KEYWORDS: Diffusion, Physics, Chemical species, Data modeling, Chemical analysis, Temperature metrology, Standards development, Mass spectrometry, Epoxies, Data processing
Progress was performed recently on the separation and characterization of the chemical species outgassed by space materials, relying on the assessment of thermogravimetric analysis (TGA) peaks by mass spectrometry (MS). A companion communication reports on this experimental technique and the first level processing of these MS data, which often allows determining which are the outgassed species, and their MS spectra. This communication focusses more on the second analysis step, i.e. the study of the MS data acquired during the initial outgassing phase. Ancient simpler outgassing analyses based on total mass measurements only, most of the time on quartz crystal microbalances (QCMs), cannot realistically determine the separate contribution of different species, even though some models consider the contribution of several species, which are indeed more “mathematical species” than physical ones. In contrast, this new approach, also taking into account the MS measurements during the outgassing, and known species spectra (from the TGA/MS analysis done previously), allows a more realistic determination of the contribution of each real chemical species to the total outgassing. Even though results are not yet final and perfect, measured outgassing fluxes from several species and materials are presented. Their physical analysis, through comparison and fit by diffusion or other possible outgassing laws are also presented. At this level, they clearly point to diffusion laws, rather than to any other outgassing law, although not necessarily always Fickian diffusion. This method was applied to typical US or European outgassing approaches, with either isothermal ASTM-1559 outgassing tests or multi-temperature VBQC-type tests.
Well-established procedures for the characterization of contamination during outgassing usually involve total mass measurements through quartz crystal microbalance (QCM). Recently, the addition of mass spectrometry (MS) measurements to these data has become more common. The combination of both high sensitivity QCM and MS data may lead to a better understanding of the physics taking place during outgassing contamination processes. The way to do so is to complement the basic measurements of total mass loss on QCMs by the identification of each species and the quantitative determination of each species contribution. In a first characterization step, the thermogravimetric analysis of contaminants deposited on QCMs allows a partial species separation that helps exploiting mass spectrometry data. In return, these data permit a finer species separation. The key to these measurements is to obtain sufficient signal to noise ratio in the mass spectrometer. Though outgassing of space materials is not done the same way in Europe (multi-temperature steps, ECSS-Q-TM-70-52A) and in the US (isothermal, ASTM E-1559-09), both tests could be used to perform a first species separation, as reported here. Most species outgassed by a few common materials were identified (and quantified) through TGA and MS coupling. As reported in a companion paper, the knowledge of these species’ spectra then allows the analysis of the MS data during the initial outgassing phase, determining the quantitative outgassing of each species and leading to the improved comprehension of the physical laws ruling outgassing.
Psyche is a NASA Discovery-class mission that is designed to visit the metallic asteroid (16) Psyche to determine its origin and conditions of formation and to understand whether parallels between the asteroid and the cores of terrestrial planets can be drawn. [1] The Psyche instrument suite consists of a magnetometer, a gamma ray and neutron spectrometer (GRNS), the Psyche Multispectral Imagers (PMI) and the Deep Space Optical Communications (DSOC) technology demonstration payload. PMI and DSOC drive the overall contamination sensitivity of the Psyche mission. Unique contamination analysis challenges for the Psyche mission included: developing a novel molecular contamination transport model for parametric assessments of outgassing risk [2]; implementing a contamination-induced optical throughput degradation model; justifying the need for a T-0 purge and deployable aperture cover for DSOC; and modelling the sputtering and transport of contaminants due to electric propulsion system plume impingement. Contamination control implementation challenges on Psyche included: using a commercial telecommunications satellite bus to host scientific instruments; interfacing with a new spacecraft contractor; and creating a “chamber inside a chamber” for spacecraft TVAC to protect JPL’s 25ft Space Simulator. [3] This work describes JPL’s Contamination Control program for the Psyche mission, including the planning and execution of strategies to resolve those mission-unique challenges in preparation for launch.
