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.
出处
《火箭推进》
CAS
2008年第5期5-9,共5页
Journal of Rocket Propulsion
关键词
氧化亚氮
微推力器
喷管
有限元分析
nitrous oxide
micro-thruster
nozzle
finite element analysis
