摘要
三乙胺和硝酸-27S作为自燃推进剂可应用于火箭发动机中。对这两种自燃推进剂的燃烧性能进行了研究,应用逐步逼近法计算其热力性质,当最佳混合比为4.1,燃烧室压力为4.5MPa时,最佳海平面比冲为2786m/s。通过试验证明了三乙胺和硝酸-27S自燃技术的可行性。
C6H15N and HNO3-27S can be used as hypergolic propellant in rocket engines. The combustion capability was studied in this paper. The thermodynamic characteristics were calculated by stepwise approaching method. It was obtained that the optimal mixture ratio is 4.1 and the optimal sea level specific impulse is 2786m/s at the combustion pressure of 4.5MPa. It is proved by experiment that spontaneous combustion of C6H15N and HNO3-27S is feasible.
出处
《火箭推进》
CAS
2008年第6期50-54,共5页
Journal of Rocket Propulsion
关键词
三乙胺
硝酸-27S
自燃
混合比
C6H15N
HNO3-27S
spontaneous combustion
mixture ratio
