固体火箭发动机中铝粉燃烧研究概述  

A survey of study on aluminum combustion in solid rocket motors

作　　者：王宁飞[1] 苏万兴[1] 李军伟[1] 张峤[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《固体火箭技术》2011年第1期61-66,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(51076015)

摘　　要：介绍了固体火箭发动机中单个铝颗粒燃烧模型的发展与铝颗粒的燃烧特性;阐述了铝粉分布燃烧现象、分布燃烧放热与声场的耦合关系及其对发动机稳定性的增益作用;总结了惰性颗粒的阻尼理论以及在表面旋涡脱落条件下惰性颗粒对压强振荡的放大作用;提出了应从复杂流场中全面考虑铝粉燃烧对发动机的增益与阻尼作用,建立其对发动机工作稳定性影响的综合判据的观点。The development of single aluminum particle combustion models and its combustion characteristics are briefly and precisely introduced.Distributed combustion phenomenon is elaborated.The driving mechanism on combustion stability caused by the coupling between distributed combustion heat release and acoustic filed is explained.The inert particle damping effect along with the driving mechanism under vortex shedding are summarized.Based on the previous studies,future work on aluminum combustion is pointed out for further research： the driving and damping mechanism should be considered comprehensively for the purpose of modeling the integrated criteria of the aluminum combustion effect on the stability of solid rocket motors.

关 键 词：固体火箭发动机 铝颗粒 燃烧模型 分布燃烧 微粒阻尼 旋涡脱落 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]