N_2O单组元微型推进器内参数敏感性的研究  

Investigation of parameter sensitivity in micro monopropellant thruster based on N_2O

作　　者：柴宁[1] 姜培学[1] 孙锡九[1] 任泽霈[1] 

机构地区：[1]清华大学热能工程系,北京100084

出　　处：《热科学与技术》2004年第2期157-161,共5页Journal of Thermal Science and Technology

基　　金：国家杰出青年科学研究基金资助项目 ( 5 0 0 2 5 617) ;国家重点基础研究发展计划资助项目 ( G19990 3 3 10 6)

摘　　要：对一种新型的推进剂 N2 O在催化剂床中的流动和传热传质进行了数值模拟研究。分析和研究了催化剂的孔隙率、长度、比表面积、传质 Sh对推进系统的瞬态及稳态性能的影响。结果表明 :推进系统的瞬态性能与催化剂的孔隙率和长度有关 ,稳态性能与催化剂的比表面积及推进剂在催化剂床内的传质 Sh有关。研究结果为进一步改善微型化学火箭内部结构、提高其推进性能提供了理论依据。Numerical simulation of the heat and mass transfer and flow characteristics of a novel propellant (N 2O) in a circular catalyst-filled tube was presented. The influence of catalyst porosity, length, specific area and Sherwood number to the transient and stable performance of the thruster were studied and analyzed. The results indicate that the transient performance of the thruster is related to the catalyst porosity and length whereas the stable performance of the thruster is related to the catalyst specific area and the Sherwood number. These conclusions are beneficial to improve the catalyst structure and promote the overall performance.

关 键 词：单组元微型推进器 传热传质 小卫星系统 参数敏感性 催化剂 孔隙率 

分 类 号：TK123[动力工程及工程热物理—工程热物理]