Bi3+敏化YSZ:Eu高温压力敏感磷光涂层及其氧致猝灭机理研究

表面空气流速差引起的表面压力是乘波体高超声速飞行器外形设计与优化的关键参数。然而风洞试验中现有压力敏感涂层因高温热解/蒸发失效问题仅能提供200℃以下的表面压力数据，缺乏耐高温压力敏感涂层成为制约高超声速飞行器设计的瓶颈。申请人基于最新发现的氧空位诱发氧致猝灭效应，提出以高温喷雾热解法和等离子喷涂技术制备的Bi3+敏化YSZ:Eu高温压力敏感磷光涂层，可实现温度高达600℃的表面压力测量，具有重大的科学意义与战略价值。重点研究磷光涂层的压力敏感特性，包括压力与磷光寿命/强度的定量关系、压力敏感度和敏感温度区间，分析晶体结构和稀土离子浓度对压力敏感特性的影响，掌握压力敏感特性在高温环境下的演化规律，构建压力-磷光寿命/强度物理模型和电荷迁移带-压力敏感特性数学模型，阐明氧空位诱发氧致猝灭效应的基本条件、机理和影响因素。本项目旨在为高超声速飞行器领域高温表面压力测量提供新材料和新技术。

Surface pressure generated by the air flow velocity difference is critical parameter in configuration design and optimization of ride wave body hypersonic aircrafts. However, in wind tunnel testing, pressure sensitive paints only can offer accurate measurement of pressure parameters under the temperature of 200 ℃ due to the thermal decomposition or sublimation failure of paints at high temperature. Lack of high temperature pressure sensitive coating has become the bottleneck of hypersonic aircrafts configuration design. Based on the newly discovered oxygen vacancy induced oxygen quenching effect, the applicant put forward a high temperature pressure sensitive Bi3+ sensitized YSZ:Eu phosphor coating prepared using high temperature spray pyrolysis and air plasma spraying technique, which can be used to measure surface pressures at temperatures up to 600 °C. This has great scientific significance and strategic value. The pressure sensitivity characteristics, which include the relationship between surface pressure and luminescent lifetime/intensity, pressure sensitive and sensitive temperature region, will be studied. The role of the crystal structure and the rare earth ion doping concentration on the pressure sensitivity characteristics will also be identified. The evolution of the pressure sensitivity characteristic after thermal aging will be investigated. Then a pressure-luminescent lifetime/intensity physical model and a charge transfer state-pressure sensitivity mathematic model will be developed. Finally the basic conditions, mechanisms and influence factors of the oxygen vacancy induced oxygen quenching will be analyzed in detail. The research achievements of the present project can also provide new method for the surface pressure measurement of the compressor blade of aero engines and gas turbines. The aim of the proposed research is to provide new materials and new techniques for the high temperature surface pressure measurement in the hypersonic aircraft field.