高超声速激波风洞气动力测量技术研究

项目名称： 高超声速激波风洞气动力测量技术研究

项目编号： No.11302232

项目类型： 青年科学基金项目

立项/批准年度： 2014

项目学科： 数理科学和化学

项目作者： 汪运鹏

作者单位： 中国科学院力学研究所

项目金额： 28万元

中文摘要： 高超声速激波风洞由于流场瞬时建立，在进行气动力试验时，巨大的冲击载荷激发起模型、测力元件、支撑系统及风洞部件的振动，形成惯性干扰力。其与真实气动力混杂在一起，甚至覆盖气动力，将极大降低试验精准度，出现气动信号无法使用的情况。同时，试验模型的尺度、质量也受到极大的限制。因此，应用激波风洞进行测力试验仍存在诸多问题，尤其对于大、重模型的测力试验，更是鲜有报道和文章发表。本项目基于这些测力关键技术问题，探索新型内置杆式应变天平结构，利用有限元数值技术设计优化激波风洞测力专用应变天平；对冲击振动载荷进行系统的理论、数值及试验（模态）分析，提出针对激波风洞气动力试验低频振动惯性力干扰信号的合理补偿方法；针对若干测力技术关键问题，拟定不同试验方案，并在力学所高温气动国家重点实验室的JF12复现高超声速飞行条件激波风洞开展实际测量。

中文关键词： 高超声速；激波风洞；气动力测量；应变天平；

英文摘要： Due to the instantaneous flow field and the short test time, mechanical vibration of the balance system is generated and cannot be damped when the measurement of aerodynamic force is carried out in hypersonic shock tunnel. The inertial forces lead to low frequency vibrations of the model and its motion cannot be addressed through digital filtering since enough cycles cannot be found during a tunnel run. This implies restriction on the model size and mass as its natural frequencies are inversely proportional the length scale of the model. Therefore, there are still many problems for the aerodynamic measurements in a shock tunnel, especially for the large and heavy models, where almost no relevant reports and articles can be found. In order to overcome the difficulties encountered by the measurement of aerodynamic force in the shock tunnel, we explore the new structure of the balance, design and optimize the special strain balance for the aerodynamic measurement in hypersonic shock tunnel; The theoretical, numerical and experimental (modal) analyses are carried out for mechanical vibration of the measurement system, in order to reasonably compensate for output signal, which created by using the large model with low-frequency vibration; In order to solve the key technical problems, the different test cases for the

英文关键词： hypersonic；shock tunnel；aerodynamic force measurement；strain gauge balance；