摘要
本文叙述固体火箭喷管扩张段硅基内衬烧蚀和温度场的耦合计算方法.烧蚀采用非定常的液体层烧蚀模型;温度场计算采用圆柱坐标系下的一维径向瞬态导热模型,考虑材料在高温下形成的炭化层和热解层,而由烧蚀产生的边界移动问题用坐标变换的方法处理.利用烧蚀和导热计算方程组中二者的结合部,通过充分耦合,获得了更准确的预示计算结果.
This paper describes a coupling calculation method for ablation and temperature field on SPRM nozzle with silica-phenolics. A unsteady liquid layer model is considered for calculation.The temperature field is treated as one dimensional in a cylindric coordinates,transient heat-conduction problem. By using coordinates transformation, the physical plane with moving boundary resulting from ablation is turned into the rectangular coordinates calculating plane with fixed boundary.Finally, a more accurate calculation result is obtative with a full consideration of the coupling term in both ablative equation and heat-conduction equation.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1991年第3期19-25,共7页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
喷管
烧蚀
温度分布
Rocket engine nozzle, Ablation,Temperature distribution, Coupledmode, Calculation
