后燃对火箭发动机羽流红外特性的影响  

Influence of afterburning on infrared signature of rocket motor exhaust plume

作　　者：王伟臣[1] 魏志军[1] 张峤[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2010年第11期2612-2618,共7页Journal of Aerospace Power

基　　金：预研基金项目(9140A28020409BQ0150)

摘　　要：为研究火箭发动机后燃羽流近场的红外辐射特性,建立了羽流红外传输的计算模型,通过在能量方程中引入辐射源项,实现了流场计算与辐射传输的耦合求解.计算中考虑了10种组分,使用有限速率化学反应模型对羽流后燃现象进行计算,分别使用有限体积法和离散坐标法求解羽流流场和辐射传输方程,得到了羽流红外辐射强度在115μm范围内随波长变化的曲线及辐射强度在近场内的分布云图,与试验数据符合较好.在羽流近场内能够捕捉到辐射特性随流场物性变化的情况,表明耦合求解能提高辐射计算精度.随着来流马赫数和飞行高度的增加,后燃引起的羽流红外辐射强度的增量均变小.To study the infrared signature of rocket motor afterburning exhaust plume,the calculation model for infrared radiation（IR） transfer of rocket motor was built.The radiation source item was induced to energy equation,and the plume flow field and radiation transfer was calculated together.Finite rate chemistry reaction model was used to simulate 10 species afterburning exhaust plume;finite volume method and discrete ordinates method were separately used to solve the plume flow field and the radiation transfer equation.The spectral radiation intensity from 1 μm to 15 μm and radiation intensity contours were obtained,both of which agreed well with the experimental data from articles.The results show that the IR characteristics in the near plume field can be captured dependently from the physical characteristics of flow field,indicating that the coupled solution can increase the calculation resolution.With the increase of Mach number and flight height,the radiation intensity increment of exhaust plume caused by afterburning effect declines.

关 键 词：火箭发动机 后燃羽流 红外辐射 耦合求解 有限速率化学反应模型 有限体积法 离散坐标法 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]