高超声速飞行器常规螺线管磁控热防护系统可行性分析

摘要

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.%针对高超声速飞行器鼻锥热防护，构造常规圆柱螺线管磁控热防护系统的物理模型。采用低磁雷诺数磁流体数学模型，对外加磁场作用下的高超声速鼻锥流场进行数值模拟；分析常规螺线管磁控热防护系统的有效磁感应强度范围；给出满足导线电流密度工作极限的螺线管几何参数的要求。研究表明，由于磁控“饱和现象”及导线电流密度的限制，系统可行工作范围为驻点磁感应强度B0∈[0.05 T，0.20 T]；B0＝0.20 T时，驻点热流密度和总热流分别降低了31.3％和56.6％，热防护效果良好；但磁控系统导线质量仍然较重，应采用可缩短与驻点间距离的异形螺旋管或超导磁铁等替代方法来满足工程防热需求。