Two Pulse Solid Propellant Rocket Motor Solution

被引：0

作者：

Konecny, Pavel ^{[1
]}

机构：

[1] Univ Def, 65 Kounicova, Brno, Czech Republic

来源：

INTERNATIONAL CONFERENCE ON MILITARY TECHNOLOGIES (ICMT 2015) | 2015年

关键词：

two pulse solid propellant rocket motor; divided combustion chamber; gas flow through orifice;

D O I：

暂无

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

The paper deals with mathematic simulation of dynamic processes in two pulse solid propellant rocket motor. The dynamic approach to the solution is formed by the differential equations of the mass and energy conservation laws in gas flow. Pressure and thrust courses are used for demonstration of the solution results.

引用

页码：49 / 53

页数：5