摘要
为了提高N2O单组元推力器预热效果,对推力器结构做出改进,引入内加热的预热模式.在模拟真空环境下开展了内加热式推力器预热试验,以10W功率加热5 800s,使催化剂温度达到260℃(533K),证明了内加热模式的可行性及优越性.开展了内加热式N2O单组元推力器系统的三维建模,并利用有限元软件对推力器预热过程进行了分析,得到了推力器结构温度场随时间的变化情况.数值分析结果与试验数据吻合良好,验证了所用仿真模型的准确性.进一步对简化结构后的内加热式推力器在模拟太空环境下分别施加10,5,3W加热功率时的预热过程开展了数值仿真研究,结果表明:10W和5W加热功率能使催化剂在3600s内达到工作温度250℃,可为N2O单组元推力器的实际应用提供参考.
In order to promote the preheating effect of N2O monopropellant thruster,the structure of the thruster was improved and inner-heating mode was set up.The preheating experiment of the thruster with inner-heater was conducted in a vacuum chamber,and the catalyst was heated to 260 ℃（533 K） with 10 W after 5 800 s,confirming the feasibility and advantage of the inner-heating mode.3-D model of the thruster was built and finite element software was utilized to analyze the preheating process.Time-dependent temperature filed of the structure was obtained.Numerical result agrees well with the experimental data,which demonstrates the accuracy of the simulation model.Then a simplified system model of the thruster with inner-heater was designed and 10,5,3 W power were utilized to simulate the preheating process in space environment.The result shows that the catalyst will be heated to 250 ℃ with 10W and 5 W power in 3 600 s,which can provide some references for the practical application of N2O monopropellant thruster.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第3期556-560,共5页
Journal of Aerospace Power
关键词
N2O
单组元推力器
内加热
预热
有限元分析
N2O
monoprorellant thruster
inner-heating
preheating
finite element analysis
