不同压力工况下AP-HTPB推进剂微尺度燃烧的数值模拟

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英文篇名：Numerical Simulation of Micro-Scale Combustion of AP/HTPB Propellant Under Various Pressure Conditions 作者：陈王琦 ; 余永刚 英文作者：CHEN Wangqi;YU Yonggang;School of Energy and Power Engineering,Nanjing University of Science and Technology; 关键词：AP/HTPB固体推进剂 ; 燃烧模型 ; 含能颗粒 ; 数值模拟 ; 燃速 英文关键词：ammonium perchlorate/hydroxyl-terminated polybutadiene solid propellant;;combustion modeling;;energetic particles;;numerical simulation;;burning rate 中文刊名：CUXI 英文刊名：Journal of Ordnance Equipment Engineering 机构：南京理工大学能源动力工程学院; 出版日期：2019-03-25 出版单位：兵器装备工程学报 年：2019 期：v.40;No.248 基金：国家自然科学基金项目(51176076) 语种：中文; 页：CUXI201903049 页数：6 CN：03 ISSN：50-1213/TJ 分类号：247-252

摘要

针对高氯酸铵/端羟基聚丁二烯稳态燃烧,建立了简化的二维三明治模型进行数值模拟,研究了不同压力工况对其燃烧特性的影响。计算结果表明:随着压力从0. 3 MPa增大到7. 2 MPa,总体火焰结构依次经历了预混火焰、预混扩散火焰和扩散-火焰的变化,并且随着压力的增加,整个燃面温度不断升高,表明气相对固相的热反馈加强,整个推进剂的燃烧速度快速增加。
        Ammonium perchlorate hydroxyl-terminated polybutadiene composite solid propellant is commonly used as solid fuel for rockets. The engine performance is highly relevant to the characteristics of AP/HTPB composite propellant,and pressure is one of the dominant factor of propellant combustion and influences their burning characteristics. To study the steady combustion process under various pressure conditions,a simplified 2 D periodic sandwich unit was established. Results show that the flame structure changes with the pressure ranges from 0. 3 MPa to 7. 2 MPa,moreover,the temperature of the interface between solid and gas increases as the pressure is increasing,which means the higher of the pressure,the bigger thermal feedback from gas phase to solid phase,the burning rate is soar as the higher pressure.

引文

[1]FITZGERALD R P,BREWSTER M Q.Flame and surface structure of laminate propellants with coarse and fine ammonium perchlorate[J].Combustion&Flame,2004,136(3):313-326.
    [2]GADUPARTHI T,PANDEY M,CHAKRAVARTHY S R.Gas phase flame structure of solid propellant sandwiches with different reaction mechanisms[J].Combustion&Flame,2016,164:10-21.
    [3]PRICE E W,SAMBAMURTHI J K,SIGMAN R K,et al.Combustion of ammonium perchlorate-polymer sandwiches[J].Combustion&Flame,1986,63(3):381-413.
    [4]TAEHOKIM I C,PARK Y K.A study on the low pressure burning characteristics of the composite propellants[C]Joint Propulsion Conference and Exhibit.2013.
    [5]RAMAKRISHNA P A,PAUL P J,MUKUNDA H S,et al.Combustion of sandwich propellant at low pressures[J].Proceedings of the Combustion Institute,2005,30(2):2097-2104.
    [6]窦燕蒙,罗运军,李国平,等.储氢合金/AP/HTPB推进剂燃烧性能研究[J].推进技术,2013,34(2):285-288.
    [7]JACKSON T L.Modeling of Heterogeneous Propellant Combustion:A Survey[J].Aiaa Journal,2012,50(50):993-1006.
    [8]徐冠宇,刘佩进,金秉宁.振荡环境下多层三明治模型火焰波动特性研究[J].固体火箭技术,2018(2).
    [9]孙迪,刘佩进,刘林林,等.基于BDP模型的AP/HTPB推进剂燃速参数敏感性分析[J].固体火箭技术,2015(2):245-250.
    [10]CAO Y J,YU Y G,YE R.Numerical analysis of AP/HTPBcomposite propellant combustion under rapid depressurization[J].Applied Thermal Engineering,2015,75:145-153.
    [11]HEGAB A,JACKSON T L,BUCKMASTER J,et al.Nonsteady burning of periodic sandwich propellants with complete coupling between the solid and gas phases[J].Combustion&Flame,2001,125(1):1055-1070.
    [12]MICCIO F.Numerical modeling of composite propellant combustion[J].Symposiumon Combustion,1998,27(2):2387-2395.
    [13]谢虓,祝青,肖春,等.石蜡/HTPB复合流体黏温特性测试[J].兵器装备工程学报,2017,38(6):138-141.
    [14]CHORPENING B T,KNOTT G M,BREWSTER M Q.Flame structure and burning rate of ammonium perchlorate/hydroxyl-terminated polybutadiene propellant sandwiches[J].Proceedings of the Combustion Institute,2000,28(1):847-851.