摘要
通过研究AP/HTPB推进剂燃烧模型可以对其各组分的消耗情况,以及推进剂燃烧时的化学反应机理有更清晰的认识,为解决燃速调节和配方设计问题提供支持。通过建立一维三相燃烧模型,分别采用Hawkins的1步反应机理以及Jeppson的8步反应机理进行模拟计算,得到了推进剂燃烧表面凝聚相区的温度和组分分布,发现采用Jeppson的8步反应机理,可得到凝聚相区域的组分演化大致要经历分解反应、分解产物与组分反应以及分解产物间发生反应三个反应阶段;而对于Hawkins的1步反应机理,分析了不同的质量流量、压强、推进剂配方中的Al粉含量对凝聚相区燃烧反应的影响,发现Al粉含量对反应速率影响显著。
By studying the AP/HTPB propellant combustion model,it is possible to have a clearer understanding of the con sumption of each component and the chemical reaction mechanism of the propellant during combustion,and to provide support for solving the problem of burning rate regulation and formulation design.In this paper,a one dimensional three phase combustion model was established,and the one step reaction mechanism of Hawkins and the eight step reaction mechanism of Jeppson were used to simulate the calculation.The temperature and composition distribution of the cohesive phase of the propellant combustion surface were obtained.It was found that Jeppson 8 was used.The reaction mechanism of the step can obtain three reaction stages in which the composition evolution of the condensed phase region undergoes decomposition reaction,decomposition product and component reac tion,and reaction between decomposition products.For the one step reaction mechanism of Hawkins,different mass flows are ana lyzed.The influence of the Al powder content in the pressure and propellant formulations on the combustion of the condensed phase zone showed that the Al powder content had a significant effect on the reaction rate.
作者
王英男
徐博言
王革
李冬冬
陈林君
WANG Yingnan;XU Boyan;WANG Ge;LI Dongdong;CHEN Linjun(College of Aerospace and Architectural Engineering,Harbin Engineering University,Harbin 150001,China;College of Energy and Power Engineering,Beihang University,Beijing 100191,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第1期29-37,共9页
Journal of Solid Rocket Technology
