嵌入多孔球形颗粒的超高燃速推进剂内弹道研究  

Interior Ballistics of Ultra-High Burning Rate Propellant Embedded with Porous Spherical Particles

作　　者：李永盛 蔺向阳[2] 李世鹏[3] 易黎明 LI Yong-sheng;LIN Xiang-yang;LI Shi-peng;YI Li-ming(Inner-Mongolia Power Machinery Institute,Hohhot 010010,China;College of Chemistry and Engineering,Nanjing University of Technology,Nanjing 210094,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]内蒙动力机械研究所,内蒙古呼和浩特010010 [2]南京理工大学化工学院,江苏南京210094 [3]北京理工大学宇航学院,北京100081

出　　处：《推进技术》2022年第11期442-446,共5页Journal of Propulsion Technology

基　　金：国防创新特区(17-863-03-ZT-005-001-01)。

摘　　要：针对现有多孔推进剂性能一致性差、燃速和密度难以调节的不足,本文提出了在复合推进剂中嵌入多孔球形颗粒以实现超高燃速的方案。介绍了多孔球形颗粒的配方和成型工艺,对其内弹道和撞击感度进行了测试。研制了不同配方的嵌入多孔球形颗粒的超高燃速推进剂,通过内弹道性能测试,研究和分析了该类推进剂的燃烧特性。研制和试验结果表明,高孔隙率、低密度的多孔球形颗粒容易产生对流燃烧,但安全性能良好;在复合推进剂中嵌入多孔球形颗粒以实现超高燃速的方案可行,能够通过调节多孔球形颗粒自身的孔隙率和能量密度以及其在推进剂中的比例,实现从常规推进剂到超高燃速推进剂密度和燃速的有效调节。In order to solve the problems of poor performance consistency and difficult adjustment of burning rate and density of monolithic porous propellant,a scheme of embedding porous spherical particles in composite propellant to achieve ultra-high burning rate is proposed.The formulation and forming process of porous spherical particles are introduced.The interior ballistics and impact sensitivity are tested.Ultra-high burning rate propellants with different formulations embedded with porous spherical particles were developed.The combustion characteristics of this kind of propellants were studied and analyzed through the internal ballistic performance test.The development and test results show that the porous spherical particles with high porosity and low density are easy to produce convective combustion,but the safety performance is good.The scheme of embedding porous spherical particles in composite propellant to achieve ultra-high burning rate is feasible.It can effectively adjust the density and burning rate from conventional propellant to ultra-high burning rate propellant by adjusting the porosity and energy density of porous spherical particles and their proportion in propellant.

关 键 词：超高燃速 多孔球形颗粒 内弹道 固体发动机 固体推进剂 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]