Proe轴对称矢量喷管结构设计
毕业论文关键词 固体火箭发动机 推力矢量 结构设计 可动喷管 运动分析
Title Axisymmetric vectoring nozzle design
AbstractThis paper describes the background and significance of axisymmetric vectoring technology,describes the development of solid rocket motor thrust vectoring technology,the current situationand the main vectored nozzle. For the domestic research needs,Put forward the feasible movablenozzle sports programs - ball nozzle, elaborated development of ball nozzle and the advantages,analyzed the ball nozzle structure ,by calculating, respectively, to complete the ball nozzle innertube profile design, the structure and size design of the ball nozzle male ball and femalesocket,the combustion chamber base design , and the design of two control rods. By proe 3Dmodeling software to construct three-dimensional model of a ball nozzle,complete thesimulation assembly of all parts ,and the movement of the bodies are obtained by analyzing themovement of the movable nozzle, that nozzle from the balance position starting, the actuator rodextension and compression, respectively, each elongated 1mm, the nozzl swinging anglegradually reduces,and each compression 1mm, the nozzle swinging angle graduallyincreases.Nozzle can achieve maximum swing angle of ± 13 °. By proe three-dimensionalsoftware and Autocad software,each parts drawing is obtained ,which shows the specificstructure of each member.By hydraulic drive lever work, making the nozzle swing
.Keywords Solid rocket motor Thrust vector Structural Design Movable nozzleMotion analysis
目录
1绪论.1
1.1研究背景和意义.1
1.2.1国外固体火箭发动机推力矢量喷管的发展状况.2
1.2.2我国推力矢量喷管的发展状况4
1.3推力矢量控制装置分类.4
1.4喷管及推力矢量装置的设计要求4
1.5本课题的研究内容4
1.6本文的结构.5
2总体设计.6
2.1几种主要的固体火箭发动机矢量喷管的对比..6
2.2球窝喷管结构设计.9
2.2.1设计理念9
2.2.2球窝喷管的结构特点..2
2.2.3材料选择..3
2.2.4球窝喷管的结构分析..3
3球窝喷管的零部件设计5
3.1喷管结构设计..5
3.1.1喷管内型面设计5
3.1.2喷管的具体结构设计..7
3.1.3喉部设计..8
3.2阴球窝结构设计.9
3.3燃烧室底座结构设计11
3.4外套筒与作动杆结构设计.13
3.4.1球铰中心与铰链中心的距离测定13
3.4.2作动杆与外套筒的尺寸的确定..14
4运动分析..18
5总结与愿望.21
5.1总结..21
5.2愿望..21
致谢22
参考文献.23
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