脉冲爆震发动机的飞行性能计算与分析  

Calculation and analysis of pulse detonation engine flight performance

作　　者：金涛[1] 何立明[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《推进技术》2007年第2期190-193,共4页Journal of Propulsion Technology

基　　金：中国博士后科学基金资助项目(中博基[2003]03号)

摘　　要：为了获得脉冲爆震发动机的飞行性能参数随飞行高度和飞行速度的变化规律,在应用最小G ibbs自由能理论建立求解爆震燃烧的平衡成分及其浓度、平衡参数的基本关系式,据此对爆震波特性参数进行数值模拟的基础上,通过引入进气道和尾喷管建立了一定飞行状态下的多管自吸气式脉冲爆震发动机理论性能计算模型,对脉冲爆震发动机的性能随飞行高度、速度的变化趋势进行研究。结果表明,在不同飞行高度和飞行马赫数的状态下,脉冲爆震发动机性能有一定的变化规律,同时模型也考虑了加入尾喷管对性能的影响,为脉冲爆震发动机的性能分析与理论设计提供了依据。To gain the changing rules of pulse detonation engine performance parameters with different flight altitude and Mach number, the basic equations of detonation combustion＇ s equilibrium composition and density, equilibrium parameters were established for numerical simulation of detonation wave performance parameters with theory of Gibbs free energy minimization, and with which, a performance calculation model of air-breathing pulse detonation engine with inlet and nozzle was established in some flight regimes. The variation trends of the pulse detonation engine performance with flight altitude and velocity were studied. The results show that performance of pulse detonation engine has some variation trends in some regimes of different flight altitude and Mach number. The effect of nozzle on performance is also considered in the model and it gave a basis for performance analysis and design of pulse detonation engine.

关 键 词：脉冲爆震发动机 飞行品质 计算 模型 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]