摘要
针对采用硝酸／HTPB型推进剂的固液混合火箭发动机，采取数值方法研究了氧化剂质量通量对固体燃料热解表面退移速率及换热的影响。研究表明，固体燃料热解表面轴向平均对流换热热流密度、总热流密度以及退移速率与氧化剂质量通量的n次方近似成正比，n的值介于0．6～0．7之间；固体燃料热解表面的辐射换热热流密度近似与氧化剂质量通量成正比；随着氧化剂质量通量的增加，辐射换热占总换热量的比例逐渐增加，增加幅度逐渐减小。
The influence of mass flux of oxidizer on surface heat flux and regression rate of nitriac/HTPB propellant fuel in hybrid rocket motors was studied by means of numerical simulations method. The results show that average convective heat flux density, total heat flux density and regression rate along the axial direction are approximately proportional to the nth power of mass flux of oxidizer, and n is between 0.6 - 0.7. Radiant heat flux is proportional to mass flux of oxidizer. The ratio of radiant heat flux to total heat flux density increases but the increasing amplitude decreases gradually with higher mass flux of oxidizer.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第4期383-387,共5页
Journal of Solid Rocket Technology
关键词
混合火箭发动机
退移速率
对流换热
辐射换热
热流密度
hybrid rocket
regression rate
convective heat transfer
radiant heat transfer
heat flux density
