MEMS固体化学推进器设计与建模研究  

Design and modeling of MEMS-based solid propellant propulsion

作　　者：尤政[1] 张高飞 林杨[1] 任大海[1] 

机构地区：[1]清华大学精密仪器与机械学系,北京100084

出　　处：《光学精密工程》2005年第2期117-126,共10页Optics and Precision Engineering

基　　金：国家"863"高技术项目;973国家安全重大基础研究项目。

摘　　要：研制了一种基于MEMS(微机电系统)技术的固体化学微推进器。给出了推进器的结构设计、工艺流程,以及推进剂加注方法。建立了推进器点火过程热传导模型,利用该模型分析了不同因素对点火延迟时间的影响。同时,通过建立推进器性能模型,进行了推进单元推力和冲量的预测,给出了仿真结果。结果表明:减小点火电阻衬底材料的密度、热导率和比热可以减小点火延迟时间和点火功率;在一定条件下,增大喷管出口与喉部面积比能够提高推进器真空推力和冲量;MEMS在推进系统中的应用,能够满足微小型卫星对星载推进系统小型化、微推力、高精度的要求。MEMS-based solid propellant propulsion-was developed. The structural design and fabrication process of the thruster, as well as the approach of propellant injection are presented. A thermal conduct model of ignition phase was established, with which the effect of various parameters on the ignition delay is analyzed. Meanwhile, the development of the model for performance simulation of micro thruster is described. The result indicates that low density, thermal conductivity and specific heat of substrate material of ignitor resistor can reduce the ignition delay time and power consumption; under certain condition, increasing the exit-to-throat section ratio of nozzle will help to raise the thrust and impulse bit of the propulsion in vacuum. It can be concluded that MEMS-based propulsion can meet the requirement of miniaturization, micro thrust and high accurate impulse bit for the propulsion system of micro satellite.

关 键 词：微推进器 微机电系统 点火延迟 微推力 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程] TN433[电子电信—微电子学与固体电子学]