C/C喉衬稳态烧蚀的工程计算  

Engineering Calculation of C/C Throat Insert Ablation

作　　者：方丁酉[1] 夏智勋[1] 姜春林[1] 

机构地区：[1]国防科技大学航天技术系,长沙410073

出　　处：《固体火箭技术》2000年第2期24-27,共4页Journal of Solid Rocket Technology

摘　　要：根据固体火箭发动机燃烧中氧化性组分扩散控制喷管喉衬烧蚀和 A12 O3 沉积对喉衬的保护 ,提出 C/C喉衬稳态烧蚀的工程计算方法。 3个实验发动机的烧蚀预示结果与实测结果吻合 。Based on the diffusion rate of oxidizing species to nozzle surface and Al 2O 3 deposition on the nozzle surface,during firing tests of the solid rocket motors,an engineering method of ablative calculation for C/C throat insert is presented.The calculated results agree with the experimental results of three experimental motors.It shows that the calculation method has a better precision.

关 键 词：固体推进剂火箭发动机 喷管喉部 烧蚀 工程计算 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]