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A novel ion-beam surface treatment process with simultaneous surface renewal (IB/SSR) providing charge-dissipative properties to the treated surfaces was developed at ITL and successfully used for treatment of both sides of variously shaped and sized flat conductor cables (FCC) that are being used in various applications in aerospace, space and commercial programs. The results of surface resistivity (SR) measurements of the front side of FCC’s used as interconnects in solar panel arrays on satellites in Geostationary (GEO) orbit averaged around 10 MΩ/sq for short FCC units and around 8 MΩ/sq for long units. The SR values for back sides averaged around 18 MΩ/sq for both short and long FCCs. These values remained unchanged during ~ 1 month storage of the treated FCCs at lab conditions, and after a following 2-2.5 year’s storage. Extended long-term ground-based GEO environment simulation testing experiments (15 years space equivalent) that involved simultaneous exposure to all three GEO environmental factors, i.e. protons, electrons, and UV have been performed on two specially selected FCC sets. These sets included pristine and IB/SSR-treated FCCs, with both front and back FCC surfaces being exposed. It was demonstrated that the surface conductivity obtained on the insulating space polymer films is almost insensitive to space radiation during the 15 years in GEO. It was also shown that the long-term influence of GEO radiation on thermal optical characteristics of both FCCs sides does not significantly differ for pristine and ion-beam treated samples., Новий процес обробки поверхні іонно-променевою поверхнею з одночасним оновленням поверхні (IB / SSR), що забезпечує дисипативні властивості заряду оброблених поверхонь, був розроблений в ITL і успішно використаний для обробки обох сторін різної форми та розміру плоских провідних кабелів використовуються для різних застосувань в аерокосмічній, космічній та комерційній програмах. Результати вимірювань поверхневого опору (SR) на лицьовій стороні FCC, що використовуються як взаємозв'язки в масивах сонячних панелей на супутниках на геостаціонарній орбіті (GEO), складали в середньому близько 10 МОм / кв. Для коротких блоків FCC та близько 8 МОм / кв. Для довгих блоків. Значення SR для тильних сторін у середньому становили близько 18 МОм / кв. Для коротких і довгих FCC. Ці значення залишались незмінними протягом ~ 1 місяця зберігання оброблених FCC у лабораторних умовах та після наступного 2-2,5 року зберігання.Розширені довготермінові експерименти з моделювання навколишнього середовища GEO (15-річний космічний еквівалент), які передбачали одночасний вплив усіх трьох факторів середовища GEO, тобто протонів, електронів та УФ, були проведені на двох спеціально підібраних наборах FCC. Ці набори включали незаймані та оброблені IB / SSR FCC, причому як передня, так і задня поверхня FCC були виставлені. Було продемонстровано, що поверхнева провідність, отримана на ізолюючих космічних полімерних плівках, майже не чутлива до космічного випромінювання протягом 15 років у ГЕО. Було також показано, що довгостроковий вплив ГЕО-випромінювання на теплооптичні характеристики обох сторін ФКК суттєво не відрізняється для зразків, що обробляються первинними та обробленими іонним пучком., Новый процесс ионно-лучевой обработки поверхности с одновременным обновлением поверхности (IB / SSR), обеспечивающий рассеивающие заряд свойства обрабатываемых поверхностей, был разработан в ITL и успешно использован для обработки обеих сторон плоских проводников разной формы и размеров (FCC), которые используются в различных приложениях в аэрокосмических, космических и коммерческих программах. Результаты измерений удельного поверхностного сопротивления (SR) передней стороны панелей FCC, используемых в качестве межсоединений в массивах солнечных панелей на спутниках на геостационарной (GEO) орбите, составили в среднем около 10 МОм / кв. Для коротких блоков FCC и около 8 МОм / кв. Для длинных блоков. Значения SR для задней стороны в среднем составляют около 18 МОм / кв как для коротких, так и для длинных FCC. Эти значения оставались неизменными в течение ~ 1 месяца хранения обработанных FCC в лабораторных условиях и после следующих 2-2,5 лет хранения.На двух специально отобранных наборах FCC были проведены расширенные долгосрочные эксперименты по моделированию среды на ГСО (космический эквивалент 15 лет), которые включали одновременное воздействие всех трех факторов окружающей среды ГСО, то есть протонов, электронов и УФ-излучения. Эти наборы включали первичные и обработанные IB / SSR FCC, с открытыми как передняя, так и задняя поверхности FCC. Было продемонстрировано, что поверхностная проводимость, полученная на изоляционных космических полимерных пленках, практически нечувствительна к космическому излучению за 15 лет работы в GEO. Также было показано, что долговременное влияние излучения GEO на теплооптические характеристики обеих сторон ГЦК существенно не различается для исходных и обработанных ионным пучком образцов.

