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

被引：0

作者：

Huang, M.-C. ^{[1
]}

Wang, X.-J. ^{[1
]}

Wang, N. ^{[1
]}

机构：

[1] Inst. of Aerospace/Material Eng., National Univ. of Defence Technology, Changsha 410073, China

来源：

| 2001年 / Journal of Propulsion Technology卷 / 22期

关键词：

Combustion - Compressibility of liquids - Differential equations - Liquid propellants - Mathematical models - Viscosity of liquids;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

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.

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