关键词: 火箭发动机;高空;火箭排气;计算机模拟

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.

Key words: Rocket engine;High altitude;Rocket exhaust;Computeried simulation