The goals of the 10th International Space Conference on "Protection of Materials and Structures from Space Environment" ICPMSE-10J, since its inception in 1992, have been to facilitate exchanges between members of the various engineering and science disciplines involved in the development of space materials, including aspects of LEO, GEO and Deep Space environments, ground-based qualification, and in-flight experiments and lessons learned from operational vehicles that are closely interrelated to disciplines of the atmospheric sciences, solar-terrestrial interactions and space life sciences. The knowledge of environmental conditions on and around the Moon, Mars, Venus and the low Earth orbit as well as other possible candidates for landing such as asteroids have become an important issue, and protecting both hardware and human life from the effects of space environments has taken on a new meaning in light of the increased interest in space travel and colonization of other planets. And while many material experiments have been carried out on the ground and in open space in the last 50 years (LDEF, MEEP, SARE, MISSE, AOP, DSPSE, ESEM, EURECA, HST, MDIM, MIS, MPID, MPAC and SEED), many questions regarding the environmental impact of space on materials remain either poorly understood or unanswered. The coming generations of scientists will have to continue this work and tackle new challenges, continuing to build the level of confidence humans will need to continue the colonization of space. It is hoped that the proceedings of the ICPMSE-10J presented in this book will constitute a small contribution to doing so.

International audience; Results of making surfaces of flexible cable conductors, used for solar arrays in geostationary orbit, charge dissipative by a specially developed method of ion-beam surface treatment with simultaneous surface renewal are presented. All flexible cable conductor surfaces, including those with rough morphology and foreign inclusions, achieved surface resistivity of ∼10–20 MΩ/sq. at room temperature and kept charge dissipation in a wide +/-150 °C space-related temperature range. A testing space qualification program confirmed all treated flexible cable conductors being resistant to thermal cycling and humidity, mechanically durable, and radiation resistant in geostationary orbit. All flexible cable conductors successfully survived 15 years space-equivalent geostationary orbit imitating testing. A comparison of beginning- and end-of-life characteristics of original and treated flexible cable conductors after this testing confirmed additional decrease of surface resistivity and almost equal final thermal-optical characteristics. Electrostatic discharge testing in a geostationary orbit charging testing facility demonstrated the long-lasting charge-dissipation properties of the treated flexible cable conductors, fully preventing them from building up critical charges in geostationary orbit environment, when a reliable grounding path is ensured for the surfaces.

Spacecraft operating in the low Earth orbit (LEO) are exposed to an environment characterized by very low pressure, various atomic species, temperature extremes, ultraviolet (UV) radiation, electromagnetic radiation and atomic oxygen (AO), which is produced by the dissociation of molecular oxygen by UV radiation. The destructive influence of AO on polymer-based materials and composites and the synergistic effects between AO and other environmental factors have been dramatically demonstrated in LEO flights and ground-based simulators. This paper investigates the effects of contamination, structure and the synergism between temperature and AO fluence on polymer-based materials, and provides an overview of the recent developments in the design and use of protective coatings for polymer and composite materials in the LEO environment and their testing in ground-based space environment simulators. Three trends in protective coatings research are identified and discussed: (a) the improvement of technologies for high-performance oxide-based coatings; (b) self-healing coatings based on special semi-organic polymers; (c) protective multilayered structures. An evaluation is made of the properties and behaviour of different protective coatings on the polymers and composite materials used in spacecraft applications.

