复合材料多面体支架设计与成型技术研究

发布时间：2018-03-20 10:11

本文选题：复合材料　切入点：多面体支架　出处：《北华航天工业学院》2015年硕士论文　论文类型：学位论文

【摘要】：卫星总装直属件通常悬臂安装在卫星外板上,具有承受集中载荷大、外部环境恶劣的特点,为保证其刚强度要求,通常采用高性能铝合金机加成型。此种方法结构重量大、工艺复杂,研制周期长,制约卫星总体研制计划。本文以某型号卫星总装直属件中的数传天线支架研制任务为背景,以支架结构设计要求为依据,展开碳纤维复合材料多面体支架的设计与成型技术研究工作。本文首先通过支架构型对比分析,确定使用复合材料层合板多面体支架构型。利用PATRAN/NASTRAN软件建立多面体支架有限元模型,对2.4mm厚度的支架进行了刚强度分析,结果表明其满足了刚度要求,但无法满足强度要求。提出加强梁、局部加强、整体增强三种加强设计方案,通过分析计算后确定采用整体增强方案,完成了复合材料多面体支架结构设计工作。通过模态、频率和随机响应分析对复合材料多面体支架的结构设计进行全面考核,计算结果均满足相关技术要求,从理论上验证了多面体支架设计的可行性。多面体支架的分析结果与铝合金材质支架数据相比,固有频率提高约6Hz,各测点位置x、y、z方向响应结果值均较小。根据预浸料成型工艺的基本原理和复合材料多面体支架的结构特点,提出了阳模铺层、阴模固化的整体成型技术路线,设计了复合材料多面体支架的成型模具,制备出满足技术要求的复合材料多面体支架。最终支架结构重量2.3kg,制造周期10个工作日,满足相关技术要求。对多面体支架进行超声无损检测及力学性能测试,验证了多面体支架的成型质量。提出了多面体支架振动环境的模拟试验方案,从x、y、z方向分别对支架进行了振动试验。结果表明,支架满足技术要求中的动载荷要求,其结构设计与成型工艺合理可行。
[Abstract]:The direct parts of satellite assembly are usually mounted on the outer board of the satellite, which has the characteristics of large concentrated load and bad external environment. In order to ensure its rigid strength, high performance aluminum alloy machine is usually used to add forming. The process is complex, the development period is long, and the overall development plan of satellite is restricted. This paper takes the research and development task of the data transmission antenna support in the assembly of a satellite as the background, based on the design requirements of the support structure. The research work on the design and molding technology of carbon fiber composite polyhedron scaffolds is carried out. The configuration of composite laminated polyhedron bracket is determined. The finite element model of polyhedron bracket is established by using PATRAN/NASTRAN software. The rigid strength of the 2.4mm thick bracket is analyzed, and the results show that it meets the requirement of rigidity. But it can not meet the strength requirement. This paper puts forward three kinds of strengthening design schemes: strengthening beam, local strengthening and integral strengthening. Through analysis and calculation, the design work of composite polyhedron support structure is completed by means of analysis and calculation. The structural design of composite polyhedron scaffolds was evaluated by frequency and random response analysis, and the calculated results met the relevant technical requirements. The feasibility of the design of polyhedron scaffolds is verified theoretically. The analysis results of polyhedron scaffolds are compared with the data of aluminum alloy scaffolds. The natural frequency is increased by about 6 Hz, and the response value in the direction of x ~ (y) y ~ (z) is smaller. According to the basic principle of prepreg molding technology and the structural characteristics of composite polyhedron support, the integral forming technology of positive die layering and solidification of negative die is put forward. The molding mould of composite polyhedron scaffold was designed, and the composite polyhedron scaffold, which met the technical requirements, was prepared. The final weight of the scaffold was 2.3 kg, and the manufacturing period was 10 working days. The ultrasonic nondestructive testing and mechanical properties test of polyhedron support are carried out to verify the forming quality of polyhedron bracket. A simulation test scheme for vibration environment of polyhedron support is proposed. The vibration tests were carried out in the direction of xyz. the results show that the support meets the requirements of dynamic load in the technical requirements, and its structure design and molding technology are reasonable and feasible.
【学位授予单位】：北华航天工业学院
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V443.4;V46

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