电弧放电诱导喷气流偏转数值模拟研究  

Numerical Simulation of Arc Discharge Induction Jet Flow Deflection

作　　者：陈峰[1] 张百灵[1] 张杨[1] 陈怡然 李灏[1] 

机构地区：[1]空军工程大学等离子体动力学重点实验室,陕西西安710038 [2]空军北京航空装备训练基地,北京100067

出　　处：《空军工程大学学报（自然科学版）》2012年第4期11-15,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(50776100)

摘　　要：利用电弧放电,在拉瓦尔喷管的扩散段内诱导出斜激波,使得扩散段内的超声速气流经过该斜激波后发生偏转喷出喷口,从而产生推力矢量。为获得不同条件对电弧放电诱导喷气流偏转效果的影响规律,在电弧放电与超声速流场耦合的数学模型基础上,开展喷气流马赫数1.5的条件下,电弧放电区域大小、放电温度、放电位置及喷管落压比对电弧放电诱导喷气流偏转效果影响规律的数值模拟研究,并通过初步的实验验证。实验结果表明电弧等离子体诱导激波产生喷气流偏转的方案可行,数学模型建立正确。By using the arc discharge, the oblique shock wave is inlet, making the supersonic airflow in the diffuser deflect after induced in a position of the convergent - divergent passed through the oblique shock, which produced thrust vector. On the bases of existing mathematical model of the coupling of arc discharge and supersonic flow field, numerical simulation on the factors of discharge area, temperature, position, and nozzle pressure drop those affect the flow deflection has been performed under the flow Mach number 1.5. The preliminary experimental on arc discharge inducing jet flow deflection verifies the feasibility of the plan, and the correctness of the mathematic mod-el, the result of the numerical simulation lays the theoretical basis for the subsequent experiment research.

关 键 词：电弧放电 斜激波 喷气流偏转 推力矢量 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]