数值模拟液体火箭尾焰流场和红外辐射特性

刘尊洋; 汪亚夫; 邵立; 孙晓泉

doi:10.15892/j.cnki.djzdxb.2013.04.027

弹箭与制导学报 >

2013 , Vol. 33 >Issue 4: 119 - 122

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2013.04.027

弹道与气动力技术

数值模拟液体火箭尾焰流场和红外辐射特性

刘尊洋 ,
汪亚夫 ,
邵立 ,
孙晓泉

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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

刘尊洋(1984-),男,江苏徐州人,博士研究生,研究方向:目标红外辐射特性计算。

收稿日期: 2012-11-20

网络出版日期: 2025-05-26

基金资助

国家重点实验室基金(10J006)

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Numeric Simulation of Flow Field and Infrared Radiation of Liquid Rocket

LIU Zunyang ,
WANG Yafu ,
SHAO Li ,
SUN Xiaoquan

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State Key Laboratory of Pulsed Power Laser Technology, Electronic Engineering Institute of PLA, Hefei 230037, China

Received date: 2012-11-20

Online published: 2025-05-26

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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。

关键词： 液体火箭; 尾焰; 流场; 红外辐射; 有限体积法

本文引用格式

刘尊洋 , 汪亚夫 , 邵立 , 孙晓泉 . 数值模拟液体火箭尾焰流场和红外辐射特性[J]. 弹箭与制导学报, 2013 , 33(4) : 119 -122 . DOI: 10.15892/j.cnki.djzdxb.2013.04.027

Abstract

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.

Key words： liquid rocket; exhaust plume; flow field; infrared radiation; finite volume method

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参考文献

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