钛材降低成本的途径

降低钛及钛材加工生产成本是钛及钛材走向民用的重大问题。本文介绍了海绵钛、钛铸件、钛粉冶金产品、钛合金及残钛回收的低成本生产和加工方法，以期对推广钛的民用有所裨益。     

超塑成形技术研究及其在航空航天上的应用

从超塑成形技术的早期研究入手,综合分析了超塑成形技术的研究现状,包括合金材料、成形设备、陶瓷模具及模拟技术现状等,总结归纳了超塑成形技术在航空航天工业上的应用,重点介绍了EADS-CASA采用SPF或SPF/DB制造发动机零件及外壳零件,以及美国、欧空局、日本制造航天器贮箱的SPF技术,最后探讨了目前国际上超塑成形技术的几个主要研究方向,包括轻质镁合金的超塑成形、用于SPF的搅拌摩擦焊插件以及陶瓷、透明金属的超塑成形技术研究等。     

A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures

During a recent experimental test campaign performed in the framework of ESA Contract 16721, the ballistic performance of multiple satellite-representative Carbon Fibre Reinforced Plastic (CFRP)/Aluminium honeycomb sandwich panel structural configurations (GOCE, Radarsat-2, Herschel/Planck, BeppoSax) was investigated using the two-stage light-gas guns at EMI. The experimental results were used to develop and validate a new empirical Ballistic Limit Equation (BLE), which was derived from an existing Whipple-shield BLE. This new BLE provided a good level of accuracy in predicting the ballistic performance of stand-alone sandwich panel structures. Additionally, the equation is capable of predicting the ballistic limit of a thin Al plate located at a standoff behind the sandwich panel structure. This thin plate is the representative of internal satellite systems, e.g. an Al electronic box cover, a wall of a metallic vessel, etc. Good agreement was achieved with both the experimental test campaign results and additional test data from the literature for the vast majority of set-ups investigated. For some experiments, the ballistic limit was conservatively predicted, a result attributed to shortcomings in correctly accounting for the presence of high surface density multi-layer insulation on the outer facesheet. Four existing BLEs commonly applied for application with stand-alone sandwich panels were reviewed using the new impact test data. It was found that a number of these common approaches provided non-conservative predictions for sandwich panels with CFRP facesheets.     

某型无人机碳纤维尾撑钻孔组合夹具设计与应用

结合设计图样及材料特性,研究了一种用于加工碳纤维尾撑的工艺及钻孔组合夹具,并阐述了其设计要点。     

Tensile properties analysis of CFRP-titanium plate multi-bolt hybrid joints

Hybrid joints have better tensile properties than pure bonded and bolted bolts, and are increasingly used in the aerospace field. Tensile tests are carried out for the Hybrid Bonded/Bolted(HBB) joints of Carbon Fiber Reinforced Polymer(CFRP) laminate and titanium alloy plate under different bolt numbers, and the corresponding load–displacement curves are obtained. At the same time, based on Continuum Damage Mechanics(CDM) theory, which is derived from 3D Hashin failure criteria, and a Cohesive Z...     

Lightweight Design of Spaceborne CFRP Rigid Antenna Reflector

In order to overcome the shortcoming of space-borne rigid antenna reflector made of carbon fiber reinforced plastic (CFRP) skins with aluminum honeycomb sandwich (SAHS) structure, a new type of full CFRP skin plus rib (SPR) structure ring-focused parabolic surface antenna reflector with the size of 2.5 m 1.9 m is designed. Under the condition that the original caliber, surface type, and interface remain unchanged, the main influence factors are designed and controlled. First, from the perspective of high stiffness, lightweight, and easy to form, a finite element simulation software is used to analyze and optimize the layout of the rib, the cross-sectional shape of the rib, the size of the rib, and the matching of the size and the coefficients of thermal expansion (CTEs) of the rib and the skin. Second, two structures are prepared by the autoclave molding process. Third, the weight and the surface precision root mean square (RMS) value are measured. The results show that the fundamental frequency of the SPR structure is 142.2 Hz, which is 3.5 Hz higher;the number of the new structural parts is reduced by 40%, and the forming process is greatly simplified. The total weight of the new structure is 11.9 kg, lighter 42.5%, indicating that the weight loss is obvious. The RMS value is 0.15 mm, which is slightly lower 0.01 mm but satisfies the accuracy requirement not greater than 0.3 mm. It is proved that the SPR structure reflector is a superior structure of the lightweight spaceborne antenna reflector.     

压-压疲劳载荷下CFRP层合板表面红外辐射特征

为探究含冲击损伤CFRP层合板在循环交变载荷下的损伤演化规律,基于热力耦合效应研究了含损伤CFRP层合板疲劳过程中的表面红外辐射特征。以压-压疲劳试验模拟交变载荷,采用红外热成像方法分析了疲劳过程中含损伤CFRP层合板的热图序列和温度数据,结果表明：随着疲劳次数的增加,损伤沿垂直疲劳载荷方向演化,热斑颜色逐渐加深,初始冲击损伤形状逐渐演化为椭圆状,最后热斑横向端部出现"尖点";试件最大表面温差演化整体呈"快速上升-缓慢上升-快速上升"规律,最后出现跳升,其中热斑尖点、最大表面温差跳升可被视为结构疲劳破坏的前兆;含损伤CFRP层合板疲劳破坏时,其最大表面温差主要与纤维和基体种类有关,而试件铺层方式相较于纤维基体类别对最大表面温差无明显影响。研究揭示了冲击后CFRP层合板在疲劳载荷作用下的损伤演化规律,为飞行器复合材料结构的剩余疲劳寿命评估与损伤容限设计奠定了基础。     

碳纤维复合材料元件静态力学测试技术及实证研究

为了验证高温、中温1和中温2碳纤维复合材料与国外碳纤维复合材料技术指标的差别,最大限度地规避国产复合材料在结构设计和使用过程中的风险,需要从宏观力学的角度,通过进行不同铺层方式的高温、中温1和中温2复合材料元件静态力学试验,对强度和应变测试数据进行比对分析,并在测试方法上有所突破。本文主要通过复合材料元件开孔拉伸试验进行分析,提出了采用引伸计来同步测量开孔拉伸强度对应应变响应的试验方法,在碳纤维复合材料元件静态力学检测中取得了良好的应用效果。     

碳纤维增强复合材料的单脉冲放电凹坑特性研究

通过单脉冲放电试验对碳纤维增强复合材料(CFRP)的放电凹坑特性进行了试验研究,发现不同碳纤维排布方向上放电凹坑形状和个数不同,电极与碳纤维垂直时出现多个凹坑的概率高达86%,并分析了多个放电凹坑产生的原因。     

铺层顺序对碳纤维复合材料钻削分层制孔的影响

在碳纤维环氧树脂基复合材料的钻削制孔加工过程中会产生很多种类的缺陷,其中分层损伤是最难以控制的缺陷,严重影响机械连接的有效性和材料的使用性能。将铺层规则尤其是防分层规则应用于层合板铺层顺序优化中,使用Memetic算法得出防止碳纤维板分层的铺层顺序,并设计CFRP制孔试验加以论证。试验结果表明,复合材料铺层角度对分层缺陷有重要影响,优化后的碳纤维复合材料可有效减少分层、毛刺缺陷。