碳纤维复合材料超声振动辅助制孔数值模拟及实验研究

发布时间：2018-01-13 05:36

本文关键词：碳纤维复合材料超声振动辅助制孔数值模拟及实验研究　出处：《南昌航空大学》2016年硕士论文　论文类型：学位论文

【摘要】：近几十年来,碳纤维增强复合材料被广泛运用于航空航天、国防科技、汽车产业及健身医疗等领域,其中在航空航天领域所运用到的碳纤维复合材料对材料本身的质量有着极高的要求,在加工制造方面也有着极高的加工精度。传统的加工制造难以满足其要求。超声辅助加工是一种新型的特种加工方法,在加工过程中有着降低切削力、切削热,提高表面加工质量的诸多优势,适用于碳纤维复合材料的切削加工。本文评述了提高孔的加工质量的必要性,超声振动钻削技术的概念、基本原理及其特点,介绍了国内外的研究现状,指出该项技术存在的问题,并对其今后的研究方向作了展望。本文以超声振动钻削工艺系统为研究对象,采用理论指导、有限元仿真模拟建模、可行性验证、实例应用与综合评估相结合的方法,分析超声振动辅助切削碳纤维复合材料过程中切削力的变化规律,分析碳纤维复合材料制孔过程中材料去除过程,建立超声振动辅助钻削碳纤维复合材料有限元仿真模型,基于碳纤维复合材料微观结构(纤维、基体)的演变,对切削过程中加工参数与加工孔质量之间的关系进行了研究;搭建碳纤维复合材料超声振动辅助钻削实验平台,分析碳纤维复合材料超声振动钻孔加工中各切削参数对孔出口质量的影响规律。通过有无超声辅助钻削对比实验及仿真得出的结论如下:1)在相同切削参数下,超声振动辅助钻削比普通钻削产生的切削力普遍要小,其孔的加工质量普遍要好;2)在相同的切削参数下,超声振动辅助钻削切削力随着超声振动幅值的增大先增大后减小,基体开裂损伤演化的区域范围先变大后减小,孔的出口表面质量先变差再变好,因此在超声振动辅助钻削碳纤维复合材料时为得到更高质量的孔应选用合适的振幅;3)在相同的主轴转速下,随着进给速度的增加,切削力增大,基体损伤越严重,孔的出口表面质量出现的缺陷越严重;在相同的进给速度下,随着主轴转速的提高,切削力减小,基体损伤越小,孔的出口表面质量越好;4)在碳纤维复合材料的钻削制孔过程当中,其轴向切削力的大小会影响加工孔的质量,切削力越小加工出来的孔出口表面质量越好,反之越差。
[Abstract]:In recent decades, carbon fiber reinforced composites (CFRP) have been widely used in aerospace, defense technology, automobile industry and health care. The carbon fiber composites used in the field of aerospace have very high requirements for the quality of the materials themselves. Ultrasonic aided machining is a new kind of special machining method, which can reduce cutting force and cutting heat in the process of machining. In this paper, the necessity of improving the machining quality of holes, the concept, the basic principle and the characteristics of ultrasonic vibration drilling technology are reviewed. This paper introduces the present research situation at home and abroad, points out the existing problems of this technology, and makes a prospect for its future research direction. This paper takes the ultrasonic vibration drilling process system as the research object and adopts the theoretical guidance. Finite element simulation modeling, feasibility verification, example application and comprehensive evaluation method are used to analyze the changing law of cutting force in ultrasonic vibration assisted cutting of carbon fiber composites. This paper analyzes the material removal process of carbon fiber composites in the process of making holes, and establishes the finite element simulation model of ultrasonic vibration assisted drilling of carbon fiber composites, based on the evolution of microstructure (fiber, matrix) of carbon fiber composites. The relationship between machining parameters and hole quality is studied. The experimental platform for ultrasonic vibration assisted drilling of carbon fiber composites was built. The influence of cutting parameters on the quality of hole outlet in ultrasonic vibration drilling of carbon fiber composites is analyzed. The conclusions are as follows: 1). Under the same cutting parameters. The cutting force produced by ultrasonic vibration assisted drilling is generally smaller than that produced by ordinary drilling, and the machining quality of its holes is generally better. 2) under the same cutting parameters, the ultrasonic vibration assisted cutting force increases first and then decreases with the increase of ultrasonic vibration amplitude, and the range of damage evolution of matrix first increases and then decreases. The quality of the outlet surface of the hole first becomes worse and then better, so the proper amplitude of the hole should be chosen in the ultrasonic vibration assisted drilling of carbon fiber composite material in order to obtain the higher quality of the hole. 3) at the same spindle speed, with the increase of feed speed, the cutting force increases and the matrix damage becomes more serious. At the same feed speed, with the increase of spindle speed, the cutting force decreases, the smaller the matrix damage, the better the quality of the outlet surface of the hole. 4) in the drilling process of CFRP, the axial cutting force will affect the quality of the hole, the smaller the cutting force, the better the surface quality of the hole outlet, and the worse the hole surface quality is.
【学位授予单位】：南昌航空大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：TG663

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