摘要
通过建立固体火箭发动机点火瞬态数学模型,对某大型分段式固体火箭发动机工作初期小火箭式点火装置的火焰喷射方式、分段对接部位火焰传播过程以及前后翼燃面的传播过程等进行数值计算研究。计算结果表明,发动机点火过程中,燃烧室内的流动顺畅,没有出现压强异常振荡现象,点火初期的火焰冲击对分段对接部位的绝热结构影响很小,但整个后翼槽药面全部点燃用时在整个火焰传播期用时占比过大。数值计算结果与全尺寸发动机地面热试车结果对比表明,数值计算点火平衡压强、压强爬升时间以及升压速率与地面热试车结果吻合性好。
In order to investigate the flame jet of micro-rocket igniter, flame spreading in the segmented gap and development of the burning surface in the fwd-finocyl and aft-finocyl, a numerical analysis based on ignition transient model was established in a large segmented SRM.The numerical results indicate that the inner flow field of chamber is stable, and there is no abnormal pressure oscillation during the ignition transient, the influence of initial stage flame shock on the insulation of segmented structure is slight, but the time of all grain surface burning of aft-finoeyl is too long in the whole time of flame spreading.Compared with the ground ex- periment results of the full-scale segmented SRM, the simulation results show that ignition equilibrium pressure, time of ignition pressurization and pressure gradient are in good agreement with experiment results.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2017年第2期141-145,共5页
Journal of Solid Rocket Technology
