喷喉烧蚀损失计算

推进技术 ›› 1998, Vol. 19 ›› Issue (5): 38-42.

喷喉烧蚀损失计算

方丁酉,夏智勋,张为华,张炜

长沙国防科技大学航天技术系;长沙国防科技大学航天技术系;长沙国防科技大学航天技术系;长沙国防科技大学航天技术系

发布日期:2021-08-15
基金资助:
国防科技重点实验室基金

THROAT EROSIVE LOSS COMPUTATION

Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defence Technology,Changsha,410073

Published:2021-08-15

摘要/Abstract

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。

关键词: 固体推进剂火箭发动机;性能预测;喷管烧蚀

Abstract: 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

Key words: Solid propellant rocket engine;Performance prediction;Nozzle ablation

方丁酉,夏智勋,张为华,张炜. 喷喉烧蚀损失计算[J]. 推进技术, 1998, 19(5): 38-42.