| RDX/AMMO-BAMO推进剂燃烧模型 |
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| 引用本文： | 李苗苗,汪越,郭效德,宋洪昌,李凤生.RDX/AMMO-BAMO推进剂燃烧模型[J].固体火箭技术,2009,32(6). |
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| 作者姓名： | 李苗苗 汪越 郭效德 宋洪昌 李凤生 |
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| 作者单位： | 1. 南京理工大学,国家特种超细粉体工程技术研究中心,南京,210094
2. 湖北航天化学技术研究所,襄樊,441003 |
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| 基金项目： | 国家"973"基金资助课题 |
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| 摘 要： | 以详细的气相基元反应机理为基础,建立了RDX和RDX/AMMO-BAMO(80∶20)推进剂的一维、稳态燃烧模型.计算了0.1～10 MPa压强下RDX和RDX/AMMO-BAMO推进剂的燃速、燃烧波结构、气相热反馈等燃烧特性参数.预估的燃速值与实验值吻合得很好,相对误差都在10%以内.计算结果显示,20%AMMO-BAMO共聚物的加入,降低了RDX推进剂的燃速,降低幅度约为42%.
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| 关 键 词： | 固体推进剂 燃烧模型 |
Modeling of RDX/AMMO-BAMO pseudo-propellant combustion |
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| LI Miao-miao,WANG yue,GUO Xiao-de,SONG Hong-chang,LI Feng-sheng.Modeling of RDX/AMMO-BAMO pseudo-propellant combustion[J].Journal of Solid Rocket Technology,2009,32(6). |
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| Authors: | LI Miao-miao WANG yue GUO Xiao-de SONG Hong-chang LI Feng-sheng |
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| Institution: | LI Miao-miao1,WANG yue2,GUO Xiao-de1,SONG Hong-chang1,LI Feng-sheng1(1.National Special Superfine Powder Engineering Center,Nanjing Univ.of Science and Technology,Nanjing 210094,China,2.Hubei Inst.of Aerospace Chemotechnology,Xiangfan 441003,China) |
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| Abstract: | The steady-state combustion of RDX and mixtures of RDX/AMMO-BAMO characteristics include the burning rate, pressure exponent, combustion wave structure and heat feedback were calculated. Computed combustion characteristics are in reasonable agreement with the experiment result. The calculated results show that the addition of AMMO-BAMO copolymer result in a decrease of the burning rate by 42%. |
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| Keywords: | RDX AMMO BAMO solid propellant combustion mode RDX AMMO BAMO |
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