摘要
分析了喷喉烧蚀计算的各种方法，并用实例比较了各种计算方法的优劣。理论分析和计算结果表明，用平均膨胀比与初始膨胀比计算出的理论真空比冲之比，或在平均膨胀比与初始膨胀比下按一维两相平衡流计算出的真空比冲之比来计算喷喉烧蚀效率较好。
The calculation methods of throat erosion are analyzed and compared by example.It shows that the ratio of theoretic vacuum specific impulse with average nozzle expansive ratio to that with initial nozzle expansive ratio is preferable for the throat erosive efficiency computation.Moreover,the ratio of one dimension two phase equilibrium flow vacuum specific impulse with average nozzle expansive ratio to that with initial nozzle expansive ratio is also preferable for the computation
出处
《推进技术》
EI
CAS
CSCD
北大核心
1998年第5期38-42,共5页
Journal of Propulsion Technology
基金
国防科技重点实验室基金
关键词
固体推进剂
火箭发动机
性能预测
喷管
烧蚀
Solid propellant rocket engine,Performance prediction,Nozzle ablation
