摘要
可燃喷管固体火箭发动机具有成本低、可靠性高等优点,可用作运载火箭助推器,本文对它的性能进行了初步探索。理论计算的内弹道曲线及喷管型面与实验结果基本一致,实验结果表明,该发动机的比冲稍低于钢喷管发动机的比冲;喷喉圆柱段的燃速比收敛段和扩散段的燃速高,燃烧规律也不相同。
The solid rocket motor with a combustible nozzle, which can be used forthe booster of launching vehicles, has advantages of low cost and high reliability. Thepreliminary exploration for its performance is presented. The theoretically calculated in-ternal ballistic curve and nozzle contour essentially agree with the experimlntal results.The results show that the specific impulse of the motor is slightly lower than that of themotor with a steel nozzle, and the burning rate of the nozzlc throat cylinder is higherthan that of the convergent and divergent sections, with the different combustion regular-ities from each other.
出处
《固体火箭技术》
EI
CAS
CSCD
1992年第1期1-6,共6页
Journal of Solid Rocket Technology
关键词
固体火箭
火箭发动机
喷管
Solid rocket engine
Rocket engine nozzle
Interior ballistic calculation
Nozzleless rocket engine Booster