Many polymer-based materials degrade in low earth orbit (LEO), mainly due to the damaging environmental effects of hyperthermal or fast atomic oxygen of energy E ∼ 5 eV and solar vacuum ultraviolet radiation. Fast atomic oxygen fluxes of similar energies are generated now in ground-based facilities that are used for accelerated testing of materials. This paper presents a brief overview of the effects of interaction of fast atomic oxygen fluxes with polymer-based materials in the LEO space environment and in ground-based simulators, and discusses a few possible applications of fast atomic oxygen fluxes. Such applications can lead to considerable advantages over plasma treatment, aimed at improvement of adhesion-related and optical properties of polymer-based materials, high-quality precise photoresist etching and passivative oxidation of advanced semiconductor materials, and modified or entirely new surface properties of biomaterials and chemical sensors.

This paper is an overview of instrumentation developed and created by ITL Inc. for simulated testing and performance evaluation of spacecraft materials, structures, mechanisms, assemblies and components in different space and planetary environments. The LEO Space Environment Simulator allows simulation of the synergistic effect of ultra-high vacuum conditions, 5 eV neutral atomic oxygen beams, Vacuum-Ultraviolet (VUV) and Near-Ultraviolet (NUV) radiation, and temperature conditions. The simulated space environmental conditions can be controlled in-situ using a quadruple mass-spectrometer, Time-of-Flight technique, as well as Quartz Crystal Microbalance sensors. The new NUV System is capable of delivering an NUV power intensity of up to 10 Equivalent Suns. The design of the system uses horizontal orientation of the 5 kW Mercury lamp, focusing of NUV radiation is achieved due to a parabolic reflector. To address the Lunar/Martian surface environments, the Planetary Environmental Simulator/Test Facility has been developed and built to allow for physical evaluation of the effects of the Lunar/Martian dust environments in conjunction with other factors (ultra-high vacuum or planetary atmospheric conditions, VUV/NUV radiation, thermal cycling, and darkness). The ASTM E 595/ASTM E 1559 Outgassing Test Facility provides the means for the outgassing test of materials with the objective to select materials with low outgassing properties for spacecraft use and allows to determine the following outgassing parameters: Total Mass Loss, Collected Volatile Condensable Materials, and Water Vapor Regained.

Surface engineering techniques are being used extensively in the aerospace and space industries as well as a variety of other industries to develop, maintain, or change a wide range of functional properties, including physical, chemical, electrical, electronic, magnetic, mechanical, wear-resistant and corrosion-resistant properties. An overview of the present, state-of-the-art, situation in the field of surface modification of space materials is presented. A number of surface modification technological solutions that differ from the traditional protective coating approaches are discussed that change the surface properties of treated materials thus protecting them from the hazards of low earth orbit (LEO) and geostationary orbit (GEO) environments or impairing new functional properties to space materials used in LEO/GEO, with examples of their testing, characterization and applications provided. Keywords: surface modification; space environment; low earth orbit; photosil; Materials for LEO and GEO orbits; surface engineering; space materials; thermal control paints; ion implantation; implantox; carbosurf; ion-beam texturing; charge dissipative polymer surfaces

