固体火箭技术2025，Vol.48Issue(4)：546-553,8.DOI:10.7673/j.issn.1006-2793.2025.04.005
含铝复合固体推进剂点火燃烧特性分析
Ignition and combustion characteristics of aluminized composite solid propellant
摘要
Abstract
The performance of solid rocket motors is highly dependent on the energetic characteristics of the propellant.The com-bustion behavior of aluminized propellants significantly influences its performance.For investigating the ignition and combustion charac-teristics of solid propellants,an optical diagnostic experimental system was designed and implemented,integrating laser ignition,high-speed micr-imaging,and emission spectroscopy acquisition.This system was employed to investigate the effects of nitramine and pres-sure on the ignition delay,burning rate,combustion temperature,and aluminum agglomeration size distribution of the propellant.The ex-perimental results demonstrate that increasing the pressure can reduce the residence time of aluminum particles at the burning surface,leading to smaller agglomerate size in the condensed phase,at a pressure of 3.5 MPa,the particle size of the aggregate decreases by a-bout 120 μm.However,the introduction of nitramine decreases the burning rate and combustion temperature of the propellant,resulting in a nonlinear relationship between ignition delay time and pressure.This study by about 0.5 mm/s provides critical experiment by a-bout 35℃evidence and theoretical support for optimizing solid propellant formulations and combustion characteristics.关键词
固体推进剂/团聚/燃烧特性/光学诊断Key words
solid propellants/agglomeration/combustion behavior/optical diagnostic分类
航空航天引用本文复制引用
李强,王登可,冯亚亚,王华斌,彭晨,余西龙,谢竞生..含铝复合固体推进剂点火燃烧特性分析[J].固体火箭技术,2025,48(4):546-553,8.基金项目
内蒙古自然科学基金(2021BS05014). （2021BS05014）
