摘要
为了适应端面燃烧高装填比固体火箭发动机的点火需求,基于Al/CuO/PVDF纳米铝热含能体系,设计了3种不同粘结剂含量的含能墨水配方,采用3D墨水直写打印技术制备了3种厚度均为150μm的含能薄膜。对含能薄膜的微观形貌、热性能和燃烧性能进行了表征和测试,并对含能薄膜与固体推进剂的点火匹配特性进行了试验研究。结果表明:3种含能薄膜表观质量好、结构完整、组分分布均匀;随着配方中PVDF组分含量的增加,薄膜放热量降低,相应的薄膜燃速也降低;配方F2具有最小的点火延迟,平均值为107 ms,点火延迟与燃速不是简单的正相关关系,即最低点火延迟在合适的燃速下获得。
In order to meet the ignition requirements of end-burning solid rocket engine with high charge-weight ratio,based on the Al/CuO/PVDF nanothermite energetic system,three energetic ink formulations with different binder contents were designed,and three types of energetic thin films with a thickness of 150μm were prepared using 3D ink direct writing printing technology.The microstructure,thermal properties,and combustion performance of the energetic films were characterized and tested,and the ignition matching characteristics between the energetic films and solid propellants were experimentally studied.The results show that the three types of energetic thin films have good apparent quality,complete structure,and uniform component distribution;As the content of PVDF component in the formula increases,the heat release of the film decreases,and the corresponding burning rate of the film also decreases;Formula F2 has the smallest ignition delay,with an average value of 107 ms.The ignition delay is not simply positively correlated with the burning rate,meaning that the shortest ignition delay is obtained at an appropriate burning rate.
作者
杨智
王玉强
陈乐健
韩书锋
刘钧
杜晋龙
张志超
许建兵
YANG Zhi;WANG Yu-qiang;CHEN Le-jian;HAN Shu-feng;LIU Jun;DU Jin-ong;ZHANG Zhi-chao;XU Jian-bing(Xi’an Aerospace Propulsion Technique Institute,Xi’an,710025;School of Chemistry and Chemical Engineering,Nanjing University of Science and Technology,Nanjing,210094)
出处
《火工品》
北大核心
2025年第4期90-96,共7页
Initiators & Pyrotechnics
基金
国家自然科学基金面上项目(22275092,52372084)。
关键词
纳米铝热剂
含能薄膜
3D墨水直写打印
固体推进剂
点火匹配
Nanothermite
Energetic thin film
3D ink direct writing printing
Solid propellant
Ignition matching
