高焓激波风洞爆轰驱动技术研究

激波风洞爆轰驱动技术利用引爆可燃混合气体快速释放的化学能产生强激波,压缩激波管的试验气体,提供产生超高速流动所需的试验气源,是近十几年来发展成功的激波风洞强驱动方法.本文分布介绍了反向爆轰驱动、正向爆轰驱动和反向爆轰膨胀驱动模式,分析了应用这些驱动技术产生的高焓、高雷诺数、高超声速流动的气源特点,探讨了不同驱动模式影响激波风洞性能的关键因素.并重点介绍了反向爆轰膨胀驱动模式,分析了影响缝合条件的参数以及二次波现象.应用这些爆轰驱动技术,研制了能够产生总焓为1000K～8000K,具有较长试验时间的高品质超高速气流.为开展高超声速气动实验研究奠定了良好的基础.

Study on detonation drivers for high-enthalpy shock tunnels

In detonation-driven shock tunnels,strong shocks can be generated in shock tubes with chemical energy to compress test gases for hypervelocity experiments.Recently,the detonation driven shock tunnel has become a promising advanced hypersonic test facility.The detonation dfivers were introduced in the paper,including the backward detonation driver,the forward detonation driver and the backward detonation-expansion driver.The reservoir states were analyzed to examine the different detonation drivers.The backward detonation-expansion driver was discussed more to investigate into matching operation condition and secondary waves.With those detonation drivers,an excellent test platform was developed to replicate the hypervelocity flight conditions for air-breathing hypersonic vehicles.High-enthalpy test flows were generated with the total temperature from1000K～8000K with long test duration.Such the flows provide the hypersonic study with the outstanding experimental facilities.