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兵工学报 ›› 2024, Vol. 45 ›› Issue (7): 2228-2239.doi: 10.12382/bgxb.2023.0546

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助推段火箭发动机喷焰红外辐射特性数值计算

张腾1, 牛青林1,*(), 柳云峰2, 高文强1, 董士奎3   

  1. 1 中北大学 机电工程学院, 山西 太原 030051
    2 内蒙古航天红峡化工有限公司, 内蒙古 呼和浩特 010076
    3 哈尔滨工业大学 工信部空天热物理重点实验室, 黑龙江 哈尔滨 150001
  • 收稿日期:2023-05-31 上线日期:2023-09-13
  • 通讯作者:
  • 基金资助:
    国家自然科学基金项目(52006203); 国家自然科学基金项目(U22B2045); 山西省回国留学人员科研资助项目(2021-113)

Numerical Calculation of Infrared Radiation Characteristics of Rocket Engine Exhaust Plume in Boost Phase

ZHANG Teng1, NIU Qinglin1,*(), LIU Yunfeng2, GAO Wenqiang1, DONG Shikui3   

  1. 1 School of Mechanical and Electrical Engineering, North University of China, Taiyuan 030051, Shanxi, China
    2 Inner Mongolia Aerospace Hongxia Chemical Co., Ltd., Huhehot 010076, Inner Mongolia, China
    3 Key Laboratory of Aerospace Thermophysics of MIIT, Harbin Institute of Technology, Harbin 150001, Heilongjiang, China
  • Received:2023-05-31 Online:2023-09-13

摘要:

助推段火箭发动机尾喷焰具有显著的红外辐射特性,成为天基红外预警系统重点关注的对象。以三组元固体发动机为研究对象,建立连续流域和过渡流域的尾喷焰反应流场计算模型,采用两级助推段质心弹道法确定飞行弹道,通过反向寻优法完备发动机型谱参数,基于等效单喷管法简化流场计算,基于窄谱带法和视在光线法计算尾喷焰的红外辐射特性。研究结果表明:复燃效应使得尾喷焰红外辐射光谱强度升高约20倍,谱带积分强度升高约10倍;尾喷焰红外光谱存在2.7μm和4.3μm的特征峰值;低空流域的光谱强度较高,且不同谱带内积分强度随高度的升高呈现出波动规律和暗区现象;助推段尾喷焰辐射强度差值高达3个量级,尤其在4.3μm较为明显。所得成果可为火箭在助推段的探测和识别提供一定的理论参考。

关键词: 火箭发动机, 三组元推进剂, 助推段, 尾喷焰, 红外辐射

Abstract:

Rocket engine exhaust plume during the boost phase is a main object captured by space-based infrared early warning systems due to its significant infrared radiation features. A tripropellant solid rocket engine is taken as the research object. The calculation models of exhaust plume flow fields in continuous and rare regimes are established.The flight trajectory is determined considering the two-stage boost phase.The design parameters of engines are evaluated by the reverse optimization method, and the calculation of flow field is simplified by using an equivalent single nozzle method.The infrared radiation characteristics of rocket exhaust plume are predicted based on the statistical narrow band method and the line-of-sight approach.The results show that the afterburning effect makes the infrared radiation intensity of the plume increase by about 20 times and the in-band radiance increase by about 10 times. There exist two characteristic peaks in 2.7μm and 4.3μm bands in the infrared spectrum of exhaust plume. The spectral intensity of low-altitude exhaust plume is relatively high, and the integrated intensity within different spectral bands exhibits fluctuation patterns and trough region with the increase in altitude. The difference of the in-band radiances of exhaust plume in the boost phase is up to three orders of magnitude, especially in 4.3μm band.This work can provide a theoretical reference for the detection and recognition of rocket in the boost phase.

Key words: rocket engine, tripropellant, boost phase, exhaust plume, infrared radiation

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