A space materials exposure experiment was condcuted on the exterior of the Russian Service Module (SM) of the International Space Station (ISS) using the Micro‐Particles Capturer and Space Environment Exposure Device (MPAC&SEED) of the Japan Aerospace Exploration Agency (JAXA). Results reveal artificial environment effects such as sample contamination, attitude change effects on AO fluence, and shading effects of UV on ISS. The sample contamination was coming from ISS components. The particles attributed to micrometeoroids and/or debris captured by MPAC might originate from the ISS solar array. Another MPAC&SEED will be aboard the Exposure Facility of the Japanese Experiment Module, KIBO Exposure Facility (EF) on ISS. The JEM/MPAC&SEED is attached to the Space Environment Data Acquisition Equipment‐Attached Payload (SEDA‐AP) and is exposed to space. Actually, SEDA‐AP is a payload on EF to be launched by Space Shuttle flight 2J/A. In fact, SEDA‐AP has space environment monitors such as a high‐energy particle monitor, atomic oxygen monitor, and plasma monitor to measure in‐situ natural space environment data during JEM/MPAC&SEED exposure. Some exposure samples for JEM/MPAC&SEED are identical to SM/MPAC&SEED samples. Consequently, effects on identical materials at different positions and operation periods of ISS will be evaluated. This report summarizes results from space environment monitoring samples for atomic oxygen analysis on SM/MPAC&SEED, along with experimental plans for JEM/MPAC&SEED.

Atomic oxygen (AO) is among the predominant factors in Low Earth Orbit (LEO) space environment. Ground‐based laboratory AO exposure testing was performed to investigate interaction between atomic oxygen and materials that were intended for use in future missions on LEO spacecraft. Two types of adhesive materials, i.e., E‐32 epoxy and GS414 silicone were tested in Atomic Oxygen Test Facility at the Beijing Institute of Spacecraft Environment Engineering (BISEE). The effective atomic oxygen fluence in the conducted tests was approximately 1.4×1021 atoms/cm2 which is close to the fluence of a two‐year exposure in LEO orbit. Significant mass losses of epoxy adhesive materials were detected after the exposure to atomic oxygen, but relatively small mass changes were found in silicone samples. The erosion yields of epoxy samples were from 3.2×10−24 cm3/atom to 3.8×10−24 cm3/atom. Surface bleaching by atomic oxygen was found in epoxy samples. The surface on silicone sample remained glossy after AO exposure. Both ...

This report presents the results of an investigation of thermo‐optical characteristics, i.e. the total solar absorptance, αs and solar emittance, e of thermal control coatings (TCC) exposed to the space environment at a geostationary orbit (GEO). Experiments results from samples that were flown on space vehicles (SV) “Yamal‐100” and “Yamal‐200” for 8 and 4 flight years, respectively, are presented here. The results from experiments flown for 6 and 2 flight years were presented in an earlier article [1].The αs and e characteristics were measured by a calorimetric method through monitoring the temperatures of the coating samples that were used as microcalorimeters (MC) and a mathematical treatment of the temperature data. The temperature sensors were attached to the back side of the flown samples.

We studied measurement of secondary electron emission (SEE) of metal and insulating materials used for satellite thermal insulation or other such purposes. The SEE yield measurement is very important for analyzing charge accumulation on satellite surfaces for a space environment because electron emission related to irradiated electrons influences the amount of surface charge. Therefore, we tried to measure the SEE yield. Furthermore, we must consider degradation phenomena of surface materials for spacecraft caused by radioactive rays. According to the degradation of materials, those SEE yields might change compared to a non‐degradation sample. Therefore, we tried to measure the SEE yields of surface materials for spacecraft which are treated using the degradation process. For preparing a degradation sample, those samples were irradiated by an electron beam and UV to simulate degradation in a space environment. We take three irradiation conditions for electron beam and UV irradiation that related with GEO ...

