提高固液混合火箭发动机燃面后退速率的方法  

Ways of Enhancing the Fuel Surface Regression Rate in Hybrid Rocket Motor

作　　者：宋志兵[1] 王振国[1] 方丁酉[1] 张炜[1] 夏智勋[1] 胡建新[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《火炸药学报》2008年第1期78-82,共5页Chinese Journal of Explosives & Propellants

摘　　要：固液混合火箭发动机的燃面后退速率低是制约该类发动机应用的主要因素。通过对大量相关文献分析,明确了固液混合火箭发动机中提高燃面后退速率的主要方法,方法一是在燃料中加添加剂,如AP粉和Al粉,方法二是使进入燃料腔的液体氧化剂产生旋流,这些方法对提高固液混合火箭发动机的性能具有重要意义。The low fuel regression rate in hybrid motor is the principal factor affecting the application of the motor. The paper summarized and analyzed the different ways to enhance the fuel regression rate of hybrid motor reported in literatures. Two main approaches to increase the burning rate of solid fuel were understood. The first one is to use additives such as AP and Al powder in the fuel compositions. The second one is to form swirl flow of liquid oxidizer injected into the fuel port. These ways are of great importance to enhance the performance of hybrid rocket motor.

关 键 词：固液混合火箭发动机 燃面后退速率 固液混合推进剂 

分 类 号：V436.2[航空宇航科学与技术—航空宇航推进理论与工程] V435.21