低磁场量子化霍尔电阻样品发展综述

基于量子化霍尔效应建立电阻标准是当今前沿计量技术,是国际上定义电阻单位的最高标准,其核心部件是量子化霍尔电阻样品,传统砷化镓样品通常需要工作在10 T以上的强磁场环境中,磁体研制难度大,成本高,不易推广应用。随着量子电阻标准小型化、低成本化和国产化的发展,研制低磁场量子化霍尔电阻样品是发展趋势。介绍了砷化镓、石墨烯和铁磁拓扑材料三种低磁场量子电阻样品的原理,总结了研究现状和存在的问题,从磁场、温度、测量不确定度和技术成熟度等方面分析了三种方法的优势及不足,旨在为我国发展低磁场量子电阻标准提供理论基础。     

Feasibility study of thermo-compensated resistance brazing welding of C/C composites and T2 copper with AgCuTi filler metal

The dissimilar materials joining of C/C composites to T2 copper were performed successfully by thermo-compensated Resistance Brazing Welding (RBW) with AgCuTi filler powder. The interfacial microstructure, phase composition, and shear strength of the resistance brazed joints were investigated by the relevant analysis method. Experiment results indicated that the order affecting the shear strength of the C/C-Cu joint was welding current, welding pressure, and welding time in turn. The shear strength of backward thermo-compensated RBW was higher than that of forward thermo-compensated RBW due to the Peltier effect. The maximum shear strength of the C/C-Cu joint was 11.56 MPa in the optimized welding parameter with welding current of 8.0 kA, welding time of 60 ms, and welding pressure of 0.10 MPa by backward thermo-compensated RBW. The interface structure at the resistance brazed joint with this welding parameter was C/C composites/TiC/Cu (s.s)/T2 copper. The TiC phase was verified at the interface of the brazed joint by Scanning Electron Microscope (SEM), Energy-Dispersive X-ray Spectrometer (EDS), and X-ray Diffraction (XRD). Considerable fractures occurred in the C/C composites and partial fracture occurred at the interfacial reaction layer.     

2219 铝合金VPTIG 焊接接头拉伸性能分析

2219 铝合金气孔敏感性较强,变极性TIG 焊接工艺可以有效减少和抑制气孔产生,是适合于
2219 铝合金的焊接工艺。本文介绍了2219T62 铝合金VPTIG 焊接接头的拉伸性能,进行了拉伸断口形貌分析
和微观组织分析。结果表明:2219T62 铝合金VPTIG 焊接接头强度系数可以达到65% 以上,焊接接头为混合
断裂方式,VPTIG 焊缝盖面层气孔相比打底层较多。     

Hardware qualification for scientific ballooning missions

The European Stratospheric Balloon Observatory (ESBO) initiative aims at simplifying the access to stratospheric balloon missions. We plan to provide platforms and support with instrument design in order to support scientists. During the design process, the inevitable question of qualification for the harsh flight conditions arises. Unfortunately, there is no existing standard for qualification of stratospheric ballooning hardware. Thus, we developed a qualification procedure for use within ESBO and similar projects.In this paper, we present our analysis of the environmental conditions in the stratosphere. While conditions at typical balloon float altitudes are similar to the space environment, there are also some relevant differences. For example, the thermal environment is dominated by radiation and thermal conduction, but the remaining atmosphere still supports a certain amount of convection. The remaining atmospheric pressure in the stratosphere also leads to reduced arcing distances. Vibrational loads are far less than for space missions, but quasi-static or shock loads may occur. The criticality of radiation increases with mission duration.Based on the environmental conditions, we present the qualification procedures for ESBO, which are based on the European Cooperation for Space Standardization (ECSS) standards for space systems. Overtesting against too high requirements leads to overengineering, driving mission cost and mitigating the advantages of balloons over space missions. Therefore, we modified the ECSS standards to fit typical scientific ballooning missions over several days at altitudes up to 40 km. Furthermore, we analyzed design rules for space systems with regard to their relevance for scientific ballooning, including material and component selection. We present the experience from the hardware qualification process for the ESBO prototype STUDIO (Stratospheric UV Demonstrator of an Imaging Observatory). Even though boundary conditions are different for each individual mission, we aimed for a broader approach: We investigated more general requirements for scientific ballooning missions to support future flights.     

