塞理论更准确，更方便地用于人身气动弹性。在各种合适的条件下，对三维低剖面雷达机翼的热弹性弹性裕度（代表高超音速飞行器的控制面）进行了检查。发现该系统对湍流建模以及从层流到湍流行的过渡位置很敏感。在考虑正确的条件下，真正的天然气eu000bects扮演着次要的角色。这项研究强调了从层流到湍流的过渡，热应力和高超声速飞行器的稳定裕度之间的重要关系。

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