NASA’s Europa Clipper mission will conduct a detailed reconnaissance of Jupiter’s moon Europa and investigate whether the icy moon could host conditions suitable for life. To perform these tasks, the spacecraft will carry several scientific instruments, including cameras, mass spectrometers, radars, magnetometers, plasma sensors and dust analyzer. These state-of-the-art instruments are very sensitive to molecular contamination; hence it is important to properly design preferential venting paths that minimize the transport of contaminants to the instruments sensitive surfaces. The JPL Contamination Control Group developed a physics-based approach to quantify the amount of contaminants escaping from the thermal blankets vents. This approach includes a thorough design of the thermal blankets and vents in the Europa Clipper geometrical model and a detailed analysis of the transport of contaminants from outgassing components underneath the thermal blankets to the vents. The physics-based thermal blankets venting model enhances the ability to assess and control outgassing contamination on Europa Clipper, and subsequently to properly design venting locations that provide a preferential escape path for outgassed molecules. The model also provides more accurate results compared to the historic approach (area ratio) widely used in literature to estimate outgassing from thermal blankets vents.
The Spectro-Photometer for the History of the Universe, Epoch of Reionization and Ices Explorer (SPHEREx) is a Jet Propulsion Laboratory (JPL) and Caltech led mission which will perform the first near-infrared all-sky survey to address the goals of NASA’s astrophysics division. SPHEREx accomplishes these surveys of the entire celestial sphere with an infrared telescope cooled to cryogenic temperatures by a passive thermal system. Because the SPHEREx payload has both an optical telescope and a passive thermal system, it is highly sensitive to particulate contamination. In this work the JPL Contamination Control (CC) group develops a computational physics framework to model particulate transport contamination from the fairing environment during launch, which is the largest particulate contamination source for most missions. Even with strict contamination control during ground processing, the launch environment can induce enough particulate contamination to exceed the scientific requirements of sensitive missions. For SPHEREx, particulate contamination in the telescope has a direct impact on the quality of the scientific data gathered during the surveys. Additionally, particulate contamination of the thermal system has a detrimental effect on its ability to cool the instrument to its cryogenic operating temperatures and maintain temperature stability. Due to these sensitivities it is imperative for SPHEREx that the particulate contamination from launch be comprehensively understood and mitigated wherever possible. The computational physics framework developed in this work is used to obtain precise estimates of particulate contamination on the SPHEREx payload and provides mitigations to ensure the mission meets its scientific requirements.
KEYWORDS: Contamination, Analytical research, Monte Carlo methods, Chemical analysis, Computer simulations, Contamination control, Space operations, Atmospheric sciences, Particles, Aerospace engineering
The Jet Propulsion Laboratory (JPL) has pursued a multi-disciplinary effort to experimentally characterize and computationally simulate the effects of powered descent onto the Europan surface. As part of the proposed Europa Lander technology development and maturation activities, JPL Contamination Control and the German Aerospace Center (DLR) are conducting a test program to characterize monopropellant plume-induced contamination, the preliminary results of which are showcased in this presentation. These measurements have been used in the further development of JPL’s computational physics simulations of descent engine plumes interacting with the Europan surface with direct simulation Monte Carlo (DSMC) techniques, and in broader support of contamination control strategies for the proposed Europa Lander mission.
If all goes according to plan, in February 2021, NASA will land the Mars 2020 Rover on the surface of Mars. Mars 2020 is the latest in a series of unmanned Martian robotic rover missions that are part of NASA’s Mars Exploration Program, a long-term effort of robotic exploration of the planet. The mission seeks to address high-priority goals for Mars exploration, including answering questions about the potential for past life on Mars. Mars 2020 will look for evidence of habitable conditions on Mars in the ancient past, as well as look for signs of past microbial life itself. The mission also seeks to understanding the geological history and evolution of the planet, and to prepare for future robotic and human exploration. The Mars 2020 spacecraft and rover borrow heavily from the Mars Science Laboratory (MSL) mission and Curiosity rover which landed on Mars in 2012. This reliance on proven technology helps reduce mission risk and cost. Mars 2020 does contain new technology, including a drill for coring samples from Martian rock and soil and a Sample Caching System for gathering, storing and preserving samples for possible future return to Earth. In this paper, we will review the primary goals of the Mars 2020 Mission and look at the reasons for choosing Jezero Crater as the landing site. We will discuss the design and build of the Mars 2020 Spacecraft system and its similarities and differences with Mars Science Laboratory and the Curiosity Rover. We will also review the Mars 2020 Scientific Instrument Suite and their goals. Finally, we will review the Return Sample Contamination Control requirements and the design choices that were made to facilitate meeting these requirements.
