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为了获得脉冲爆震火箭发动机(PDRE)的性能参数,采用液态煤油为燃料、氧气为氧化剂、压缩氮气为隔离气体,进行了一系列多循环爆震实验。使用孔板流量计测量煤油流量,使用集气法测量氧气流量,使用动态压电式压力传感器测量了爆震室轴向的沿程压力,使用火焰温度及水蒸气浓度红外光谱测量仪测量爆震管出口平面的尾焰温度,使用动态压电式推力传感器测量PDRE所产生的瞬时推力。实验获得PDRE不同频率下的平均推力和比冲。实验结果表明:爆震压力和温度随着工作频率的变化而有所变化,填充系数对于PDRE比冲大小有着显著影响。采用爆震室部分填充的策略,可以显著地提高发动机比冲。
In order to obtain the performance parameters of pulse detonation rocket motor (PDRE), a series of multi-cycle detonation experiments were carried out using liquid kerosene as fuel, oxygen as oxidant and compressed nitrogen as isolation gas. The kerosene flow rate was measured by orifice flowmeter, the oxygen flow rate was measured by gas gathering method, the axial pressure along the detonation chamber was measured by dynamic piezoelectric pressure sensor, and the flame was measured by flame temperature and water vapor concentration infrared spectrometer Tube temperature at the exit of the outlet plane was measured using a dynamic piezoelectric thrust sensor to measure the instantaneous thrust generated by the PDRE. The average thrust and specific impulse at different frequencies of PDRE were obtained experimentally. The experimental results show that the pressure and temperature of the knocking vary with the operating frequency, and the filling factor has a significant effect on the PDRE specific impulse size. The strategy of partially filling the detonation chamber can significantly improve the engine specific impulse.