低功率氮氢混合物电弧加热发动机模拟研究  

Simulation Analysis on the Low-Power Nitrogen/Hydrogen Mixtures Arcjets

作　　者：魏延明[1] 耿金越[1] 何青松[2] 王海兴[2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]北京航空航天大学,北京100191

出　　处：《空间控制技术与应用》2015年第1期1-8,共8页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(11275021;11072020)

摘　　要：对低功率电弧加热发动机内的传热与流动过程进行了数值模拟研究,分别采用氮氢混合物模拟氨和肼作推进剂,计算获得了不同入口总压和弧电流的多种工况条件下发动机内温度和速度分布.结果表明,随着弧电流的增加,发动机出口处的温度、速度和比冲也随之增加;随着入口总压的增加,工作气体流量增加,发动机喷管出口处轴向速度增加.对NASA 1 k W级电弧加热发动机采用氮氢模拟肼作推进剂进行了数值模拟,模拟结果与文献报道的实验结果大体相符.A modeling analysis is given to investigate the plasma flow and heat transfer of low-power（ kW class） arc-heated thrusters（ arcjets）. The hydrogen / nitrogen mixtures are chosen as the propellants to simulate decomposed ammonia and hydrazine. The temperature and velocity distributions in the arcjets with different inlet pressures and arc currents are presented. The modeling results show that with the increase of the arc current,the temperature along the axis increases,and the velocity at the exit plane and the specific impulse also increase. With the increase of inlet pressure,the mass flow rate and velocity at the center of nozzle exit also increase. A numerical simulation is carried out for the NASA 1-kW class arcjet thruster,and the results are almost consistent with the available experimental data.

关 键 词：电弧加热发动机 流动与传热 数值模拟 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]