碳纳米材料辐射效应研究现状

碳纳米管（CNTs）和石墨烯是碳纳米材料中新兴的两种类型,因其优异的电学、热学、机械等性能,是目前航天工程中具有很大应用前景的材料.在复杂的空间环境中,辐射效应对材料的结构和性能具有重要影响,是决定其稳定性和适应性的关键因素之一.本文对碳纳米管和石墨烯材料的电子、离子等辐射效应研究现状进行了讨论分析,对辐射过程中缺陷的产生和类型、辐射在材料制备以及功能化改性修饰方面的应用、辐射对器件性能的影响以及空间适应性进行了分析,简述了以碳纳米材料为基础的复合材料的辐射效应以及辐射缺陷对材料性能影响的作用机制,提出了目前碳纳米管和石墨烯辐射效应研究中仍需要开展的工作,并对其在空间科学中的应用进行了展望.      

聚合物基复合材料凸头螺栓连接研究进展

机械连接是聚合物基复合材料最典型的连接方式,因其在连接工艺性和可靠性方面的优势,使其在航空航天制造领域得到了广泛应用。对凸头螺栓连接聚合物基复合材料接头的研究进展进行综述。回顾了复合材料接头的机械连接形式,讨论了在拉伸加载下的失效过程,详细论述了复合材料接头的损伤模式;重点讨论了复合材料接头力学性能影响因素的研究进展,包括复合材料性能（纤维类型、增强体结构形式、纤维与金属混杂层板、铺层角度及比例、固化工艺、初始材料缺陷）、紧固件性能（紧固件刚度、钉头型式、螺栓直径、螺纹密封、间隙配合、干涉配合、紧固件缺失）、连接板性能、侧向约束（拧紧力矩、预紧面积、补偿垫片、接触面摩擦因素）、几何效应（复合材料板尺寸、板厚与孔直径比、层合板宽度与孔直径比、孔端距与孔直径比、螺孔形状、螺孔质量、螺孔位置误差）、载荷（静载荷、动态载荷、疲劳载荷、蠕变、松弛、温湿载荷）等;对聚合物基复合材料凸头螺栓连接的未来研究方向进行了展望。     

聚合物基PTC材料稳定性的研究

提高导电复合材料的PTC(Positive Temperature Coefficient)强度和稳定室温电阻的重现性,是研究和使用聚合物基PTC材料所追求的目标.PTC材料经过在开关温度及其以上的较宽温度范围内重复热循环后,室温电阻升高,PTC强度降低.研究了辐射交联和在不同气氛中长时间热老化对聚合物基PTC复合材料的室温电阻、PTC强度、结晶度和开关温度等性能的影响.结果表明:辐射交联和氮气氛保护均有利于提高PTC材料的电性能稳定性,室温电阻和PTC强度的变化率相对较小.     

聚合物基纳米复合材料的理论研究进展

讨论了国内外关于聚合物基纳米复合材料的理论研究,包括聚合物/层状结构硅酸盐PLS(Polymer-Layer Silicate)纳米复合材料的热力学、动力学和微观力学,以及聚合物/颗粒状无机纳米复合材料的纳米微粒分散原理、纳米粒子尺寸与复合材料性能之间的关系等.      

航天器材料KAPTON和F4.6薄膜充电性能研究

Kapton和F4.6是两种航天器上最常用的重要热控材料,但它们都是高绝缘的有机高分子聚合物,故在充分利用它们的优良物化性质时,不能不关心它们在空间亚暴环境下表面充电的性能。为此本文在简述了新增环境温度变化的条件后,详细讨论了这两种材料在模拟空间真空、空间亚暴时电子辐照、太阳辐照及其所处环境温度变化时,它们表面电阻率随环境变化响应规律,并由此预测其充电的状态。     

航天服材料与发展动向

在载人航天飞行中,航天服是确保宇航员生命安全和具有良好工作能力的必不可少的一种装备,而选择或研制航天服所用的特种材料是航天服研制中的一项关键枝术。本文就空间环境对航天服材料的影响,航天服材料性能要求及其发展动向进行了较全面的论述。     

复合材料结构三维有限元分析的材料参数

在调研现有文献复合材料结构三维数值分析中材料参数的基础上,阐述了基于单层板材料性能数据建立复合材料三维材料参数的方法.通过对复合材料π接头结构的三维数值模拟和试验,研究了三维材料参数中不确定参数对结构刚度预测的影响;分别采用三维修正的最大应力准则、最大应变准则、蔡-胡准则和Hashin准则评价π接头的初始破坏,结合试验数据,研究不同失效准则对复合材料π接头结构的适用范围以及材料参数对初始破坏强度预测的影响.研究工作可为一般层合复合材料结构的三维建模提供参考,并为深入理解复合材料π接头结构力学性能、准确预测其破坏强度提供理论支持.     

