H_2O_2-PE固液混合火箭发动机试验研究  

Experimental study on hydrogen peroxide and polyethylene hybrid rocket motors

作　　者：杜新[1] 汪亮[1] 葛李虎[2] 张宝庆[1] 张研[1] 

机构地区：[1]西北工业大学航天工程学院,西安710072 [2]中国航天科技集团公司11所,西安710100

出　　处：《固体火箭技术》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)。

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 H2O2PE 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

关 键 词：固液混合火箭发动机 试验研究 过氧化氢 PE 振荡燃烧 燃烧稳定性 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]