摘要
为了研究悬浮子弹药悬停装置的可行性,设计了一种侧进气涡轮驱动悬浮装置,并进行了动力学分析和试验研究。组合动量理论和叶素理论建立了悬浮装置提升力分析模型,同时建立了侧进气涡轮动力分析模型,并通过试验,得到悬浮装置提升力大小和喷嘴分布、射流入射角与质量流率对涡轮驱动性能的影响。
In order to study the feasibility of small hovering device in floating projectile, an experimental device driven by small side intake turbine （SIT） was designed, and aerodynamics analysis and experimental research was conducted. The lifting force was analyzed by combining momentum theory and the blade element theory and verified by experiment. The model of aerodynamics analysis of SIT was established by using the momentum theory, and the performance of SIT was test through experiment. Number and distribution of the jet nozzle, incident angle and mass flow rate have a great of effects on the performance of SIT. The result of this paper can provide the research of floating projectile.
出处
《四川兵工学报》
CAS
2013年第3期21-25,共5页
Journal of Sichuan Ordnance
关键词
悬浮装置
涡轮驱动
动力特性
hovering device
turbine driving
dynamics characteristics
