固体火箭发动机装药端面燃烧燃速畸变现象分析  

Preliminary Analysis on Cone Burning of Solid Propellant in End-Burning Rocket Motors

作　　者：许鹏[1] 梁景媛[1] 梁国柱[1] 孙再庸[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]航天科工集团六院四十一所,内蒙古呼和浩特010010

出　　处：《火炸药学报》2006年第5期32-34,62,共4页Chinese Journal of Explosives & Propellants

摘　　要：分析比较了引发固体火箭发动机装药燃速畸变的因素,如壁面附近的增塑剂、固化剂的迁移以及细氧化剂聚集等。认为固体装药燃速畸变现象产生的根本原因是壁面附近的氧化剂颗粒质量分数高于中心区域,氧化剂平均粒度低于中心区域。为验证这一理论分析,用基于粒状扩散火焰(GDF)模型得到的推进剂燃速计算公式,以氧化剂的含量和粒度为变量,计算了AP推进剂的燃速。结果表明,燃速计算值的变化趋势与理论分析结果相一致。Main factors that cause the cone burning of solid propellant were emphatically analyzed and compared, such as the concentration of fine oxidizer particle and the migration of plasticizer and curing agent at the interface near the wall. The most basic reason of causing the cone burning was that the concentration and particle size of oxidizer at the interface were different from that near the center line. To prove the analysis in theory, the burning rate of a certain AP propellant was calculated with various particle size and concentration of the oxidizer using the burning rate formula based on the granular diffusion flame （GDF） combustion model, showing a change trend in burning rate, proving a current analysis and giving a reference for avoiding the cone burning in engineering.

关 键 词：物理化学 固体火箭发动机 装药 端面燃烧 燃速畸变 燃速 

分 类 号：TQ432.2[化学工程]