N_2O微推力器性能及喷管热结构分析  

N_2O micro-thruster performance and the nozzle thermo-structure analysis

作　　者：孙威[1] 方杰[1] 郑力铭[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《火箭推进》2008年第5期5-9,共5页Journal of Rocket Propulsion

摘　　要：针对采用氧化亚氮推进剂的单组元微推力器开展了比冲性能影响因素的分析,分析结果显示微推力器比冲与氧化亚氮分解效率及喷管扩张比有着密切关系。利用有限元分析法对高空及地面试验两种工况下氧化亚氮单组元微推力器喷管的结构温度场开展了数值仿真计算,并在结构温度场仿真计算的基础上进一步对地面试验用喷管的结构应力场进行了分析。初步试验表明,所设计的微喷管在地面工况下工作良好。Performance analysis for monopropellant micro-thruster using nitrous oxide （N20） propellant was conducted based on the thermodynamic computation. Preliminary results show that decomposition rate of nitrous oxide and the expansion ratio of nozzle both effected the specific impulse of the thruster. Finite element analyses on temperature field of micro-nozzle were conducted respectively under vacuum and ground conditions. Subsequently, analysis on stress field of nozzle for ground test was conducted. Results of simulation show that peak value of temperature and stress both appear at the throat section of the nozzle. Preliminary experiments under ground condition have testified the reliability of the micro-nozzle.

关 键 词：氧化亚氮 微推力器 喷管 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]