原子氧对航天材料表面的作用与防护 I原子氧与航天材料的作用

综述了低地球轨道环境下原子氧与航天材料的相互作用及其机制，介绍了原子氧敏感性材料以及它们在低地球轨道环境下的降解情况。     

空间材料的原子氧侵蚀理论和预测模型

低地轨道环境中的原子氧对航天器材料的侵蚀导致材料的性能变坏甚至失效，原子氧的侵蚀机理和防护技术是当前空间环境效应研究的热点．在对原子氧效应机理已有理解的基础上，准确预测空间材料在低地轨道环境中由原子氧引起的侵蚀效应，可对设计者在工程选材和飞行器设计提供帮助。本文综述了近年来发展的原子氧与空间材料相互作用的理论模型和侵蚀速率预测模型，并对各种模型进行了分析，也指出了关于原子氧效应的研究重点．     

Mechanically Robust Atomic Oxygen‐Resistant Coatings Capable of Autonomously Healing Damage in Low Earth Orbit Space Environment

Polymeric materials used in spacecraft require to be protected with an atomic oxygen (AO)‐resistant layer because AO can degrade these polymers when spacecraft serves in low earth orbit (LEO) environment. However, mechanical damage on AO‐resistant coatings can expose the underlying polymers to AO erosion, shortening their service life. In this study, the fabrication of durable AO‐resistant coatings that are capable of autonomously healing mechanical damage under LEO environment is presented. The self‐healing AO‐resistant coatings are comprised of 2‐ureido‐4[1H]‐pyrimidinone (UPy)‐functionalized polyhedral oligomeric silsesquioxane (POSS) (denoted as UPy‐POSS) that forms hydrogen‐bonded three‐dimensional supramolecular polymers. The UPy‐POSS supramolecular polymers can be conveniently deposited on polyimides by a hot pressing process. The UPy‐POSS polymeric coatings are mechanically robust, thermally stable, and transparent and have a strong adhesion toward polyimides to endure repeated bending/unbending treatments and thermal cycling. The UPy‐POSS polymeric coatings exhibit excellent AO attack resistance because of the formation of epidermal SiO₂ layer after AO exposure. Due to the reversibility of the quadruple hydrogen bonds between UPy motifs, the UPy‐POSS polymeric coatings can rapidly heal mechanical damage such as cracks at 80 °C or under LEO environment to restore their original AO‐resistant function.     

LEO大型载人航天器主动电位控制技术进展

LEO大型载人航天器主动电位控制技术可以有效的防护空间等离子体充放电效应对于航天器造成的安全隐患,确保航天员出舱和航天器空间对接作业的顺利完成。通过研究LEO大型载人航天器与空间等离子体的相互作用,从原理上认识空间等离子体对于航天器的危害程度。分析回顾国外主动电位控制技术在LEO大型载人航天器上的成功应用及发展情况,得出启示和初步的主动电位控制系统设计设想。对比国内外主动电位控制领域的核心技术,对主动电位控制技术的发展和应用提出了建议。     

原子氧防护涂层技术研究

原子氧是低地球轨道主要的残余气体粒子,其化学性质非常活泼,是极强的氧化剂,会对空间材料的性能产生严重的影响。介绍了低地球轨道的原子氧环境及原子氧防护方法;对有机、无机和复合原子氧防护涂层的优缺点、研究进展情况以及空间应用情况进行了详尽的阐述;最后分析了原子氧防护的发展方向。     