The performance of contamination sensitive components—such as optical components—can be degraded by particulate matter depositing on the surfaces. Particles can accumulate during manufacturing, handling and operation. For a space-based system, particles can shed from the fairing and redistribute onto sensitive surfaces during launch. An engineering modeling approach has been developed for modeling particle migration during launch. The approach involves particle detachment from the fairing, particle transport through the venting atmosphere inside the fairing, and attachment to the receiving surface. Particle size and amounts on the fairing surface can be modeled using distributions from standards, such as IEST-STDCC1246E, as well as from empirical data obtained from tape lifts. Surface interactions are modeled using theoretical as well as empirical data. Commercial computational fluid dynamics codes are used to calculate the gas flow in the fairing during depressurization during launch. This approach not only provides insight into particle redistribution during launch but also can be used to establish fairing cleanliness requirements.
One of the Mars 2020 mission’s primary science objectives is to seek out traces of past life on Mars – the rover’s sample caching system (SCS) will collect and store rock cores and regolith samples for possible return to Earth for analysis by a future mission. These samples must be contaminated with fewer than 10 parts-per-billion (PPB) total organic carbon (TOC) of terrestrial origin to permit an unambiguous detection of Martian organic signatures; this 10 PPB threshold translates to less than a monolayer of adsorbed contaminant molecules on the inside surfaces of sample tubes. Achieving such a stringent requirement has necessitated some of the strictest contamination control protocols ever enacted in NASA’s history. Throughout all phases of the mission, sources of terrestrial organic carbon can contaminate samples and sample caching hardware through a variety of transport mechanisms in free-molecular and continuum flow regimes. Predicting and mitigating the contamination of future returned samples requires a comprehensive understanding and cataloging of contaminant sources, transport mechanisms, and adsorption characteristics. Therefore, JPL Contamination Control has developed a novel multispecies model based on experimental measurements of Mars 2020 flight hardware, which has been applied in characterizing organic carbon contaminant sources, species compositions, and outgassing rate dependences on temperature. These are the boundary conditions for an end-to-end modeling framework in which the transport and deposition of contaminant species are calculated for each mission phase, culminating in a prediction of the total quantity of terrestrial organic carbon within future returned samples.
The field of contamination control has evolved to deal with increasingly sophisticated instruments developed in response to increasingly complex missions. Although there have been failures and degraded instrument performance due to contamination, contamination control methods have been largely successful to date. However, due to improvements in technology and the desire for more sensitive science measurements, spacecraft are no longer clean enough to meet more stringent contamination requirements. New contamination control engineering methods will require institutional investments. As a first step toward identifying appropriate areas for these investments, a “brainstorming” exercise is performed addressing some of the more important areas where improvements are needed.
As a laboratory for scientific research, the International Space Station has been in Low Earth Orbit for over 17 years and is planned to be on-orbit for another 10 years. The ISS has been maintaining a relatively pristine contamination environment for science payloads. Materials outgassing induced contamination is currently the dominant source for sensitive surfaces on ISS and modelling the outgassing rate decay over a 20 to 30 year period is challenging. Using ASTM E 1559 rate data, materials outgassing is described herein as a diffusion-reaction process with the interface playing a key role. The observation of -1/2 (diffusion) or non-integers (reaction limited) as rate decay exponents for common ISS materials indicate classical reaction kinetics is unsatisfactory in modelling materials outgassing. Nonrandomness of reactant concentrations at the interface is the source of this deviation from classical reaction kinetics. A t-1/2 decay is adopted as the result of the correlation of the contaminant layer thicknesses and composition on returned ISS hardware, the existence of high outgassing silicone exhibiting near diffusion limited decay, the confirmation of nondepleted material after ten years in Low Earth Orbit, and a potential slowdown of long term materials outgassing kinetics due to silicone contaminants at the interface.
