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中文摘要：
采用航空煤油为燃料、氧气为氧化剂、压缩氮气为隔离气体，进行了大量的两相脉冲爆震火箭发动机原理性实验。利用8个压力传感器测量了爆震室轴向沿程的压力，所测得爆震波压力接近充分发展的C—J爆震波。两个实验模型分别使用了0．45和0．9m的Shchelkin螺旋作为DDT（deflagration to detonation transition）间接起爆的增强装置。实验模型Ⅰ的DDT距离约为0．65m，爆震波速约为1873m／s；实验模型Ⅱ的DDT距离约为0．55m，爆震波速约为1838m／s。两种实验模型DDT距离的差异主要是由爆震室内Shchelkin螺旋长度不同引起的。虽然Shchelkin螺旋在缩短DDT距离上起到积极作用，但在形成充分发展爆震波后会降低爆震波的强度。
英文摘要：
Utilizing kerosene as the fuel, oxygen as oxidizer and nitrogen as purge gas, a series of proof-of-principle experiments of a two-phase pulse detonation rocket engine were successfully conducted. The detonation chamber pressure traces were recorded by piezoelectric pressure transducers. The measured pressure of detonation wave was close to that of C-J detonation. Shchelkin spirals as the deflagration-to-detonation transition enhancement device were employed in two PDRE models. The DDT distance and detonation wave velocity were about 0.65 m and 1 873 m/s, respectively, in one model with Shchelkin spirals of 0. 45 m length, while those were about 0.55 m and 1 838 m/s in the other with Shchelkin spirals of 0. 9 m length. The difference of the DDT distance mainly resulted from the different length of Shchelkin spirals in the detonation chamber. Though performing positive effects on shortening the DDT distance, Shchelkin spirals would decrease the detonation wave＇s intensity during the detonation propagation.
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