摘要
介绍了挤压式H2O2 PE固液混合火箭发动机试验系统及发动机结构特点。研究了确定固液混合火箭发动机工作点的方法,按照这种方法可以使发动机在最佳的配比附近工作,有利于提高燃烧效率和比冲。分析了固液混合火箭发动机低频耦合振荡机理和现象,利用氧化剂和燃料燃烧时滞的概念,理论上计算模拟了发动机的低频耦合振荡过程,提出了避免这种燃烧振荡的措施和方法。
A pressurization test system for H2O2PE hybrid rocket motors and the hybrid rocket motor structures are presented. The method for defining the working point of the hybrid rocket motor is discussed. The best ratio of oxidizer to fuel is adjusted for high combustion efficiency and high specific impulse.The phenomenon and the mechanism of low frequency oscillation combustion are also analyzed. With the aid of concept of fuel and oxidizer combustion delaying, theoretic calculation is done for simulating coupling oscillation between feed system and chamber pressure. Some methods are provided for avoiding and preventing low frequency oscillation in the hybrid rocket motors
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2003年第2期61-64,共4页
Journal of Solid Rocket Technology
基金
国防科技重点试验室基金(51470030101HK314)
西北工业大学博士论文创新基金(5211102 0800 G14108)。