High velocity impact characteristics of MWNT added CFRP at LEO space environment

In this paper, multi-wall carbon nanotube (MWNT) added carbon fiber reinforced plastics (CFRP) composites are suggested as solutions to improve the impact energy absorbing capability of CFRP for spacecraft application because it was proven that the resistance against LEO environment and the quasi-static material properties of CFRP can be improved by adding MWNT in previous papers. To verify the effect of MWNT on the impact energy absorbing capability of composite materials, normal CFRP and MWNT-reinforced CFRP were prepared and tested by using a two-stage light gas gun that can accelerate an aluminum ball of a diameter of 5.56 mm to 1 km/s. And the applicability of MWNT against hypervelocity impact of space debris was studied. In addition, accelerated ground simulation experiments were performed for each material model to simulate the aging of composite materials to verify the effect of LEO environmental aging on impact absorbing capability of composites. For the aging experiment, the impact specimens were simultaneously exposed to high vacuum, atomic oxygen, ultra violet light, and thermal cycling. After being exposed to simulated LEO environment, high velocity impact tests were performed for each material. As a result, MWNT did not have a significant improvement on the impact energy absorbing capability of CFRP under high velocity impact, even though the quasi static material properties are improved by adding MWNT. This is caused by the early generation of fiber breakages on the impact surface before enough generation of progressive failure which is one of the impact energy absorbing mechanism. Similarly, MWNT has less effect on the impact energy absorbing capability of CFRP under LEO environment.     

真空-紫外线对空间材料降解的研究进展

综述了真空-紫外线的空间环境效应及真空-紫外线对空间材料的降解作用.真空-紫外线辐射使材料表面粗糙度增大,表面成分、结构发生变化,机械性能和光学性能下降,同时真空-紫外还可以与原子氧产生协同效应,加速材料的降解.     

Spacecraft electrical power subsystem: Failure behavior, reliability, and multi-state failure analyses

This article investigates the degradation and failure behavior of spacecraft electrical power subsystem (EPS) on orbit. First, this work provides updated statistical reliability and multi-state failure analyses of spacecraft EPS and its different constituents, namely the batteries, the power distribution, and the solar arrays. The EPS is shown to suffer from infant mortality and to be a major driver of spacecraft unreliability. Over 25% of all spacecraft failures are the result of EPS failures. As a result, satellite manufacturers may wish to pursue targeted improvement to this subsystem, either through better testing or burn-in procedures, better design or parts selection, or additional redundancy.Second, this work investigates potential differences in the EPS degradation and failure behavior for spacecraft in low earth orbits (LEO) and geosynchronous orbits (GEO). This analysis was motivated by the recognition that the power/load cycles and the space environment are significantly different in LEO and GEO, and as such, they may result in different failure behavior for the EPS in these two types of orbits. The results indicate, and quantify the extent to which, the EPS fails differently in LEO and GEO, both in terms of frequency and severity of failure events. A casual summary of the findings can be stated as follows: the EPS fails less frequently but harder (with fatal consequences to the spacecraft) in LEO than in GEO.     

溶胶-凝胶法制备抗原子氧涂层及性质研究

采用有机无机复合的溶胶-凝胶方法,合成了用于聚合物表面保护层的前驱溶液.采用旋转涂覆方法,将前驱溶液涂覆于聚酰亚胺基片上,制成了表面涂层.将所制得的相应涂层分别进行原子氧暴露试验,其表面形貌的变化通过扫描电镜观测.结果表明,在原子氧辐照下,无保护的聚酰亚胺表面已非常粗糙,与辐照前的光滑表面形成显著的对比.而涂覆有保护层的表面,原子氧辐照前后却没有变化.这表明使用这种有机无机复合的溶液涂层具有很好的抗原子氧能力.     

聚合物材料表面原子氧防护技术的研究进展

聚合物材料具有质量轻、强度高等优点, 常被用作航天器表面的复合结构基材。原子氧是低地球轨道空间中成分含量最高的粒子之一, 对暴露在航天器表面的聚合物材料易形成大通量、高能量轰击, 造成其表面氧化侵蚀和质量损失, 使聚合物材料的性能发生不同程度的衰退, 也是导致航天器件可靠性降低、工作寿命缩短的主要环境因素。本文对当前国内外通用的几种聚合物材料表面原子氧防护技术进行了整理归纳, 其中表面化学改性方法结合了体材改性和常用防护涂层的优点, 得到的有机/无机复合改性防护层具有较好的综合防护性能。文中分析了近年来由计算模拟法开展原子氧与表面防护材料相关作用机理的研究, 指出采用计算模拟结合试验的研究方法, 有可能从本质上揭示复合改性层与原子氧的作用机理, 从而促进原子氧防护材料与防护技术的研究发展。     

