导弹用吸气式两相脉冲爆震发动机可行性研究

Exploring Feasibility of Missile's Employment of Air-Breathing Two-Phase PDE (Pulse Detonation Engine)

设计了内径为60 mm的吸气式两相脉冲爆震发动机,并在冷流条件下测试了进气道的流阻系数。在接近大气压条件下,成功地进行了以汽油为燃料、以空气为氧化剂的吸气式两相脉冲爆震发动机原理性试验。试验中在爆震管内部安装Shchelk in螺旋来促进爆震波的生成,所测量的爆震波压强接近充分发展的爆震波,发动机最高工作频率达到15 H z;进气道内压强变化幅度小于0.1 M Pa,说明所设计的进气道与爆震管匹配良好,这为将脉冲爆震发动机用于工程实际提供了技术储备。

Aim. We have gradually come to believe that recent progress in PDE research has made it quite feasible to let missiles, UAVs and UCAVs to employ air-breathing two-phase PDE. We now report the results of our exploratory study on such feasibility. In the full paper, we explain in detail our exploration; in this abstract, we just add some pertinent remarks to the two topics of our explanation： （A） experimental method and setup; Fig. 1 in the full paper shows the schematic of our experimental airbreathing PDE model, 60mm in inside diameter, which includes the well-known Shchelkin spiral; （B） experimental results and analysis; under cool flow conditions, the inner flow resistance coefficient of the inlet was measured; under nearly atmospheric pressure, a proof-of-principle experiment of a two-phase air-breathing PDE model was successfully carried out; we developed liquid C8H18/air mixture for this study; Figs. 2 through 6 in the full paper show clearly the very important fact that the measured detonation wave pressure was very close to that of fully developed detonation; the PDE model was operated at a repetition frequency up to 15 Hz with the pressure＇s variation inside the intake always within 0. 1 MPa experimentally, implying that the intake designed matches the detonation tube well.