The Materials Exposure and Degradation Experiment (MEDET) was recently launched to the ISS on Space Shuttle Flight IE, as part of the EuTEF payload on the external payload facility of ESA’s Columbus module. The experiment will operate in‐orbit for at least 1.5 years, and has the overall objectives of evaluating the effects of the complex low Earth orbit space environment on material properties, investigating material degradation due to contamination, characterising the local ISS environment and measuring the local micro‐particle flux. This paper gives a brief overview of the experiment function and the material samples which are being exposed, before presenting some of the early flight data. In this phase of the mission, all of the instruments are operating successfully, and continuously acquiring data. The preliminary results mainly concern the environmental sensors, which are operating at relatively high acquisition rates (e.g. one reading every few seconds). It has been shown that the docking of the Space Shuttle to the ISS has a significant effect on the local pressure environment. The more complex degradation experiments are acquiring at much slower rates (e.g. one reading per day) and several more months of space exposure will be required before sufficient data is generated to reach conclusions about the behaviour of the materials. However, preliminary data is presented.

There have been five Materials International Space Station Experiment (MISSE) passive experiment carriers (PECs) (MISSE 1–5) to date which have been launched, exposed in space on the exterior of International Space Station (ISS) and then returned to Earth for analysis. An additional four MISSE PECs (MISSE 6A, 6B, 7A & 7B) are in various stages of completion. The PECs are two‐sided suitcase size sample carriers that are intended to provide information on the effects of the low Earth orbital environment on a wide variety of materials and components. As a result of post retrieval analyses of the retrieved MISSE 2 experiments and numerous prior space experiments, there have been valuable lessons learned and needs identified that are worthy of being documented so that planning, design, and analysis of future space environment experiments can benefit from the experience in order to maximize the knowledge gained. Some of the lessons learned involve the techniques, concepts, and issues associated with measuring atomic oxygen erosion yields. These are presented along with several issues to be considered when designing experiments, such as the uncertainty in mission duration, scattering and contamination effects on results, and the accuracy of measuring atomic oxygen erosion.

Influence of a ground‐simulated space environment on a solid lubricant was compared to that of the real space environment. The tested lubricant that has been used for space applications was a bonded MoS2 film with organic binder. The film was irradiated individually with atomic oxygen (AO), ultraviolet rays (UV), and electron beam (EB). The fluencies of these space environment factors corresponded to exposure to the LEO environment around the International Space Station (ISS) in the Space Environment Exposure Device (SEED) experiment to about 1,2, and 3 years. Friction tests in vacuum and surface analyses were carried out for the samples. Tribological behavior of the different samples was measured using a classical reciprocating pin‐on‐flat friction test. Furthermore, XPS analysis of the film surface and the rubbing tracks was performed on the samples. Results show that due to AO irradiation, the friction coefficient decreased at an early stage of the tests that was similar to the results obtained on film...

In 2007 the scientists at Skobeltsyn Institute of Nuclear Physics Moscow State University in close cooperation with experts from many space industry organizations, institutes of Russian Academy of Science and universities prepared and published a two‐volume scientific handbook Space Model. Nearly 180 authors from 50 different organizations have taken part in creating the Space Model handbook. The total volume of the handbook amounts to more than 2000 pages.In the 1st volume the physical conditions in the outer space are described, some computational models are considered, various reference data for computing are presented. The 2nd volume is devoted to the analysis of the space environment effects on spacecraft materials and subsystems, and of ground‐based and space testing methods. The influence of spacecraft and rocket on the near‐Earth space is also discussed.The handbook is intended for specialists of space industry and students. The paper deals with the content of the handbook and the possibilities of...

Investigation of paint thermal control coatings (TCCs) with new components that are intended for spacecraft operating at high‐altitude orbits (GEO, HEO) has been carried out. Changes of optical properties under combined exposure to space environment have been measured.

This paper describes densely‐packed materials that change their stiffness under exposure to ionizing radiation. The prepreg materials additionally curable under radiation exposure can be used for fabrication of large‐size articles (e.g., supporting structures of large space antennas on space vehicles and aircraft, protective screens of spacecraft and protective structures on the Moon surface) transformed in a space environment (UV radiation, vacuum) and acquiring stiffness (shape stability) due to space factors. The materials additionally cured under radiation exposure can be obtained using specially developed complex binders with components of different sensitivity to ionizing radiation and curable via different mechanisms.