卫星尾迹带电数值模拟研究

基于运行于低轨道"冷稠"等离子体环境中的卫星可以在其尾部形成电子和离子浓度不等量的尾迹,尾迹效应可严重影响卫星的表面不等量带电。因此,在分析卫星尾迹效应物理机制的基础上,建立了尾迹效应的二维简单计算模型,利用PIC(particle-in-cell)方法编制二维模拟程序,计算了不同尺寸卫星的尾迹电位分布和高能电子注入下的卫星尾迹电位分布,从而得到了卫星尾迹带电和卫星尺寸及高能电子注入之间的关系。     

Damage behavior of atomic oxygen on CVD SiC coating-modified carbon/carbon composite in low earth orbit environment

In this work, samples of carbon/carbon (C/C) and chemical vapor deposited (CVD) SiC-coated C/C samples were investigated to understand the AO damage mechanism in low Earth orbit (LEO) environment. The ground-based simulated atomic oxygen (AO) generator was employed. Results indicate that the CVD SiC coating exhibited improved radiation resistance properties against AO radiation as evidenced by a 16% better strength retention ratio, 60% less mass ablation, and increased strength stability. The magnitude of these influences affected the surface morphology, as observed by scanning electron microscopy (SEM) and surface resistance meter test results. The variations in the surface constituents were confirmed by X-ray diffraction (XRD) and X-ray photoelectron spectroscopy (XPS) results. The main products left on surface after AO exposure are SiO₂ and SiC_xO_y film. Additionally, Si atoms are found to be the preferential reacting element in the SiC coating, and this process is accompanied by graphite precipitation, grain growth, and crack necking. Also, the damage mechanism of the AO-exposed SiC coating was revealed and is discussed.     

Atomic oxygen effects on POSS polyimides in low earth orbit

Kapton polyimde is extensively used in solar arrays, spacecraft thermal blankets, and space inflatable structures. Upon exposure to atomic oxygen in low Earth orbit (LEO), Kapton is severely eroded. An effective approach to prevent this erosion is to incorporate polyhedral oligomeric silsesquioxane (POSS) into the polyimide matrix by copolymerizing POSS monomers with the polyimide precursor. The copolymerization of POSS provides Si and O in the polymer matrix on the nano level. During exposure of POSS polyimide to atomic oxygen, organic material is degraded, and a silica passivation layer is formed. This silica layer protects the underlying polymer from further degradation. Laboratory and space-flight experiments have shown that POSS polyimides are highly resistant to atomic-oxygen attack, with erosion yields that may be as little as 1% those of Kapton. The results of all the studies indicate that POSS polyimide would be a space-survivable replacement for Kapton on spacecraft that operate in the LEO environment.     

FG/CS逐层复合保鲜涂膜对三文鱼鱼片品质的影响

目的为了提高复合涂膜对三文鱼鱼片的保鲜性能,获得具有高效长效缓释性能的生物保鲜材料。方法以亚麻籽胶(FG)和壳聚糖(CS)为成膜材料,丁香酚(EG)和月桂精油(LEO)为保鲜剂,采用流延法制备逐层FG/CS+EG/FG+LEO复合涂膜。以三文鱼鱼片为研究对象,评估复合涂膜的保鲜性能。结果 FG/CS+EG/FG+LEO复合涂膜能够显著抑制三文鱼鱼肉中微生物的生长,提高鱼肉持水力,延缓脂肪氧化、蛋白质分解和色差值的变化进程。结论 EG和LEO复配使用具有一定的协同增效作用,同时,多层涂膜组成的缓释体系有效地延长了生物保鲜剂的作用时间,使EG和LEO对鱼片的保鲜效果更好,其中FG/CS+EG/FG+LEO复合涂膜的保鲜效果最优,可使生鲜三文鱼鱼片的货架期从7 d延长至13 d。     

Graphene-reinforced epoxy resin with enhanced atomic oxygen erosion resistance

Atomic oxygen (AO) is a dominant component of the low earth orbit and can erode most spacecraft material. We demonstrated the application of graphene to enhance AO erosion resistance of spacecraft polymers. Graphene-reinforced epoxy resin nanocomposites were prepared by solidification of epoxy resin in solution with dispersed graphene flakes and their AO erosion resistance was investigated in a plasma-type ground-based AO effects simulation facility. The nanocomposites were characterized by X-ray diffraction, scanning electron microscopy, thermogravimetric analysis, and X-ray photoelectron spectroscopy. Results based on erosion kinetics revealed that a 46 % decrease in mass loss and a 47 % decrease in erosion yield were achieved by addition of only 0.5 wt% of graphene. Further analysis of the surface morphology and composition showed that the graphene nanoflakes could serve as barriers to protect underneath from AO erosion. Thus, this approach provides a novel route for improving durability and reliability of spacecraft material, especially polymers.     

