吸气式激光推进飞行器发动机特性分析  

Performance analysis of laser propulsion engine with airbreathing mode for lightcraft

作　　者：李小康[1] 张育林 程谋森[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]东风航天中心,甘肃酒泉732750

出　　处：《推进技术》2007年第5期513-516,共4页Journal of Propulsion Technology

基　　金：国家"九七三"项目(61328)

摘　　要：介绍了吸气式脉冲激光爆轰推进的环聚焦构形飞行器概念,建立了进气道流动模型;利用Chapman-Jouguet爆轰理论和Sedov自相似律,建立了冲量发生与推力传递模型,给出了冲量耦合系数及等效比冲与飞行参数、激光脉冲参数之间关系的解析表达式。计算了发动机冲量耦合系数及等效比冲随飞行高度、马赫数、入射激光强度和脉宽等因素变化的曲线,结果可为相关构形飞行器的弹道与激光器工作模式设计提供参考。The concept of laser-propelled flight vehicle with ring-focusing rail is introduced. A model for inlet air flow for laser pulse detonation engine is presented, and the impulse generation and thrust transfer model is developed by using Chapman-Jouguet theory and Sedov＇s self-similar solutions. The analytical expressions of the impulse coupling coefficient and effective specific impulse are given, which account for both flight and laser parameters. The curves of impulse coupling coefficient and effective specific impulse varying with flight altitude, flight Mach number, laser radiation intensity and pulse duration are given and discussed. The results can be used for the trajectory design and laser mode selection for a similar flight vehicle.

关 键 词：吸气式 激光推进 冲量耦合系数 等效比冲 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程] TN249[电子电信—物理电子学]