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

关键词:  火箭发动机  高空  火箭排气  计算机模拟

Key words:  Rocket engine  High altitude  Rocket exhaust  Computeried simulation

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。

Abstract:

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.