超燃冲压发动机模型壁厚优化
发布时间：2018-09-09 19:07
【摘要】：超声速燃烧冲压发动机技术是当今世界的重点研究方向,它的技术水平直接体现了一个国家的科技水平,已成为衡量一个国家科技水平的重要标准。习惯上简称为超燃冲压发动机。当飞行器马赫数大于6时,必须使用超燃冲压发动机作为推进动力,它的发展受到了很多发达国家的关注。在21世纪超燃冲压发动机技术必定会以更快的方式发展,并广泛应用于民生、军事等多个领域,影响人类的未来。超燃冲压发动机是在一个多物理场耦合的环境下工作的,工作过程中不仅有气动热引起的温度场与流场的耦合,还有因结构传热引起的结构场与温度场的耦合。超燃冲压发动机的壁面内部温度最高可以达到1400K—1600K,材料的选择也必须能够承受高温和高压,且具有较高的强度。当然,在保证正常工作的前提下,还要尽可能的降低超燃冲压发动机的质量,合理的安排材料分布,提高性能,节省材料。本文首先利用有限元软件patran对某型超燃冲压发动机建立了有限元模型,给定初始热通量和初始温度,在假定发动机正常运行10s的前提下根据传热学理论进行了热固耦合的瞬态温度场分析和结构分析。然后利用优化软件isight集成patran/nastran和mtalab,使用matlab编程来关联单元节点与壁厚,并使用isight软件中的优化方法来对超燃冲压发动机的壁厚进行优化,在满足材料极限应力和变形要求的条件下,减轻发动机重量,省去不必要的材料。
[Abstract]:Supersonic combustion ramjet technology is the key research direction in the world today. Its technical level directly reflects a country's scientific and technological level and has become an important standard to measure a country's scientific and technological level. In the 21st century, scramjet technology will surely develop in a faster way and will be widely used in many fields, such as people's livelihood, military affairs and so on, affecting the future of mankind. Only the coupling of temperature field and flow field caused by aerodynamic heat transfer and the coupling of structure field and temperature field caused by structure heat transfer can be achieved. The maximum temperature inside the wall of scramjet can reach 1400 K-1600 K. The material selection must be able to withstand high temperature and pressure and have high strength. In this paper, a finite element model of a scramjet is established by using the finite element software patran. Given the initial heat flux and temperature, the model is based on the assumption that the engine is running normally for 10 seconds. The theory of heat transfer is used to analyze the transient temperature field and the structure of the scramjet. The optimization software iSIGHT is used to integrate patran/nastran and mtalab. The matlab program is used to correlate the node and wall thickness of the scramjet. The optimization method of iSIGHT software is used to optimize the wall thickness of the scramjet to meet the material limit stress. Under the condition of force and deformation requirements, the engine weight is reduced and unnecessary materials are omitted.
【学位授予单位】：大连理工大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V231
本文编号：2233301
[Abstract]:Supersonic combustion ramjet technology is the key research direction in the world today. Its technical level directly reflects a country's scientific and technological level and has become an important standard to measure a country's scientific and technological level. In the 21st century, scramjet technology will surely develop in a faster way and will be widely used in many fields, such as people's livelihood, military affairs and so on, affecting the future of mankind. Only the coupling of temperature field and flow field caused by aerodynamic heat transfer and the coupling of structure field and temperature field caused by structure heat transfer can be achieved. The maximum temperature inside the wall of scramjet can reach 1400 K-1600 K. The material selection must be able to withstand high temperature and pressure and have high strength. In this paper, a finite element model of a scramjet is established by using the finite element software patran. Given the initial heat flux and temperature, the model is based on the assumption that the engine is running normally for 10 seconds. The theory of heat transfer is used to analyze the transient temperature field and the structure of the scramjet. The optimization software iSIGHT is used to integrate patran/nastran and mtalab. The matlab program is used to correlate the node and wall thickness of the scramjet. The optimization method of iSIGHT software is used to optimize the wall thickness of the scramjet to meet the material limit stress. Under the condition of force and deformation requirements, the engine weight is reduced and unnecessary materials are omitted.
【学位授予单位】：大连理工大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V231
【参考文献】
相关期刊论文 前2条
1 魏鑫;孙冰;郑力铭;张杰;;超燃冲压发动机进气道表面热结构设计与分析[J];航空动力学报;2008年11期
2 戎宜生;陈伟芳;杨宇斌;刘伟强;;超声速进气道结构参数优化设计研究[J];力学季刊;2010年03期
，本文编号：2233301
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