国防科技大学学报2016，Vol.38Issue(2)：25-30,6.DOI:10.11887/j.cn.201602005
高超声速飞行器常规螺线管磁控热防护系统可行性分析
Feasibility analysis of solenoid-based magnetohydrodynamic heat shield system for hypersonic vehicles
摘要
Abstract
In order to analyze the feasibility of MHD (magnetohydrodynamic)heat shield system for the nose cone of hypersonic vehicles,a normal columned solenoid-based MHD thermal protection system model was built.By using the low magneto-Reynolds MHD model,a set of numerical simulations for hypersonic nose cone with external magnetic field were performed;the feasible range of magnetic induction intensity of normal solenoid-based MHD heat shield system was obtained;the requirements of the solenoid's geometric parameters were drawn to meet the limit of coil current density.Results show that,considering the saturation effect and the current density limit existing in the process of MHD thermal protection,the system works better when the stagnation magnetic induction intensity B0 is in the range of 0.05 ~0.20 T.When B0 is equal to 0.20 T,the stagnation heat flux density and total wall heat flux is reduced by 31.3% and 56.6% respectively,indicating the effectiveness of thermal protection.However,the required coil mass is so heavy that its structure must be optimized to be actually utilized.关键词
磁流体控制/高超声速飞行器/热防护/螺线管磁铁Key words
magnetohydrodynamic flow control/hypersonic vehicle/thermal protection/solenoid magnet分类
航空航天引用本文复制引用
李开,刘伟强..高超声速飞行器常规螺线管磁控热防护系统可行性分析[J].国防科技大学学报,2016,38(2):25-30,6.基金项目
国家自然科学基金资助项目（90916018）；湖南省自然科学基金资助项目 （）
