论文标题
部分可观测时空混沌系统的无模型预测
The criterion on the Propulsive Balance of Oblique Detonation Engine
论文作者
论文摘要
由于其高热效率和紧凑的结构，斜爆炸引擎（ODE）已建立了高超音速飞行的明显优势。近年来，它已成为世界各地的研究热点。这项研究的目的是在ODE的推进平衡上得出一个标准，我们可以从中明确找到控制推进性能的关键参数。提出了一个物理模型，由进气，恒定的横截面燃烧器和发散喷嘴组成。推导了发散喷嘴产生的推力和入口产生的压力阻力的数学方程式。然后获得ODE的净推力。该标准清楚地表明，发动机入口出口处的静态温度是非常重要的参数。入口出口温度越低，特定脉冲的越高。使用这些方程式计算具有化学计量H2/空气混合物和碳氢化合物/空气混合物的特定脉冲。结果表明，ODE可以从MA8到MA15获得正净推力。
The oblique detonation engine (ODE) has established a clear superiority for hypersonic flight because of its high thermal efficiency and compact structure. It has become the research hot spot all over the world in recent years. The aim of this study is to derive a criterion on the propulsive balance of ODE, from which we can find the key parameters governing the propulsive performance explicitly. A physical model of ODE is put forth, which consists of the inlet, the constant cross-section combustor and the divergent nozzle. The mathematical equations to calculate the thrust generated by the divergent nozzle and the pressure drag produced by the inlet are deduced. The net thrust of ODE is then obtained. The criterion shows clearly that the static temperature at the engine inlet exit is a very important parameter. The lower the inlet exit temperature is, the higher the specific impulse will be. The specific impulse of ODE with stoichiometric H2/air mixture and hydrocarbon/air mixture are calculated by using these equations. The results show that ODE can obtain positive net thrust from Ma8 to Ma15.
