摘要
为计算火箭发动机尾喷管的红外特性，建立了封闭腔-净辐射法，推导了光谱透射因子和光谱吸收因子，以及封闭腔表面辐射净热流．表面及气体温度的方程。作为验证，计算了一个充满均匀辐射性介质的轴对称柱形封闭腔的辐射换热，与文献的计算结果比较有很好的一致性；还计算了一火箭发动机尾喷管的辐射特性，分析了该喷管在中波红外波带2～6μm和长波红外波带8～14μm及全波长的有效辐射和净辐射热流。结果表明，在气体辐射作用下，火箭发动机喷管进出口平面的辐射有一定的光谱差异性；壁面有效辐射沿轴向的分布取决于壁温变化，平直段和收敛段有效辐射较强，扩张段有效辐射较弱；中波红外波带2～6μm喷管的辐射热流占全波长辐射能量的60％以上。
ha order to calculate infrared characteristics of rocket motor nozzle, the enclosed cavity-radiative heat flux method was developed. Furthermore spectral transmission and absorption factors together with the equations relating to the rediative heat flux and gas temperature were deduced. For verification, rediative heat tranfer of one axisymmetric cylindrical enclosed cavity filled up with homogeneous radiative medium was calculated. The calculation results agree well with those in reference. Moreover infrared characteristics of a rocket motor nozzl was calculated, and effective and net radiative heat flux of the nozzle in mid-wave infrared band 2 - 6 μm, long-wave infrared band 8 - 14 μm and full wave band were analyzed. The results show that spectral radiation from the inlet and outlet of the nozzle present apparent discontinuity, and the effective radiation distribution along axial direction was dependant on wall temperature. The effective rediation is very strong on the flat and convergent section of the nozzle, but weak on the divergent section. The rediative heat flux of the nozzle with mid-wave infrared band 2 - 6 μm is 60 percent of that in full wave band.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2007年第2期110-114,共5页
Journal of Solid Rocket Technology
关键词
火箭发动机
喷管
红外辐射
封闭腔
热流
rocket engine
nozzle
infrared radiation
enclosed cavity
heat flux
作者简介
张小英（1973-），女，博士，主要从事目标的红外与可见光特性的研究。E-mail：zxy1119@scut.edu.cn
