摘要
针对固定几何形状冲压发动机超音速进气道在高马赫数状态下工作时品质降低问题,提出从补燃室或燃气发生器引入燃气喷入外压缩面和喉道,实现对进气道外压缩波系和有效喉道面积进行调节的方案。采用数值方法计算了不同马赫数工况下,喷射条件变化时进气道的性能参数。根据流场数值计算结果,采用B样条理论建立了燃气射流控制可调进气道数学模型,利用此数学模型可确定进气道外部斜激波位置以及总压恢复系数随工作马赫数和射流喷射条件的变化关系。结果表明,随着射流入射角度和射流流量增大,射流调节能力呈增强趋势。
For solving the problem of performance decreasing for fixed-geometry inlet of solid rocket ramjet working at high mach number,a jet controll inlet scheme was proposed to bring the gas from second-combustion chamber to external compression face and throat so as to adjust the external shocks and effective throat area.By using the numerical method,the performance parameters were obtained with changing jet conditions at different mach number.According to numerical results,a jet control mathematical model was established according to B-spline.This model could be used to determine the position of the external shocks and the TPR of the inlet with the variation of mach number and jet conditions.The results show that the adjusting ability of the jet is enhanced along with the increase of jet mass rate and jet angle.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第6期641-645,共5页
Journal of Solid Rocket Technology
关键词
可调进气道
燃气射流控制
数值模拟
数学模型
variable inlet
gas jet controll
numerical simulation
mathematical model
