Design and modeling of MEMS-based solid propellant propulsion

YOU Zheng; ZHANG Gao-fei; LIN Yang; REN Da-hai

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Design and modeling of MEMS-based solid propellant propulsion

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- Design and modeling of MEMS-based solid propellant propulsion
- Optics and Precision Engineering Vol. 13, Issue 2, Pages: 117-126(2005)
- 作者机构：
  
  清华大学精密仪器与机械学系北京,100084
- 作者简介：
- 基金信息：
- DOI：
  CLC： V43;TN433
- Received：22 February 2005，
  
  Revised：28 March 2005，
  
  Published Online：30 April 2005，
  
  Published：30 April 2005
- 稿件说明：
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YOU Zheng, ZHANG Gao-fei, LIN Yang, et al. Design and modeling of MEMS-based solid propellant propulsion[J]. Optics and precision engineering, 2005, 13(2): 117-126.
DOI：

YOU Zheng, ZHANG Gao-fei, LIN Yang, et al. Design and modeling of MEMS-based solid propellant propulsion[J]. Optics and precision engineering, 2005, 13(2): 117-126. DOI：

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。

Abstract

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.

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Keywords

references

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