This paper presents a comparison study of single and combined space environmental effects by electrons, protons and near ultraviolet (NUV) radiation on thermal control coatings. The space environment includes many hazardous factors. Because of synergistic effects among different environmental factors and the expensive nature of the open space experiments, ground‐based combined environmental test methods are necessary to simulate orbital environmental effects. In many cases, the combined environmental effect from two or more factors is not equal to the sum of single environmental effects. By studying the effects from single environmental factors, a better knowledge of their influence on the degradation of materials could be acquired. Space environmental degradation of thermal control coatings of S781 white paint, SR107‐ZK white paint, silvered FEP, and OSR used on the outer satellite surfaces was simulated by exposing them to combined irradiation with electrons, protons and NUV. In addition, irradiation with single factors with the same parameters was performed for comparison studies. Low energy proton irradiation has been found to affect the thermal control coatings the most. The effects from combined irradiation were found to be lower than from the sum of single environmental factors.

Dielectric materials are widely used in space environment. When they are irradiated, charges will accumulate in the bulk and on the surface of the material, leading to pulse discharge events that can cause permanent changes in their physical and chemical structure. In this paper, a special method called PEA (pulse electro‐acoustic) was used to measure and analyze the space charging of several dielectric materials after they have been irradiated by different high‐energy electron beams.

The paper discusses the peculiarities of ground‐based testing of nanomaterials and spacecraft nanoelements for their durability under the influence of the space environment and the mathematical simulations of processes associated with this influence. In both cases it is necessary to take into account quantum phenomena that determine initial properties of nanomaterials and nanostructures and possible changes in them. The paper presents examples of using the physical and mathematical models, the software and the facilities at Skobeltsyn Institute of Nuclear Physics (SINP) for studying materials behavior in space environment.

Many different passive thermal control materials were flown as part of the Materials on International Space Station Experiment, including inorganic coatings, anodized aluminum, and multi‐layer insulation materials. These and other material samples were exposed to the low Earth orbital environment of atomic oxygen, ultraviolet radiation, thermal cycling, and hard vacuum, though atomic oxygen exposure was limited for some samples. Materials flown on MISSE‐1 and MISSE‐2 were exposed to the space environment for nearly four years. Materials flown on MISSE‐3, MISSE‐4, and MISSE‐5 were exposed to the space environment for one year.Solar absorptance, infrared emittance, and mass measurements indicate the durability of these materials to withstand the space environment. Effects of short duration versus long duration exposure on ISS are explored, as well as comparable data from previous flight experiments, such as the Passive Optical Sample Assembly (POSA), Optical Properties Monitor (OPM), and Long Duration Expos...

An effort is underway to merge two significant materials databases to aid the international space communities. The Russian Karpov Institute Database consists primarily of data for organic materials for space and ground-based applications. The North American SOLEXISTM database from Stellar Optics Research International Corporation (SORIC) consists primarily of data for inorganic materials, and many black, white, reflective and transmissive organic materials, for space and ground-based applications. The Karpov Institute Database on radiation stability of organic material has incorporated the results of tests conducted at Karpov Institute over the last 40 years on orders from enterprises of the Soviet space and defense industries. Test results for 638 materials were selected for inclusion into the Database, divided into fourteen categories: adhesives; coatings; composite; compounds and compositions; films; foamed materials; hermetics; inorganic materials; paints, lacquers and enamels; plastics; products; resins

