Numerical Analysis on Meso-combustion Characteristics of 2-D Layered Sandwich Propellant Model with Oxygenated Binder
As pure binder sandwich cannot cope withthe case of multi size distribution of oxidizer particles in real composite solid propellant, an compromise scheme of oxygenated binder sandwich based on implicit particles modeling method( homogenizing of fine oxidizer particles and binder) is introduced to represent AP (ammonium perchlorate)/HTPB (hydroxylterminated polybutadiene) bimodal propellant preliminarily. This paper constructs 2-D layered sandwich propellant meso-model comprising of two AP laminates separated by a oxygenated binder HTPB slab based on the representative AP composite solid propellant cell unit to study the influence of fineAP particles on meso-combustion law. Throughout numerical experiments, it is found that comparing to pure binder sandwich model:① the burning surface is relative flat under lower pressure or/and wider binder laminate and it allows a merged flame structure for even higher pressure or/and much larger binder widths, ②the higher of fine-AP content in binder laminate, the larger of global burning rate, and the effect of fine-AP content to burning rate is more distinct under higher pressure condition.
composite solid propellant sandwich oxygenated binder combustion numerical analysis
Zhou Zhiqing Yang Yuecheng Xia Xueli Zhou Wei
201 Staff, Xian Hi-Tech Institute, Xian, 710025, Shaanxi, China 201 Staff, Xian Hi-Tech Institute, Xian,710025,Shaanxi, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
1119-1122
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）