摘要
采用网格自动生成技术,给出了考虑多种材料结构的人工脱粘层前缘附近推进剂/衬层界面较为合理的疏密平滑过渡的计算网格,对整个药柱尤其是对头部人工脱粘前缘附近进行了详细的有限元计算,得出了与实际情况接近的有限元计算模型的应力、应变场。此外,还考虑了不同模量绝热层(人工脱粘层)和衬层对人工脱粘层前缘附近推进剂/村层界面应力的影响。
By means of a grid automatic generation method,this paper presents a rational smooth network near the leading edge of the stress release flaps,in which various material structures are considered.A finite-element computer program is developed and used to analyse the whole propellant grain,especially the leading edge vicinity of stress release flaps in the grain head in detail,and the stress/strain fields which are close to the reality are available.In addition,the effects of modulus of insulation. flaps and liner on the stress distribution tri the propellant -liner interface near the leading edge of stress release flaps are investigated.
出处
《固体火箭技术》
EI
CAS
CSCD
1995年第1期24-29,共6页
Journal of Solid Rocket Technology
关键词
推进剂药柱
人工脱粘层
固体推进剂
火箭发动机
Terms Propellant grain
Structure integrity
Stress release flaps
Finite element method
Gridsmethod.