摘要
采用高分子阻燃材料对多孔火药表面进行包覆处理,将包覆药与常规火药混合装填在密闭爆发器内进行点火燃烧实验,通过测量爆发器内火药燃气的压力变化规律来研究包覆药的延迟燃烧特性。建立了一个包含火药燃气与包覆层之间传热传质过程的火药延迟燃烧数学模型,并对包覆药的延迟燃烧过程进行了数值计算。结果表明,包覆药的延迟燃烧时间随着燃气压力的升高而缩短,调整阻燃剂组分及包覆厚度可以改善包覆药的延迟燃烧时间;计算的爆发器内燃气压力-时间曲线与实验结果具有较好的一致性,说明提出的数学模型能够描述包覆药的延迟燃烧过程。
The surfaces of muhiperforated propellant particles were coated with high molecular materials in different thickness. The deterrent coated propellants and traditional propellants were mixed and charged in a closed ves sel and ignited to test the combustion retardation of deterrent coated propellants by recording the pressure time profiles of combustion gases. A numerical model which included the heat and mass transfer between the combus- tion gases and coating layer to describe the combustion retardation of deterrent coated propellant was proposed. The combustion retardation of deterrent coated propellants was simulated. The results indicated that the combus- tion retardation time decreased with the increasing of pressure, and the adjustment of thickness and components of deterrent could augment the retardation time. The consistency of calculated pressure and time profiles with experimental ones indicated that the proposed model was effective for the simulation of combustion retardation of deterrent coated propellants.
出处
《火炸药学报》
EI
CAS
CSCD
北大核心
2011年第4期83-86,共4页
Chinese Journal of Explosives & Propellants
关键词
物理化学
火药
延迟燃烧
数值计算
physical chemistry
propellant
combustion retardation
numerical calculation
