爆震波多管点火特性实验

为了研究液体火箭发动机爆震波多管点火的同步性能、多次点火重复性能以及点火火炬性能,组建了氢氧爆震波多管点火实验系统。采用氢气和氧气为工质,常温供气压力0.10.5 M Pa（表压）,混合比1.87.2,进行了多次实验。实验结果表明:爆震波点火技术可以在与液体火箭发动机贮箱压力相适应的较低的供气压力下获得高温（>1300℃）高压（>1 M Pa）爆震产物,并且具备良好的点火重复性能和多管点火同步性能,多次点火重复性时间差和多管点火同步性时间差均小于0.3 m s。爆震波多管点火技术适合用于多燃烧室液体火箭发动机的同步点火。 

Experimental Investigation on Multiple Pipe Detonation Wave Ignition

To investigate the synchronization characteristics,reduplication characteristics and torch characteristics of detonation wave multiple-unit ignition technique of the liquid rocket engine,the experimental apparatus has been set up.Gas hydrogen and gas oxygen were used as working substance.Many experiments were carried out under normal temperature and 0.1～0.5 MPa gauge pressure conditions and with the mixture ratio of 1.8～7.2.The results show that the detonation wave ignition technique can provide high temperature(>1 300℃) and high pressure(>1 MPa) with low supply gas pressure which accommodates to the vapor pressure in fuel tanks of the liquid rocket engine.It has excellent synchronization and reduplication characteristics and the synchronization errors of both reduplication and multi-unit ignition are less than 0.3 ms.The detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.