三维全五向编织复合材料细观结构实验分析

对三维(3D)全五向编织复合材料的细观结构进行了实验研究,三维全五向编织复合材料是一种新型的编织复合材料,其细观结构对预测材料的性能有重要作用。采用显微计算机断层成像(micro-CT)技术得到了三维全五向编织复合材料的截面图片,通过在碳纤维试件中混编入少量玻璃纤维作为示踪纱,提高了示踪纤维束在截面图片中的的对比度。并通过三维重建得到纤维束实体模型,结合CAD技术对纤维束的横截面形状与空间走向进行了研究。结果表明:编织纱与轴纱纤维束的截面形状在材料不同区域与不同的花节高度内是变化的;在不同区域,编织纱的空间走向也是不同的;而轴纱在空间上基本保持伸直。由于编织纱对轴纱的挤压使轴纱表面产生螺旋状的压痕。      

循环湿热环境下碳纤维复合材料的界面性能

针对CCF300/5428复合材料在循环湿热环境下的吸湿-脱湿行为和层间剪切性能进行了研究,并结合扫描电镜观察了循环湿热处理的不同阶段纤维/基体界面结合状态.研究结果表明:经过反复吸湿后,水分的初始扩散速率和饱和吸湿率增加;脱湿后水对复合材料层间剪切性能的影响大部分可以消除;复合材料吸湿后室温环境下性能下降较少,但在高温高湿环境下,复合材料的性能会显著降低.     

Materials selection for applications in space environment considering outgassing phenomenon

Application of the existing materials selection methods is not much popular in space environment. This is in spite of involvement of the selection process in this field with a wide range of influential factors (e.g. conventional mechanical properties and over 21 space environmental effects). In this paper an introductory road map for employing systematic materials selection methods in the field by engaging the selection process with mechanical properties and only one of the space environmental factors is presented. Here, selected case studies, which are involved with outgassing phenomenon of materials in vacuum condition, highlight the incapability of some of the methods in dealing with such example problems. The study specifically indicates the effectiveness of the most recently introduced method, i.e. Z-transformation, over other existing methods. The results show that considering the mechanical properties of materials in conjunction with the space environmental effects produce much more reliable ranking of the candidate materials. Besides, the results recommend introducing more space environmental aspects in the selection process may produce a better outcome.     

SRB,G86和铝阳极化表面充电性能评价研究

SRB、G86涂层和铝阳极化着(黑)色是卫星表面热控用的材料。在轨道上,它们将直接与空间等离子体环境相接触,因此它们表面积累电荷的性质对是否会由它们引发放电、起弧、击穿等物理效应是至关重要的。为此在综合模拟空间环境下对它们的充电性能进行评价是十分必要的。通过实验评价可以正确了解它们的表面积累电荷的情况及其变化规律,为在工作中恰当的使用或改进提供科学依据。     

Controlled Ecological Life Support Systems (CELSS) flight experimentation.

The NASA CELSS program has the goal of developing life support systems for humans in space based on the use of higher plants. The program has supported research at universities with a primary focus of increasing the productivity of candidate crop plants. To understand the effects of the space environment on plant productivity, the CELSS Test Facility (CTF) has been been conceived as an instrument that will permit the evaluation of plant productivity on Space Station Freedom. The CTF will maintain specific environmental conditions and collect data on gas exchange rates and biomass accumulation over the growth period of several crop plants grown sequentially from seed to harvest. The science requirements of the CTF will be described, as will current design concepts and specific technology requirements for operation in micro-gravity.     

An improved Green's function for ion beam transport.

Ion beam transport theory allows testing of material transmission properties in the laboratory environment generated by particle accelerators. This is a necessary step in materials development and evaluation for space use. The approximations used in solving the Boltzmann transport equation for the space setting are often not sufficient for laboratory work and those issues are the main emphasis of the present work. In consequence, an analytic solution of the linear Boltzmann equation is pursued in the form of a Green's function allowing flexibility in application to a broad range of boundary value problems. It has been established that simple solutions can be found for high charge and energy (HZE) ions by ignoring nuclear energy downshifts and dispersion. Such solutions were found to be supported by experimental evidence with HZE ion beams when multiple scattering was added. Lacking from the prior solutions were range and energy straggling and energy downshift with dispersion associated with nuclear events. Recently, we have found global solutions including these effects providing a broader class of HZE ion solutions.     

