基于二次开发的复合材料优化技术研究

发布时间：2018-04-11 18:51

本文选题：复合材料 + 工程方法　；参考：《重庆理工大学》2015年硕士论文

【摘要】：复合材料与金属材料相比不仅仅具有强度高、刚度大等优点,而且可以通过控制铺层厚度、铺层方向等方法来改变材料的性能,使产品性能得到充分发挥,让材料设计和结构设计达到高度统一。针对飞机复合材料结构的优化设计,在保证飞机的承载能力不变情况下,通过优化复合材料的铺层比例和铺层次序,可以大幅度降低飞机的质量,从而降低飞机的生产成本。因此复合材料在飞机上的使用,是飞机在结构设计上的重大突破。如何针对复合材料进行优化设计则是这个重大突破必须解决的关键性难题。本文以复合材料机翼为研究对象,对该结构进行参数优化,得到质量最轻且满足承载能力的复合材料机翼。主要做了如下工作:(1)利用理论推导结合工程实际,得到复合材料层合板结构计算轴压屈曲载荷的工程计算方法,分别运用工程方法与有限元法,对不同厚度和尺寸的层合板结构屈曲载荷计算结果进行对比。(2)选择适用于复合材料机翼翼盒优化的技术路线,运用商业软件进行铺层次序优化,建立复合材料尺寸优化铺层库。(3)针对复合材料机翼翼盒粗模型,本文进行了前处理检查和模型预分析检查,以确保模型的正确性。针对机翼实际工况多、计算时间长的难题,本文利用单值包线法,对该机翼进行严重工况挑选,以减少计算时间,最后运用商业软件进行尺寸优化。(4)利用TCL/TK脚本语言二次开发,编写了复合材料前处理工具集和复合材料结构稳定性计算工具,达到节约建模和计算时间的目的。本文运用算例验证了优化技术路线,完成了复合材料机翼翼盒优化,并开发了能节约前处理时间的工具,对复合材料层合板结构优化设计具有一定的参考价值。
[Abstract]:Compared with metal materials, composite materials not only have the advantages of high strength and high stiffness, but also can change the properties of materials by controlling the thickness and orientation of the layers, so that the properties of the products can be brought into full play.Material design and structure design to achieve a high degree of unity.According to the optimal design of aircraft composite structure, the quality of aircraft can be greatly reduced and the production cost of aircraft can be reduced by optimizing the proportion and sequence of composite layers under the condition that the aircraft's bearing capacity is invariable.Therefore, the use of composite materials in aircraft is a major breakthrough in structural design.How to optimize the design of composite materials is a key problem that must be solved in this breakthrough.In this paper, the composite wing is studied, and the structure parameters are optimized to obtain the composite wing with the lightest mass and satisfying the bearing capacity.The main work is as follows: (1) the engineering calculation method for calculating the axial buckling load of composite laminated structure is obtained by combining the theoretical derivation with engineering practice, and the engineering method and finite element method are used respectively.The buckling load calculation results of laminated plate structures with different thickness and size are compared. (2) selecting the technical route suitable for the wing box optimization of composite wing, and using commercial software to optimize the layering order.In order to ensure the correctness of the model, the pre-processing check and model pre-analysis check are carried out for the wing box coarse model of the composite wing in order to ensure the correctness of the model.In view of the problem that the wing has many actual working conditions and long calculation time, this paper uses the single value envelope method to select the serious working conditions of the wing to reduce the calculation time. Finally, the commercial software is used to optimize the size of the wing. 4) the TCL/TK script language is used for secondary development.The pre-processing tool set of composite materials and the structural stability calculation tool of composite materials are compiled to save the time of modeling and calculation.In this paper, an example is used to verify the optimization technology, and the optimization of wing box of composite wing is completed, and a tool is developed to save the pre-processing time, which has a certain reference value for the optimization design of composite laminated plate structure.
【学位授予单位】：重庆理工大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：TB33

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