摘要
固体燃料冲压发动机性能通过进气道与导弹飞行工况关联在一起,其工作过程需考虑导弹飞行参数对发动机性能的影响。与其它冲压发动机相比,固体燃料冲压发动机一个显著特点是推进剂燃烧过程不仅与推进剂配方、发动机结构和燃烧室压强有关,还取决于燃烧室入口空气参数,因此工作过程较为复杂。在国内首次建立固体燃料冲压发动机工作过程仿真模型,并分析导弹飞行马赫数和高度对发动机性能的影响规律。
The solid fuel ramjet is related to the missile flight conditions through the inlet. Compared with other kinds of ramjet, the marked characteristic of the solid fuel ramjet is that its propellant combustion chamber process is not only concerned with the propellant composition, motor structure and combustion pressure, but also dependent on the air parameter in the combustion air inlet. Hence, the operation process is rather complex. The operation process simulation model, the first of its kind in China, was established, and the effect of the missile flight roach number and height on the motor performance was discussed.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2007年第2期10-14,共5页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(50376072)