TiNi基形状记忆合金的辐照效应

材料辐照效应是入射粒子与物质交互作用造成的物质微观组织结构与宏观性能的变化。辐照效应不仅是改善材料表面性能的重要手段,而且也是特殊环境应用材料可靠性评价的重要组成部分。TiNi基形状记忆合金是一种重要的金属智能材料,具有独特的形状记忆效应和超弹性,已在卫星、空间站等航天器以及生物医学中广泛应用。本文阐述了Ti-Ni基形状记忆合金在空间粒子(质子、电子)以及离子辐照改性的研究进展,辐照效应会对TiNi合金的微观组织结构产生影响,进而改变合金的相变行为和力学行为。然而目前关于TiNi基合金的辐照效应的研究仍处于起步阶段,组织结构和相变行为的变化规律和机理还未研究清楚,有关形状记忆效应的研究较少,仍需深入研究辐照参数、组织结构、相变行为和功能特性之间的内在联系。     

空间材料二次电子发射特性测试

空间材料的二次电子发射系数是表征航天器表面充电状态的重要参数 ,对于卫星表面带电的预测及卫星防带电设计选材具有重要的作用。为了测量空间材料二次电子发射特性 ,研制了专门的测试装置。介绍了该实验装置的主要结构、性能及技术指标等 ,通过应用计算机数据采集系统 ,并研制专门的数据处理软件 ,提高了装置的自动测量能力。实验说明 ,该装置用于空间材料的二次电子发射特性测试中测量方便、准确     

原子氧环境中聚酰亚胺的质量变化和侵蚀机制

用石英晶体微天平(QCM)原位监测并研究了聚酰亚胺薄膜在地面原子氧模拟装置中暴露时的质量变化.结果表明,聚酰亚胺薄膜在较低的原子氧束流通量暴露的初期,试样的质量先增加后降低,质量的降低与暴露的时间成正比.在高原子氧束流通量暴露的初期,试样质量的增加不明显,甚至一开始就发生稳态氧化失重.实验数据拟合的结果表明,原子氧对聚合物造成的侵蚀主要发生在有氧原子吸附的表面.质量的增加是由于较低的原子氧通量没有能完全氧化聚合物的表面.原子氧对聚合物材料的侵蚀机制服从Langmuir吸附理论.     

铝膜反射镜空间环境适应性研究

铝膜反射镜是反射式空间聚光太阳电池阵的重要组成部分。通过对铝膜反射镜电子、质子、紫外、原子氧环境等一系列辐照及环境试验,研究和考察了铝膜反射镜反射率的变化和空间环境适应性。研究结果表明,铝膜反射镜适应地球同步轨道环境条件下,反射镜平均反射率在15年寿命末期大于75%;在低地球轨道环境中有必要对铝膜反射镜进行抗原子氧侵蚀防护。     

The SPQR experiment: detecting damage to orbiting spacecraft with ground-based telescopes

The objective of the Specular Point-like Quick Reference (SPQR) experiment was to evaluate the possibility of improving the resolution of ground-based telescopic imaging of manned spacecraft in orbit. The concept was to reduce image distortions due to atmospheric turbulence by evaluating the Point Spread Function (PSF) of a point-like light reference and processing the spacecraft image accordingly. The target spacecraft was the International Space Station (ISS) and the point-like reference was provided by a laser beam emitted by the ground station and reflected back to the telescope by a Cube Corner Reflector (CCR) mounted on an ISS window. The ultimate objective of the experiment was to demonstrate that it is possible to image spacecraft in Low Earth Orbit (LEO) with a resolution of 20 cm, which would have probably been sufficient to detect the damage which caused the Columbia disaster. The experiment was successfully performed from March to May 2005. The paper provides an overview of the SPQR experiment.