微型固体火箭制造与点火技术的研究
耿欢1，侯大立2，董磊1
（1.上海交通大学 机械动力与工程学院，上海 200240；2.中国石油西气东输管道公司，上海 200122）
摘要：介绍了一种新型微型固体火箭的结构特点。首次通过微弧氧化工艺实现了铝合金材料在制造微型固体火箭燃烧室壳体方面的应用，并经数值计算验证微弧氧化层的隔热效果。根据微型固体火箭结构特点选用了半导体桥作为点火装置。为了进一步研究微型固体火箭族在空间中分组点火工作状况，设计了模拟微型固体火箭族（实验设计为180个）空间点火的实验台。实验台实现了通过小型键盘输入火箭代号，同时LED显示器显示以及单片机控制半导体桥点火等工作过程。
关键词：微型固体火箭；微弧氧化；点火技术；单片机
中图分类号：TJ7 文献标志码：A doi：10.3969/j.issn.1006-0316.2015.10.04
文章编号：1006－0316 (2015) 10－0014－05
A study of the manufacture and ignition technique of micro solid propellant thruster
GENG Huan1，HOU Dali2，DONG Lei1
( 1.School of Mechanical Engineering, Shanghai Jiaotong University, Shanghai 200240, China; 2.Petrochina West-East Gas Pipeline Company, Shanghai 200122, China )
Abstract：The application of micro solid propellant thruster on controlling the gesture and orbit of aerocraft was introduced. The configuration of the micro solid propellant thruster was described, and the Al alloy material was first applied to manufacture the wall of combustor using the PMAO technology. Base on the characteristic of micro solid propellant thruster, Semiconductor Bridge was applied as the ignition device. In order to simulating and investigating the working status of thrusters in space, an experimental platform which consists of 180 micro solid thrusters was described. Several functions have been achieved using this platform, for instance, entering the code name of each thruster with a mini-keyboard, displaying the number with a LED monitor, and controlling the semiconductor bridge with SCM.
Key words：micro solid propellant thruster；PMAO；ignition；SCM
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收稿日期：2015－03－09
作者简介：耿欢（1984－），男，工程硕士，工程师，主要从事燃气轮机技术/航天电推进技术研究工作。
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