双分量快速响应PSP高超声速流场表面压力测量技术研究

Fast response PSP offers the unique capability for full-field measurements of surface pressure on a complex aerodynamic model with a much higher spatial and temporal resolution and a lower cost. To solve the issues of slow response, temperature effect and low signal-to-noise ratio in hypersonic flow, the project will develop fast response two-color PSP measurement with higher accuracy. Single-component PSP technology is insufficient for hypersonic flow field and engineering application, the research will improve the formulation and fabrication process of the fast response two-color PSP, and study the adaptive temperature compensation method, data analysis method based on modal decomposition and the hardware requirements. At last, global pressure measurement system in hypersonic flow field based on the two-color fast response PSP would be established. Through experiment verification and theoretical analysis, this project will achieve the ability of deepening the characterization of unsteady aerodynamic loads and flow field structures. Accurate PSP data play a key role in validation and verification of computational fluid dynamics (CFD) codes. The new, non-contact and full-field optical technique is of extensive research significance and engineering application value for the aerodynamic design and performance improvement in the aerodynamics research.

快速响应PSP技术作为一种全局表面压力动态测量方法，提供以非接触方式和较小成本完成对复杂气动模型进行表面高空/时间分辨率测量的独特能力，但在高超声速风洞环境中应用还存在响应慢、温度效应强和信噪比低等问题。本项目在现有PSP技术基础上，发展高精度双分量快速响应PSP表面压力测量技术。针对单一组份PSP测试技术不足和高超声速流场表面非定常压力分布测量的工程应用需求，本项目以典型的高超声速绕流场为研究对象，展开适用高超声速流场的快速响应双分量涂料研制与优化，结合自适应的全局温度补偿修正方法和基于模态分解的数据分析方法，以及相关硬件需求研究，建立双分量快速响应PSP高超声速流场全局表面压力测量系统。通过实验验证结合理论分析，加深对非定常气动载荷及流场结构精细刻画能力，对理解流场特性，检验数值模拟起着关键作用。同时，对于高超声速飞行器气动设计、性能提升，提供全机压力数据支撑和验证具有广泛的研究意义。

全局表面压力的定量测量是流体力学中重要的课题，尤其对于高超声速飞行器气动设计、性能提升，提供全机压力数据支撑和验证具有广泛的研究意义。本课题针对高超声速流场表面压力分布，完善已有的单分量快速响应PSP技术和稳态双分量PSP技术，通过研究快速响应双分量压敏涂料配方和工艺、涂料的静态和动态特性标定、自适应的全局温度补偿校正方法及相关硬件需求等研究，建立快速响应双分量PSP高超声速流场全局表面压力测量系统，通过实验与验证研究，形成为高超声速实验提供高时间分辨率和高空间分辨率的表面压力测量的能力。本课题发展的高超风洞的双分量PSP测试系统，完成多次高超风洞测量试验，获得了高频、高精度压力试验结果，极大地提高复杂流场的实验模拟研究能力，显现高超声速复杂流动的显示和高精度测试，提升对外流、内流中复杂流动现象的认识，为高超声速飞行器设计和优化提供试验技术支持和储备。其中，高超声速PSP测量系统成果已在FD-03风洞、FD-20风洞典型压缩拐角试验中应用，提高了现有高超声速风洞PSP技术压力精确测量能力，对于高超声速/超声速飞行器的气动设计、性能提升，提供全机数据支撑和验证具有明确实用的工程应用价值。