摘要
采用热分析法、静态燃速测试、标准发动机燃速测试、爆热测试、高速摄像等手段,对比研究了石墨烯包覆铝粉取代相同规格铝粉后HTPB推进剂的热分解特性、燃烧特性及燃烧过程。结果表明,石墨烯包覆铝粉加入后使AP低、高温分解峰分别推迟7℃和22℃,抑制了AP分解,导致推进剂燃速有所降低。石墨烯包覆铝粉对丁羟推进剂团聚的影响具有两面性,一方面推进剂在石墨烯的导热作用下,石墨烯包覆铝粉燃烧更加充分,从而改善了这部分Al G复合物的团聚。另一方面铝颗粒的燃面滞留时间延长和熔化程度增加,燃烧产生大粒径团聚物,从而导致石墨烯对改善丁羟推进剂铝粉燃烧效率不明显。
By measuring the thermal decomposition,static burning rate,standard engine burning rate,explosion heat and high speed flame propagation,the decomposition characteristics,and combustion characteristics of HTPB propellants containing graphene coated aluminum or pristine aluminum powder have been studied.The results show that the addition of graphene coated aluminum powder delays the low and high temperature decomposition peaks of AP by 7℃and 22℃,respectively.It means graphene inhibits AP decomposition and leads to a decrease in burning rate of propellant.The effect of graphene coated aluminum powder on the ag glomeration of HTPB propellants has two aspects.On the one hand,graphene coated aluminum powder burns more completely due to increased heat conductivity by graphene,thus decreasing the agglomeration of this part of Al G composites.On the other hand,the burning surface residence time of aluminum particles is prolonged and the degree of melting is increased,resulting in agglomerates with larger particle size during combustion.It finally leads to the fact that graphene has no obvious effect on improving the combus tion efficiency of aluminum powder.
作者
周重洋
唐承志
吴世曦
顾健
李忠友
姚南
ZHOU Chongyang;TANG Chengzhi;WU Shixi;GU Jian;LI Zhongyou;YAO Nan(Science and Technology on Aerospace Chemical Power Laboratory,Xiangyang 441003,China;Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第1期38-44,共7页
Journal of Solid Rocket Technology
关键词
丁羟推进剂
石墨烯包覆铝粉
燃烧
团聚
butyl hydroxy propellant
graphene coated aluminum powder
burning
agglomeration