Degradation of thermal control materials under a simulated radiative space environment

A spacecraft with a passive thermal control system utilizes various thermal control materials to maintain temperatures within safe operating limits. Materials used for spacecraft applications are exposed to harsh space environments such as ultraviolet (UV) and particle (electron, proton) irradiation and atomic oxygen (AO), undergo physical damage and thermal degradation, which must be considered for spacecraft thermal design optimization and cost effectiveness. This paper describes the effect of synergistic radiation on some of the important thermal control materials to verify the assumptions of beginning-of-life (BOL) and end-of-life (EOL) properties. Studies on the degradation in the optical properties (solar absorptance and infrared emittance) of some important thermal control materials exposed to simulated radiative geostationary space environment are discussed. The current studies are purely related to the influence of radiation on the degradation of the materials; other environmental aspects (e.g., thermal cycling) are not discussed. The thermal control materials investigated herein include different kind of second-surface mirrors, white anodizing, white paints, black paints, multilayer insulation materials, varnish coated aluminized polyimide, germanium coated polyimide, polyether ether ketone (PEEK) and poly tetra fluoro ethylene (PTFE). For this purpose, a test in the constant vacuum was performed reproducing a three year radiative space environment exposure, including ultraviolet and charged particle effects on North/South panels of a geostationary three-axis stabilized spacecraft. Reflectance spectra were measured in situ in the solar range (250–2500 nm) and the corresponding solar absorptance values were calculated. The test methodology and the degradations of the materials are discussed. The most important degradations among the low solar absorptance materials were found in the white paints whereas the rigid optical solar reflectors remained quite stable. Among the high solar absorptance elements, as such the change in the solar absorptance was very low, in particular the germanium coated polyimide was found highly stable.     

材料次级电子发射特性对表面充电影响的数值计算研究

表面充电是最早被人们发现的空间环境效应, 是由空间环境引起的航天器异常和故障的主要诱因之一. 采用较精确的金属二次电子发射公式和局部电流平衡模型, 在无光照的情况下, 对不同表面材料及不同几何形体的航天器表面充电电位进行计算, 并绘制了表面材料的充电电位与最大二次电子发射系数之间的关系曲线. 根据数值计算结果及次级电子发射系数和曲线图得知, 航天器阴面充电电位与表面材料的原子序数、最大二次电子发射系数和入射离子引起的次级发射系数均有关. 该计算对航天器表面材料的选取和设计工艺有一定的参考价值.      

载人航天中高温应急的医学对策

载人航天中高温应急事件发生概率较高,应予以充分重视。首先应该克服某些消极认识和不适做法,并指出高温负荷对工效的影响,可转而续发其它事故或未能完成预定飞行计划等问题。文中根据航天实际,提出了若干与高温耐力有关的选训措施和设想,侧重论述了最大氧摄取量（ＶＯ２ｍａｘ）与耐热能力的关系。认为可以采用心功能适应指数与ＶＯ２ｍａｘ的测定作为指标,选拔潜在耐热能力较高的航天员,并在此基础上安排某些体能训练,进一步提高耐热能力,达到在万一发生情况时避免发生事故,圆满完成任务的目的。     

空间站轨道高度选择

有许多因素影响空间站轨道高度的选择,包括:任务要求,辐射环境,微流星和空间垃圾,空间站构型,运载器能力,发射窗口以及空间站的补给要求等。从补给运输系统性能考虑,要求空间站的轨道高度低一些,但是从轨道维持出发,希望空间站轨道高度高一些。该文讨论了补给、轨道维持和太阳活动对轨道高度的影响,给出了空间站的最佳运行高度。文中还以载人飞船和航天飞机为运输系统进行了数值计算,得到的主要结论是空间站的最佳运行高度不是常数,而是随着太阳活动情况和补给频繁次数变化。在太阳活动高年期间,空间站轨道高度应提高。当空间站的补给次数增加时,空间站的最佳运行高度应该下降。     

2000年前我国空间材料科学试验设想

讨论空间环境对材料制备的影响;提出空间材料研究的四个发展阶段和各国空间材料制备现今处在研究发展阶段的观点;分析我国空间材料研究的状况、任务及试验的可能途径;叙述空间材料科学研究的内容;对2000年前我国空间材料试验提出初步设想。