MHD加速器模式磁控进气道的优化设计  

Optimization of Accelerator Mode MHD Controlled Inlet

作　　者：郑小梅[1] 吕浩宇[1] 徐大军[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空学报》2010年第2期223-230,共8页Acta Aeronautica et Astronautica Sinica

摘　　要：为提高超燃冲压发动机进气道在非设计状态下的性能,对磁控进气道进行了研究。采用二维磁流体动力学(MHD)模型对加速器模式的磁控进气道进行了数值模拟和参数优化。分析了电磁作用使空气流率增加的原因,选取了一组优化的设计参数进行数值模拟,确定了磁流体关键参数与进气道主要性能参数的匹配原则。分析表明磁场的大小和方向以及电磁作用的位置对进气道性能有重要影响;唇口附近及上方的电磁作用对增加空气流率起到了关键的作用,磁流体加速器可以显著增加进气道的空气捕获率和压缩比,但由于不可逆效应总压恢复系数会减小。研究结果表明,当飞行马赫数小于设计马赫数时加速器模式的磁控进气道可以提高进气道的性能。a magnetohydrodynamic （MHD）-controlled inlet is adopted in order to improve the scramjet inlet performance in off-design conditions. The two-dimensional MHD controlled inlet in the accelerator mode is numerically simulated,and the influence of some key parameters on the performance of the inlet is analyzed. The results show that the magnitude and direction of magnetic induction and the position of the MHD interaction region have important influence on the performance of the inlet. The analysis shows that the increase of mass capture and pressure is mainly due to the MHD interaction near and up the cowl lip region. A considerable improvement of the inlet air mass capture and pressure rise is obtained while the loss of total pressure is limited to a reasonable extent. It can be concluded that the accelerator mode MHD-controlled inlet can improve the inlet performance when the flight Mach number is lower than the design value.

关 键 词：超燃冲压发动机 磁流体动力学 磁控进气道 磁流体加速器 

分 类 号：V235.211[航空宇航科学与技术—航空宇航推进理论与工程]