| 引用本文: | 高文强,孟夏莹,苏慕萍,董士奎,牛青林.火箭发动机推力与红外辐射关联特性数值分析[J].哈尔滨工业大学学报,2024,56(12):10.DOI:10.11918/202312039 |
| GAO Wenqiang,MENG Xiaying,SU Muping,DONG Shikui,NIU Qinglin.Numerical analysis of correlation characteristics between rocket motor thrust and infrared radiation signatures[J].Journal of Harbin Institute of Technology,2024,56(12):10.DOI:10.11918/202312039 |
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| 摘要: |
| 为实现火箭发动机目标分类与识别,提取发动机推力大小与尾喷焰红外辐射强度间关联关系成为必要环节。本研究以高氮高能GAP/Cl20/Al（GCA）和高氮无烟GAP/ADN/DAAOF（GAD）两种新型推进剂为研究对象,从影响发动机推力的主要型谱参数入手,基于尾喷焰内流、反应流场和红外辐射的全链路计算方法,设计燃烧室压力、喷管膨胀比和推进剂配方谱系,数值分析了发动机推力与欠膨胀尾喷焰在2.7、4.3 μm波段的辐射强度的关联性。结果表明:在燃烧室压力和喷管膨胀比变化下,发动机推力与尾喷焰辐射强度均呈对数线性关系；在同推力下,GAD较GCA推进剂的尾喷焰辐射强度偏低3~5倍；燃烧室压力和喷管膨胀比作为推力主导因素下,两种推进剂在不同来流动压下的发动机推力与红外辐射强度近似遵循统一的对数分布关系；推进剂配比变化引起的发动机推力变化较弱,在不同来流动压下两种高氮推进剂对应的尾喷焰辐射强度沿发动机推力呈现出明显的“聚集”现象,且在4.3 μm波段内的辐射强度随来流动压差异呈现出分层现象。 |
| 关键词: 固体火箭发动机 尾喷焰 推力 红外辐射 关联关系 |
| DOI：10.11918/202312039 |
| 分类号:V435；TN219 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(52006203, U22B2045)；山西省回国留学人员科研资助项目(2021-113)；山西省基础研究计划面上项目(202403021211078) |
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| Numerical analysis of correlation characteristics between rocket motor thrust and infrared radiation signatures |
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GAO Wenqiang1,MENG Xiaying2,SU Muping3,DONG Shikui4,NIU Qinglin1
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(1.School of Mechanical and Electrical Engineering, North University of China, Taiyuan 030051, China; 2.National Key Laboratory of Scattering and Radiation, Shanghai 200438, China; 3.Beijing Institute of Spacecraft System Engineering, Beijing 100094, China; 4.Key Laboratory of Aerospace Thermophysics, Ministry of Industry and Information Technology (Harbin Institute of Technology), Harbin 150001, China)
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| Abstract: |
| To achieve the classification and recognition of rocket engine targets, it becomes necessary to extract the correlation between engine thrust and the infrared radiation intensity of the rocket exhaust plume. The High-Nitrogen, High-Energy GAP/Cl20/Al (GCA) and High-Nitrogen, Smokeless GAP/ADN/DAAOF (GAD) propellants are taken as the research objects of this study. Three parameters affecting motor thrust are numerically designed including combustion chamber pressure, nozzle expansion ratio and propellant formulation. A full-link computational method consisting of the motor internal flow, reacting flow field and infrared radiation is used to predict plume infrared signatures. On basis of this method, the correlation between the in-band radiation in the 2.7 μm and 4.3 μm bands of the under-expanded plume and motor thrust is established. Results show that motor thrust is log-linearly correlated with the radiant intensity under the variations of combustion chamber pressure and nozzle expansion ratio. At the same thrust level, the radiant intensity of the exhaust plume of GAD propellant is about 3~5 times lower than that of GCA. The combustion chamber pressure and nozzle expansion ratio can also be the dominant factors for thrust. For two types of propellant motors with different ambient conditions, the thrust and plume infrared radiation intensity approximately follow a unified logarithmic distribution relationship. The change in propellant formulation causes a weaker degree of change in motor thrust. Under different ambient pressures, the plume radiation intensity distribution of both high nitrogen propellants exhibits “aggregation” as the motor thrust changes. The radiation intensity in the 4.3 μm band exhibits a layered distribution phenomenon with ambient pressure as a function. |
| Key words: solid rocket motors rocket exhaust plume thrust infrared radiation correlation relationship |
