火炬式电点火系统点火能量的正交试验研究

Orthogonal Testing Study on Ignition Energy of a Torch Ignition System

点火技术研究是实现低温液体火箭发动机多次启动的关键,而点火能量研究是确保点火可靠的前提。基于所设计的低压式点火系统方案,给出点火系统所能释放能量的计算过程;运用正交试验法探究氧入口压力、氧入口温度、氢入口压力、点火系统推进剂总流量以及点火室混合比等因素对点火能量的影响规律与影响趋势。结果表明:点火室流量对点火能量的影响程度最大,氢入口压力对点火能量的影响程度最小;随着氧入口温度、氢入口压力和点火室推进剂流量的增大,点火能量均呈增大趋势;随着氧入口压力和点火室混合比的增大,点火能量均呈减小趋势。

Ignition technology is crucial to realize cryogenic liquid rocket engines＇ multiple start-ups. So is ignition energy investigation to ignition reliability. On the basis of a self-designed low pressure ignition system, a calculation process of ignition energy release is proposed in this paper. Besides, the effect of oxygen inlet pressure, oxygen inlet temperature, hydrogen inlet pressure, propellant flow and mixture ratio on ignition energy is examined by use of orthogonal testing method. Study results indicate that the propellant flow is the most significant factor affecting the ignition power, and the hydrogen pressure exerts little influence. It is also found the ignition energy increases as the oxygen inlet temperature, hydrogen inlet pressure and propellant flow rise, while it decreased as the oxygen inlet pressure and mixture ration rise.