数值模拟液体火箭尾焰流场和红外辐射特性  

Numeric Simulation of Flow Field and Infrared Radiation of Liquid Rocket

作　　者：刘尊洋[1] 汪亚夫[1] 邵立[1] 孙晓泉[1] 

机构地区：[1]解放军电子工程学院脉冲功率激光技术国家重点实验室,合肥230037

出　　处：《弹箭与制导学报》2013年第4期119-122,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家重点实验室基金(10J006)资助

摘　　要：为了研究液体火箭尾焰的流场及红外辐射特性,建立了一个相对完整的计算模型,分别使用FLUENT软件和有限体积法(FVM)计算尾焰流场和红外辐射特性,然后使用通用大气辐射传输(CART)软件计算大气透过率,并验证了模型的正确性。利用此模型研究了典型条件下火箭尾焰的流场及红外辐射特性。结果表明,尾焰在垂直于轴线方向的辐射强度最大,并集中在2.5’3.0μm和4.2’4.7μm两个波段,在10km高空大气对2.6’2.9μm和4.1’4.6μm两个波段的辐射吸收较强。Aimed at studying the flow field and infrared radiation of a liquid rocket＇ s exhaust plume, a relatively complete calculation model was founded. The FLUENT and the finite volume method （FVM） were adopted to calculate the flow field and the infrared radiation of exhaust plume. Then, the combined atmospheric radiative transfer （CART） software was employed to calculate the transmittance of the atmosphere. The correctness of this model was testified. On the basis of this model, several characters of the rocket exhaust plume flow field and infrared radiation were studied. The results show that the radiation in the vertical direction is greater than other direction, and the band 2.5 -3.0μm and 4.2 ,-4.7μm are the dominate radiation band. At the altitude of 10km, the atmosphere absorbs greatly in the band 2.6 -2.9μm and 4.1 -4.6μm.

关 键 词：液体火箭 尾焰 流场 红外辐射 有限体积法 

分 类 号：TN215[电子电信—物理电子学]