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。

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.