摘要
建立了固液火箭发动机燃烧性能计算模型,采用一维化学平衡(ODE)方法对以硝酸为氧化剂的固液火箭发动机燃烧性能进行了初步探讨。计算表明,固液火箭发动机的比冲、特征速度和燃烧温度以及燃烧产物组分等与氧化剂和燃料的配比有密切关系,氧化剂与燃料质量配比在3.75附近时,固液火箭发动机内部的温度较高,燃烧产物组分以及特征速度达到最佳状态,比冲最高。
A computation model of combustion performances for hybrid rocket motor was derived, and combustion performances for hybrid rocket motor taking nitric acid as oxidizer were preliminarily discussed by using one-dimension chemical equilibrium method （ODE）. The calculation results show that the ratio of oxidizer to fuel is closely related to specific impulse ,characteristic velocity, combustion temperature and combustion product composition of hybrid rocket motor. When mass ratio of oxidizer to fuel is near 3.75, the temperature in the hybrid rocket motor is very high, and the combustion product composition and characteristic velocity are up to the ideal state, and the specific impulse value is the biggest.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2006年第2期117-119,共3页
Journal of Solid Rocket Technology
基金
航天技术创新基金资助项目
关键词
固液火箭发动机
硝酸
燃烧性能
化学平衡方法
hybrid rocket motor
nitric acid
combustion performance
chemical equilibrium method