Many organic-based materials exposed to low Earth orbit (LEO) environment undergo dramatic changes and irreversible degradation of physical characteristics. While many protective schemes are used to reduce the effects of LEO environment, protection of such materials in LEO still remains a major challenge, especially for future long duration missions or space stations.In addition to the traditional protective coating approaches, surface modification processes were proposed and successfully used as an approach to protect polymers, thermal control paints and other components and structures from LEO environment. Among them two surface modification processes, the Photosil™ and the Implantox™ that used new approaches in silicon functionalization, as in the Photosil™, and a modified ion implantation process, as in the Implantox™ allowed to incorporate up to 36 at.% of Si into the upper surface layer regions of the treated polymers, composite materials, thermal control paints and other high-performance organic materials.The tests conducted in plasma and fast atomic oxygen (FAO) beam facilities at comparable to LEO fluencies (∼ (1–2)·1020 at.O/cm2 ) demonstrated erosion yields lower than −10−26 cm3at, unchanged thermal optical properties, where important, and excellent thermal match between the treated layers and the bulk of the treated materials. After FAO testing, the Implantox™ treated samples were clear and transparent, with a glassy-like shiny surface with no signs of any surface erosion.

Acknowledgements. Introduction. Organizing Committee. Section A: AO/VUV Effects, Evaluation and Modeling. 1. Monte Carlo Computational Modeling of the Energy Dependence of Atomic Oxygen Undercutting of Protected Polymers B.A. Banks, et al. 2. Dynamics of Atomic-Oxygen-Induced Degradation of Materials T.K. Minton, et al. 3. Generalization of the Predictive Model of Erosion of Carbon-Based Materials by Atomic Oxygen J.I. Kleiman, et al. 4. Spectroscopic Ellipsometry Characterization of Polymers Modified by Atomic Oxygen and Ultraviolet Radiation C.L. Bungay, et al. 5. Effect of Atomic Oxygen Exposures on the Tribological Properties of Molybdenum Disulfide Lubricants M. Tagawa, et al. 6. Influence of Shielding Upon the Structure and Properties of Polymer Composite Materials, Exposed on the Surface of the Mir Orbital Complex O.V. Startsev, et al. 7. Cleanliness Support of Vehicle Fairings for Spacecraft V. Sitalo, V. Tikhiy. 8. In situ XPS Studies of Kapton Exposed to 5 eV Atomic Oxygen E. Grossman, et al. Section B: Instrumentation, Sensors, New Technologies. 9. A Low Cost, Lightweight Reusable Sensor for Atomic Oxygen Detection J.J. Osborne, et al. 10. Large-Scale ECR-CVD Preparation of Integrated Thin-Film Structures for Space Applications R.V. Kruzelecky, et al. 11. Non-Silicone Inorganic Polymer-Based Coatings for Atomic Oxygen Protection in LEO - Part 2 E. Poire, et al. 12. Research Aspects of Scaling Up the Implantox Technology for Protection of Polymers in Space Z.A. Iskanderova, et al. Section C: ThermalControl in LEO. 13. A Comparison of Space and Ground-Based Facility Environmental Effects for FEP Teflon S.K. Rutledge, et al. 14. Evaluation of Low Earth Orbit Environmental Effects on International Space Station Thermal Control Materials J.A. Dever, et al. 15. Some Aspects of the Degradation of FEP Teflon Material Under the Action of VUV, the Sun and Ground Test VUV Facilities A. Milintchouk, M. Van Eesbeek. 16. Evaluation of COF MDPS Chromic Acid Anodization in LEO Environment C. Acket, et al. 17. A Database for the Selection of Surfaces and Materials for Space and Ground-based Applications S.H. McCall, et al. 18. Thermal Control Materials and Coatings Currently Being Developed in France for Use in Low Earth Orbit F. Guerard, J.C. Guillaumon. 19. Modification of Thermal Control Paints by Photosil (TM) Technology J.I. Kleiman, et al. Section D: Charged Particles/Soft X-Rays/Meteoroids/Thermal Cycling. 20. Simulated Solar Flare X-Ray and Thermal Cycling Durability Evaluation of HST Thermal Control Candidate Replacement Materials K.K. de Groh, et al. 21. Radiation-Induced Effects in SiO2 Protective Coatings on Polymeric Spacecraft Materials C. Coia, et al. 22. Influence of Electron and Proton Fluxes on Optical Properties of Protective Enamel S.N. Skovorod'ko, et al. 23. Meteoroid Hazard in the LEO Space Environment Y.S. Yatskiv, et al. 24. Characterizing the Annual Meteoroid Streams M. Beech. 25. Oxidation Kinetics of VB Group Metals by Atomic and Molecular Oxygen A.G. Gusakov, et al. 26.

