脉冲爆震火箭发动机试验

Experiment on pulse detonation rocket engines

采用航空煤油/氧气为推进剂的脉冲爆震火箭发动机(PDRE)试验模型,进行了有关两相爆震起爆、稳定可控工作、爆燃向爆震转变机理、PDRE可爆范围、加与不加尾喷管时性能测试等方面的实验研究。结果表明,设计的PDRE模型能实现稳定、可控、高频工作,性能接近理论值。各种尾喷管均具有性能增益,其中以收敛喷管增益最大,达18%。

The experimental investigations on PDRE key issues of two-phase detonation initiation, reliable and controllable operation, deflagration to detonation transition mechanism, detonable range, thrust measurements and augmentation with nozzles were presented in detail on PDRE test models using kerosene as fuel and oxygen as oxidizer. The results show that this PDRE prototype can reliably and controllably be operated with high frequency and its performance is good. All 3 chosen nozzles can augment PDRE performance and maximal augmentation of 18% was attained by the convergent nozzle.