摘要
依据最小自由能原理,采用固体推进剂能量特性计算程序计算了标准条件下含铝锂(Al-Li)合金丁羟(HTPB)推进剂的能量性能,研究了不同Li含量的Al-Li合金粉对HTPB推进剂比冲、密度、密度比冲及特征速度的影响;并采用爆热、爆热残渣粒度分布以及活性铝含量验证了Al-2.5Li(Li质量含量为2.5%)合金粉对HTPB推进剂能量特性的影响。理论计算结果表明,采用纯Li取代Al粉,HTPB推进剂的标准理论比冲最大可增加58.11 N·s/kg;当以Al-Li合金的形式取代Al粉时,不同Li含量的Al-Li合金对HTPB推进剂配方的能量性能参数影响不同,标准理论比冲以及特征速度呈现增加的趋势,密度以及密度比冲呈现降低的趋势;当以Al-20Li合金替代Al粉时,HTPB推进剂配方的标准理论比冲最大可提高39.10 N·s/kg。爆热试验结果表明,含Al-2.5Li合金粉HTPB推进剂的爆热略高于Al粉配方,燃烧残渣粒度d 43低于对照配方;含Al-2.5Li合金粉HTPB推进剂燃烧残渣活性铝含量低于对照配方。
Based on the principle of minimum free energy,the energy properties of Al-Li alloy HTPB propellants under standard conditions were calculated by using the program for calculating the energy properties of solid propellants.The effects of Al-Li alloy powder with different Li content on specific impulse,density,density specific impulse and characteristic velocity of HTPB propellant were studied.The effects of Al-2.5Li alloy powder on the energy properties of HTPB propellant were verified by explosion heat,particle size distribution of explosion heat residue and active aluminum content.The theoretical calculation results show that the maximum theoretical specific impulse of HTPB propellant can be increased by 58.11 N·s/kg by using pure Li instead of Al powder.When Al powder is replaced by Al-Li alloy,the effect of Al-Li alloy with different Li content on the energy property parameter of HTPB propellant formulation is different;the standard theoretical specific impulse and characteristic velocity tend to increase while the density and density impulse decrease.When Al-20Li alloy is used to replace Al powder,the maximum theoretical specific impulse of HTPB propellant formulation can be increased by 39.10 N·s/kg.The experimental results show that the explosion heat of HTPB propellant containing Al-2.5Li alloy powder is slightly higher than that of aluminum powder,and the particle size d 43 of combustion residue is smaller than that of the reference formulation.The content of active aluminum in the combustion residue of HTPB propellant containing Al-2.5Li alloy powder is lower than that of the reference formulation.
作者
熊伟强
周重洋
周志豪
吴世曦
张天福
姚南
贾云娟
曾大文
郭翔
庞爱民
XIONG Weiqiang;ZHOU Chongyang;ZHOU Zhihao;WU Shixi;ZHANG Tianfu;YAO Nan;JIA Yunjuan;ZENG Dawen;GUO Xiang;PANG Aimin(Huazhong University of Science and Technology,Wuhan 430074,China;China Science and Technology on Aerospace Chemical Power Laboratory,Xiangyang 441003,China;Hubei Aerospace Chemical New Materials Co.,Ltd.,Xiangyang 441003,China;Academy of Aerospace Solid Propulsion Technology,Xi'an 710025,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2023年第5期717-723,共7页
Journal of Solid Rocket Technology
基金
国家自然科学基金(NSFC21905084
U20B2018)。
关键词
铝锂合金
丁羟推进剂
能量性能
燃烧残渣
燃烧效率
Al-Li alloy
HTPB propellant
energy property
combustion residue
combustion efficiency
作者简介
熊伟强,男,博士研究生,研究方向为复合固体推进剂;通讯作者:庞爱民,男,博士,研究方向为复合固体推进剂。