Introduction. Section A: AO/UV and Radiation Effects on Materials and Structures in the LEO Space Environment. Low Flux Atomic Oxygen: Can it Be More Hazardous than High Flux? A Risk Assessment Study Y. Haruvy. Atomic Oxygen Durability Testing of an International Space Station Solar Array Validation Coupon M.J. Forkapa., et al. A Technique for Synergistic Atomic Oxygen and Vacuum Ultraviolet Radiation Durability S.K. Rutledge, B. Banks. Atomic Oxygen Durability of Second Surface Silver Microsheet Glass Concentrators K.K. de Groh, et al. A Study of Atomic Oxygen Material Degradation by Spaceflight Experiments and Ground-Based Simulation I.L. Harris, et al. Laboratory Simulation of Low Earth Orbit C.L. Bungay, et al. Section B: Interaction of Matter with LEO Environment. Prediction of In-Space Durability of Protected Polymers Based on Ground Laboratory Thermal Energy Atomic Oxygen Testing B. Banks, et al. Ground-Based Experimental Verification of the Predictive Model of Polymer-Based Materials Erosion by Atomic Oxygen in LEO G.R. Cool, et al. Anomalous Behaviour of the Linear Expansion Coefficient of Reinforced Plastics at Increased Temperatures R. Tourussov, et al. Predictive Models of Erosion Processes in LEO Space Environment: A Basis for Development of an Engineering Software J.I. Kleiman, et al. Section C: Large Scale Coating Process Developments for Protection in LEO. The Strategic Technologies for Automation And Robotics (Stear) Program: Protection of Materials in the Space Environment Sub-Program C. Brunet, et al. Plasma-Deposited Coatings for the Protection of Spacecraft Material Against Atomic Oxygen Erosion G. Czeremuszkin, et al. Large-Scale Electron Cyclotron Resonance Deposition of Protective Coatings for Space Applications R.V. Kruzeiecky, et al. Development of High Diffuse Reflectance Surfaces on Teflon J.I. Kleiman, et al. Materials Exposure in Low Earth Orbit 2 (MELEO2): An Update E. Poire, et al. Protection of the Radarsat Spacecraft from the Low Earth Orbit Environment D. Zimcik, S. Ahmed. Section D: Synthesis and Modification of Materials and Surfaces for Protection in LEO. About Some Aspects of Changing Optical Properties of Glass in Solar Arrays and Other Space Materials on Exposure to LEO Space Environment V.G. Tikhii. Photosil(t) -- A New Surface Modification Technique for Erosion Resistance Improvement of Polymer-Based Materials in LEO J.I. Kleiman, et al. Soft X-Ray Radiation as a Factor in the Degradation of Spacecraft Materials A. Milintchouk, et al. Surface Modification of Polymer-Based Materials by Ion Implantation: A New Approach for Protection in LEO Z.A. Iskanderova, et al. TOR and COR AO-VUV Resistant Polymers for Space A. Shepp, et al. Appendix A: Organizing Committee. Index.

A digital database with full user interaction is being developed to assist in the selection of black, white, reflective and transmissive spectrally selective materials. The database will include the optical, thermal, mechanical, physical, electrical and chemical properties of the surfaces and materials, as well as the space environment and contamination effects. The present paper presents an overview of the database project and describes in detail the atomic oxygen/vacuum ultraviolet sub-module of the space-environment module of the database. The purpose of the paper is to make the community aware of the project, to encourage participation, and to identify areas where community involvement is requested.