N_2O单组元推力器预热过程有限元分析  

Finite element analysis on preheating process of N_2O monopropellant thruster

作　　者：孙威[1] 方杰[1] 张佳[1] 李乐[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：《航空动力学报》2009年第9期2152-2156,共5页Journal of Aerospace Power

摘　　要：以正交试验设计理论为指导,应用有限元分析软件针对采用N2O推进剂的单组元微推力器的在真空环境下的预热过程开展了分析,计算结果表明加热功率及推力器外表面辐射率的大小对预热效果影响明显.所开展的微推力器壳体地面预热试验的试验结果与仿真计算结果吻合良好,验证了采用仿真方法来评估预热过程的可行性.为进一步的结构及试验设计提供了借鉴.Numerical simulation on preheating process of N2O monopropellant micro-thruster was conducted as per orthogonal experimental design theory in order to study the influence of four factors-preheating power,surface emissivity,thickness of the combustor chamber and the adiabatic stuff-on the preheating process.Results of the simulation indicate that influence of the preheating power is most remarkable among the selected four factors,which is followed by the surface emissivity.Influence of the remaining two fact...

关 键 词：氧化亚氮 单组元 预热 有限元分析 

分 类 号：V439.7[航空宇航科学与技术—航空宇航推进理论与工程]