小型推进系统进发匹配高速风洞特种试验技术研究

摘要

为检验弹类等小型飞行器推进系统的进气道与发动机工作匹配特性,在暂冲式高速风洞研制了适于小型推进系统进发匹配测试的特种试验技术.研究分析了小型推进系统进发匹配高速风洞试验模型和支撑系统气动和结构问题,给出了试验方案与试验流程,解决了环境污染、试验安全性、模型热防护等关键技术问题.试验表明利用现有暂冲式风洞,能够在地面试验阶段解决小型推进系统进发匹配问题,实现发动机高空试验台或推进风洞的进发匹配试验功能,能为小型推进系统在模拟外流条件下的进发匹配测试提供良好的试验环境,具有工程应用价值.%A special test technique applied to inlet/engine matching of small-size propulsion system is developed in a high speed wind tunnel,the purpose is to predict and verify the characteristics of inlet/engine matching for the propulsion system of a small-size flying vehicle such as a cruise missile.Analysis of the aerodynamic and structural issues on the test model and support system,test plan,test methods and the related procedures,as well as the evaluation of environment pollution,test safety and model protection are represented.Tests show that the technique applied to the available intermittent wind tunnels is able to solve inlet/engine matching in the phase of ground testing,plays the roles of high altitude test beds and propulsion wind tunnels,and provides a good test environment of outer airflow simulation for small-size propulsion systems.The technique is of practical and applicable value.