激光等离子体减阻技术研究进展  

Advances in Study of Laser Plasma Drag Reduction Technology

作　　者：洪延姬[1] 李倩[1] 方娟[1] 窦志国[1] 

机构地区：[1]装备指挥技术学院基础部,北京101416

出　　处：《航空学报》2010年第1期93-101,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家"973"计划;国家自然科学基金(90916015)

摘　　要：利用激光等离子体减小高超声速飞行器的气动阻力对节能和最大限度地提高飞行器性能具有重要的意义。简单概述了高超声速飞行器的军事需求及等离子体减阻技术的分类;总结了激光等离子体减阻机理的实验研究和数值模拟情况;讨论了等离子体能量、点火位置和形状等参数对减阻性能的影响,目前利用激光等离子体技术可以减小70%的波阻。针对中国的激光等离子体减阻研究工作,分析了目前国内外研究中存在的问题,提出了深入开展激光等离子体减阻机理研究等建议。Using laser plasma to reduce aerodynamic drag of hypersonic vehicle has profound significance in saving energy and improving vehicle performance. Military requirements of hypersonic vehicle and the classification of plasma drag reduction are analyzed briefly. Experimental study and numerical simulation on drag mechanism are summarized. The influences of plasma parameters such as energy,ignition location and shape on drag performance are reviewed. At present,laser plasma technology can reduce the wave drag by 70%. In view of the research status of laser plasma drag reduction in China,the weaknesses of researches both at home and abroad are analyzed first,then it is suggested that in-depth studies of laser plasma drag reduction mechanism should be carried out.

关 键 词：激光等离子体 减阻技术 波阻 高超声速 飞行器 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程] TN249[电子电信—物理电子学]