补燃循环液体火箭发动机启动过程的模块化仿真

推进技术 ›› 2001, Vol. 22 ›› Issue (2): 101-103.

补燃循环液体火箭发动机启动过程的模块化仿真

黄敏超,王新建,王楠

国防科技大学航天与材料工程学院!湖南长沙410073;国防科技大学航天与材料工程学院!湖南长沙410073;国防科技大学航天与材料工程学院!湖南长沙410073

发布日期:2021-08-15

Modular simulation on the start process for staged combustion cycle liquid propellant rocket engine

Inst,of Aerospace and Material Engineering,National Univ. of Defence Technology, Changsha 410073,China;Inst,of Aerospace and Material Engineering,National Univ. of Defence Technology, Changsha 410073,China;Inst,of Aerospace and Material Engineering,National Univ. of Defence Technology, Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 通过模块化编程 ,建立了新一代高性能补燃发动机启动过程的部件模型。虽然采用的是集中参数方法 ,但同时考虑了液体的惯性、粘性和压缩性 ,所以建立的常微分方程组能在一定程度上反映发动机工作过程的分布特性。

关键词: 液体推进剂火箭发动机;起动;模块化设计;仿真

Abstract: The dynamic models of engine parts in a new high-performance staged combustion cycle liquid propellant rocket through the module codified were built.The lumped parameters method was used, the inertia, viscosity and compressibility of liquid were considered at the same time. However, the ordinary differential equation set can generally reflect the distributed characteristic of the flowing process in the engine.

Key words: Liquid propellant rocket engine;Starting;Modularized design;Emulation

黄敏超,王新建,王楠. 补燃循环液体火箭发动机启动过程的模块化仿真[J]. 推进技术, 2001, 22(2): 101-103.