高超声速飞行器及防热壁板的有限元分析

发布时间：2018-01-04 06:06

本文关键词：高超声速飞行器及防热壁板的有限元分析　出处：《西南交通大学》2016年硕士论文　论文类型：学位论文

【摘要】：高超声速飞行器在以超声速或者高超声速飞行的时候,因为空气的粘性作用影响,导致飞行器表面周围气体温度升高,产生强烈的气动加热问题,对高超飞行器的正常飞行和安全系数的影响是极其严重的。到目前为止,针对简单几何结构(如梁、板、机翼等)的气动力、气动热与结构相互耦合引起的气动热弹性问题的研究较多,对飞行器整体同外界环境的气动力、热分析较少。高超声速气动问题已经成为飞行器设计中的关键技术之一,同时高超声速飞行器的热环境十分复杂,它的防热问题就也成了设计研究中的另一个关键问题,因此,进行高超声速飞行器气动特性及热分析、防热结构的仿真分析对高超声速飞行器设计及选材具有十分重要的意义。本文充分结合参考资料及文献,综述了高超声速技术的发展情况,国内外气动力气动热的研究现状及开展此项工作的必要性。对高超声速气流的流动特点及飞行器飞行的热环境进行了系统的分析。简单概述了几何建模的基础知识,在Pro/E三维造型软件及Ansys Workbench有限元分析平台上探讨了建模及分析思路和特点,对网格生成技术及质量要求作出了简要说明。利用了Pro/E软件对典型的X-51A飞行器进行了三维建模,实现了参数化建模,通过尺寸修改来驱动整个模型的修改,更新的过程仅需数秒钟就可完成。利用Workbench对其进行材料设置,边界条件及网格划分等前处理操作,通过FLUNT计算了在马赫数为6,攻角0-8。等条件下的升力、阻力系数等气动特性参数,得到飞行器表面的压力分布图及速度矢量图、三维流线图。另外,对飞行器整体结构进行动力学分析和热分析,得到飞行器等效应力应变图。在刚体运动状态下的固有振动频率及振型,飞行器总体的温度分布及热流密度分布图。最终得到的分析结果与再入飞行器试验相符,研究成果在一定程度上有益于开展飞行器后续的耦合及复杂物理场的研究。同时本文对飞行器典型的加筋壁板防热结构也进行了三维建模、动力学分析及热分析等研究,对均匀及非均匀温度场下的壁板模态进行了分析对比,得到振动频率的变化曲线图,壁板的等效应力应变分布图以及安全系数分布图。进行防热结构的动力学分析以及热分析,对于将来可重复使用的飞行器的热噪声疲劳分析和热颤振分析等问题的研究都是具有非常意义的。
[Abstract]:Hypersonic aircraft in supersonic or hypersonic flight, because the viscous effect of the influence of air temperature to gas around the aircraft surface increased, has a strong impact on the aerodynamic heating problems, the normal flight of hypersonic vehicle and the safety coefficient is extremely serious. So far, the simple geometric structure (e.g. beam, plate, etc.) of the wing aerodynamic force, more research caused by aerodynamic heating and structure coupling aerothermoelasticity problem, the whole aircraft aerodynamic force with the outside environment, thermal analysis less. Hypersonic aerodynamic problems have become one of the key technologies in aircraft design, at the same time, the thermal environment of hypersonic vehicle the thermal problem is very complex, it has become another key problem in the design of the hypersonic aerodynamic characteristics and thermal analysis, thermal structure imitation It is of great significance to the analysis of hypersonic vehicle design and material. Based on the references, the paper described the development situation of the hypersonic technology, research status at home and abroad the dynamic aerodynamic heating and the necessity to carry out the work. The characteristics of the flow and thermal environment on the flight of hypersonic flow the analysis of the system. A brief overview of the basic knowledge of geometric modeling in Pro/E 3D modeling software and Ansys Workbench finite element analysis on the platform of modeling and analysis of ideas and characteristics, made a brief description of the grid generation technique and quality requirements. The use of three-dimensional modeling of typical X-51A aircraft by Pro/E software, realized parametric modeling, modified to drive the model changes by size, the update process takes only a few seconds to complete the use of its Workbench. Materials, boundary conditions and mesh pre-processing operation, calculated by FLUNT in the Maher number is 6, 0-8. angle of attack under the conditions of the lift, the characteristic parameters of the drag coefficient of gas, obtained the aircraft surface pressure distribution and velocity vector diagram, three-dimensional flow diagram. In addition, the dynamic analysis and thermal analysis the overall structure of aircraft, the aircraft equivalent stress strain diagram. Natural frequencies and mode shapes in rigid motion state, the temperature distribution and heat flux distribution of vehicle system. The results obtained are consistent with the reentry test, study the coupling research results to a certain extent, is beneficial to carry out follow-up and complex aircraft physical field. And also the thermal structure of stiffened panel is typical aircraft for 3D modeling, dynamics analysis and thermal analysis, the uniform and non uniform temperature The panel mode field are analyzed, get the change curve of vibration frequency, wall equivalent stress and strain distribution and the safety factor distribution. The dynamic analysis of thermal structure and thermal analysis, for the future study of reusable spacecraft thermal noise fatigue analysis and thermal flutter analysis problems are it is of great significance.

【学位授予单位】：西南交通大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V244.1

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