摘要
以高能固体推进剂热分解特性和燃烧模型的研究成果为基础,建立了由化学结构参数计算NEPE推进剂的燃速和压强指数的公式,计算了氧化剂组分含量和粒度对燃烧性能的影响。经验证,计算结果与实测燃速值的偏差全部在±20%以内,其中80%的偏差在±10%以内。这说明所建立的模型基本合理,编制的NEPE类推进剂燃速计算程序基本可行。
On the basis of an analysis and investigation on thermal behavior and combustion model of the high energy solid propellant, considering the combustion characteristics of NEPE propellant, the burning rate and pressure exponent equation of NEPE was derived based on the chemical structure, In the light of this model, a computer program is compiled to compute the burning rate and its pressure exponent. The effects of oxidizer（ AP, RDX and HMX） content and particle size on the propellants combustion characteristics are studied systematically. The results show that most of calculated results are within the ten percent relative error range of the experimental values. It proves that the model and the program are reasonable.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2008年第4期502-507,共6页
Journal of Propulsion Technology
基金
国家“九七三”项目(61337020302)
关键词
固体推进剂
高能推进剂
燃烧模型+
燃烧性能
计算方法
燃速
Solid propellant
High energy propellant
Combustion model^＋
Combustion performance
Calculation method
Burning rate
