摘要
本文阐述了利用透明窗发动机——高速摄影装置研究氧化剂粒度对复合固体推进剂侵蚀燃烧影响的方法。对基本配方相同,只是氧化剂粒度不同的三种复合固体推进剂进行了实验研究。经过测试、分析和计算,得出了不同氧化剂粒度推进剂的侵蚀效应对气流速度和压力的关系式,进而得出了氧化剂粒度的大小对复合固体推进剂侵蚀效应的影响关系。
This paper deiinenated the method to study the effects of oxidizer particle site on erosive burning of composite sclid propellants by transparent plexiglass window motor-high-speed motion picture equipment. For three composite solid probellants whichthe fundamental formulation parameters are identical. but the oxidizer partical size ore different complited experimental study. By determination, analysis and colculation, derive d the relations of erosive burning sensitivity of composite propellants contained different oxidizer particle size versus crossflow velocity and pressure, as a conseguence, derived the relations of the erosive burning sensitivity of composite solid propellants.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1990年第1期105-112,共8页
Journal of Astronautics
关键词
固体推进剂
侵蚀
燃烧
氧化剂
粒度
Composite solid propellant, Solid rocket, Engine erosive burning,Solid rocket oxidizer.
