高空火箭发动机羽流特性的计算机预估  

COMPUTATIONAL PREDICTION FOR HIGH ALTITUDE PLUME CHARACTERISTICS OF ROCKET MOTOR

作　　者：刘青云[1] 崔继嵩 张平[1] 

机构地区：[1]北京理工大学

出　　处：《推进技术》1993年第6期25-31,共7页Journal of Propulsion Technology

摘　　要：根据真空膨胀模型、均匀激波层理论以及牛顿薄激波层理论建立了一种气体向真空膨胀的简单分析模型,给出了近似解,并编制了计算机程序。该程序可用于预估高度在100km到2000km范围内的火箭羽流的边界、羽流核心区的速度以及密度分布和羽流的特征参数。计算结果与同类文献的可比结果比较基本一致。A simplified analytical model for gas expansion into vacuum is constructed in this paper. According to the model homogeneous-shock-layer theory and Newtonian thin-shock-layer theory, the approximate solutions are given and a computer code is programmed. This code can be used to calculate the boundary of a plume, the velocity and density variations in the core region of the plume flowfield, and the characteristic parameters of the plume for the rocket motors at the altitudes from 100km to 2000km. It is shown that the computational results have a basical a-greement with the comparable ones from relative references.

关 键 词：火箭发动机 火箭排气 计算机模拟 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]