2195铝锂合金弧焊技术研究现状

铝锂合金具有密度低、比模量高、比强度高、抗疲劳及腐蚀性能良好等特点,被认为是航空航天领域最有应用前途的结构材料之一.本文回顾了铝锂合金的发展历程,介绍了新一代2195铝锂合金的成分、组织结构及可焊接性,分析其焊接过程出现的主要问题,概述了国内外机构通过优化2195铝锂合金配用焊丝及弧焊工艺,改善接头组织结构及力学性能的...     

2195铝锂合金钨极氩弧焊接工艺研究

针对2195铝锂合金在焊接时裂纹敏感性高、气孔敏感性高、易氧化等问题，开展氩弧焊接工艺研究，对焊接头的抗裂性、力学性能及显微组织进行了分析。研究表明，提高焊缝金属中的Cu含量，可以有效降低2195铝锂合金熔焊接头的裂纹敏感性，裂纹率K₁=0%,K₂=0%。2195铝锂合金单面双层焊接接头力学性能最佳，抗拉强度超过376 MPa，延伸率达到5.5%。提高焊接试板的清理深度可以解决焊接气孔敏感性高的问题，增加氩气拖后保护及背保护措施可以有效防止焊接氧化问题。熔焊工艺研究可为2195铝锂合金的工程应用提供技术支撑。     

推进剂管理装置的可靠性增长及试验验证

采用原始的焊接方式焊接筛网式推进剂管理装置的收集器合格率低、可靠性差。为此,采用纯钛箔作为过渡层进行了不锈钢筛网与钛合金支压板的电阻缝焊试验以及随后这两者与钛合金骨架的电子束焊试验,然后进行了地面力学环境下的振动试验,以验证焊接方式改进后收集器的可靠性。焊接试验结果表明,纯钛箔过渡层一方面可以大幅降低筛网在电阻缝焊时的焊接热量,有效地减小筛网的热变形;另一方面可以在电阻缝焊后形成牢固、封闭的纯钛/不锈钢筛网焊缝过渡区,有效地增加电子束焊时筛网的变形抗力,从而使得焊接后试样的合格率和性能大幅提高。振动试验结果表明,焊接方式改进后收集器的可靠度置信下限从0.90增加到了0.96。     

Review on residual stress and its effects on manufacturing of aluminium alloy structural panels with typical multi-processes

In the aerospace industry, integrated aluminium alloy plates and stiffened panels with high accuracy and performance attract significant interest. To manufacture these panels as integrity with high accuracy, multiple processes need to be utilised, such as machining, welding and forming. During the whole manufacturing chain, residual stresses can be generated and redistributed in the components among different processes. The residual stress would significantly affect the shapes and properties of the final products. Currently, these great effects are not well considered in the design and manufacturing processes. This paper aims to draw a general understanding of the residual stress generated in the pre-manufacturing processes and its effects on subsequent manufacturing processes. The mechanisms and distributions of residual stresses generated in typical pre-manufacturing processes of structural panels, including machining, welding and additive manufacturing (AM), are firstly summarised. The detailed effects of generated residual stresses on distortion and application properties in subsequent manufacturing processes are then concluded. In addition, current methods developed for the investigation of residual stress effect in multi-processes manufacturing are critically reviewed, including experimental, analytical, finite element (FE) and machine learning methods. Furthermore, the future development trend of methods for residual stress consideration and control in the design of manufacturing processes is summarised, providing comprehensive guidance to achieve the high accurate manufacturing of aluminium alloy structural components.