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摘要目前微推进器在航天领域是研究热点之一。固体化学微推进器作为一种重要的微推进器在微型航天器、微卫星姿态调整和轨道保持方面具有很好的应用前景。为了研究高性能固体化学微推进器，本文主要研究在微尺度下复合推进剂装药工艺、推进剂燃烧特性及测试分析。63766
利用高速摄影技术研究了AP/环氧树脂推进剂在微细石英管内的燃烧现象，得到了燃烧速度随圆管内径、壁厚的变化；利用热成像技术分析了圆管内径对热损失的影响。研究表明：推进剂在微管中的燃烧存在临界壁厚效应，当石英管管壁厚度小于临界厚度时，壁厚越厚，壁面热损失增加，燃速降低；当壁厚大于临界厚度时，壁厚越厚，壁面热损失越少，燃速升高；1mm内径的石英管临界厚度在2mm~3mm之间；相同壁厚下，内径在1mm~3mm，燃速随着玻璃管内径的增大而增大，当内径增加到一定值，内径对燃速影响趋于稳定；相同壁厚，内径越大向环境对流传热的损失热量越多。研究结果对于完善固体化学微推进器技术具有一定意义。
毕业论文关键词： 微尺度，推进剂，燃烧速度，临界壁厚，热损失
毕业设计论文外文摘要
Title Testing and Analysis of Gas-solid Two-phase Flow Field Combustion of Propellant in Micro-tube
Abstract
Currently micro-propulsion research in the field of aerospace is one of the hotspots. Solid chemical micro-thruster as an important micro-thruster power has maintained a good prospect, especially in the micro-spacecraft, micro-satellite attitude and orbit adjustment to maintain respect. To study high-efficiency solid chemical micro-thruster, the charge process of propellant in micro-scale, the characteristics of propellant combustion and testing were investigated by this dissertation.
The change of burning rate of AP/ER (Ammonium Perchlorate /Epoxy Resin) varied with tube diameters, wall thickness in micro-scale quartz tube were obtained by the high-speed photography. The phenomenon of the change of thermal loss of AP/ Epoxy Resin varied with tube diameters were obtained by thermal imaging technology .The result showed that the critical thickness effects existed. Thinner than critical thickness, thermal loss through tube wall increased and burning rate decreased with thicker wall. However, thermal loss decreased and burning rate increased when wall thickness got thinner, below the critical thickness. Critical thickness of silica tube with 1mm inner diameter was between 2mm and 3mm. With constant wall thickness, the inner diameter 1mm -3mm, thermal loss became significant when inner diameter increased, and burning rate increased with larger inner diameter under certain diameter, but burning rate became stabilize above this diameter. With constant wall thickness, the larger diameter and the more thermal loss of convective heat transfer to the environment. Findings had a certain significance for improving solid chemical micro-thruster technology.
Keywords Micro-scale, propellant, burning rate, the critical thickness, thermal loss
1 引言 1
1．1 论文研究的背景和意义 1
1．2 微尺度燃烧国内外研究概述 2
1.2.1 微尺度燃烧稳定性 3
1.2.2 微尺度燃烧火焰结构 4
1.3 本文研究内容 4
2 微尺度推进剂燃烧特性实验 5
2.1 药剂制备与注装 5
2.1.1 实验材料
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