AZ93 with a fluoropolymer overcoat is an option to simplify ground handling of space hardware. The overcoat applied on some on-orbit International Space Station (ISS) hardware provides contamination protection for optically sensitive ceramic thermal control coatings. However, if the fluoropolymer is not eroded on-orbit by atomic oxygen (AO), then it will darken. This will increase the solar absorptance resulting in possible thermal performance degradation. If the fluoropolymer overcoat was not present, optical performance would be significantly improved. To characterize the optical performance of the AZ93 with the fluoropolymer overcoat for modeling the UV degradation, laboratory testing of the coating was performed at Marshall Space Flight Center (MSFC). Sample coupons prepared by AZ Technology were exposed under vacuum to ultraviolet radiation. At periodic intervals, the samples were removed from the testing chamber to acquire images and to measure the solar absorptance. The images showed visible differences between AZ93 with the overcoat and without the overcoat as vacuum ultraviolet (VUV) exposure increased. Darkening is more pronounced in the samples with the fluoropolymer overcoat. This was also evident in the solar absorptance measurements. Optical properties of AZ93 with the fluoropolymer overcoat significantly degraded in comparison to those without the overcoat. A short period of little change followed by an exponential rise in solar absorptance was observed. The optical degradation of the fluoropolymer overcoat is described in terms of surface reaction chemistry and kinetics and is found to follow a pseudo first order reaction rate.
The International Space Station (ISS) solar arrays provide power that is needed for on-orbit experiments and operations.
The ISS solar arrays are exposed to space environment effects that include contamination, atomic oxygen, ultraviolet
radiation and thermal cycling. The contamination effects include exposure to thruster plume contamination and erosion.
This study was performed to better understand potential solar cell optical performance degradation due to increased
scatter caused by plume particle pitting. A ground test was performed using a light gas gun to shoot glass beads at a solar
cell with a shotgun approach. The increase in scatter was then measured and correlated with the surface damage.
Carlos Soares, Ronald Mikatarian, Danny Schmidl, Miria Finckenor, Michael Neish, Kichiro Imagawa, Magdeleine Dinguirard, Marc van Eesbeek, S. F. Naumov, A. N. Krylov, L. V. Mishina, Y. I. Gerasimov, S. P. Sokolova, A. O. Kurilyonok, N. G. Alexandrov, T. N. Smirnova
This paper presents an overview of International Space Station (ISS) on-orbit environments exposure flight experiments. International teams are flying, or preparing to fly, externally mounted materials exposure trays and sensor packages. The samples in these trays are exposed to a combination of induced molecular contamination, ultraviolet radiation, atomic oxygen, ionizing radiation, micrometeoroids and orbital debris. Exposed materials samples are analyzed upon return. Typical analyses performed on these samples include optical property measurements, X-ray photo spectroscopy (XPS) depth profiles, scanning electron microscope (SEM) surface morphology and materials properties measurements. The objective of these studies is to characterize the long-term effects of the natural and induced environments on spacecraft materials. Ongoing flight experiments include the U.S. Materials International Space Station Experiment (MISSE) program, the Japanese Micro-Particles Capturer and Space Environment Exposure Device (SM/MPAC&SEED) experiment, the Russian SKK and Kromka experiments from RSC-Energia, and the Komplast flight experiment. Flight experiments being prepared for flight, or in development stage, include the Japanese Space Environment Data Acquisition Attached Payload (SEDA-AP), the Russian BKDO monitoring package from RSC-Energia, and the European Materials Exposure and Degradation Experiment (MEDET). Results from these ISS flight experiments will be crucial to extending the performance and life of long-duration space systems such as Space Station, Space Transportation System, and other missions for Moon and Mars exploration.
We present the results of a laboratory test to determine the effects of bulk-deposited DC-704 silicone-oil contaminant film on the transmittance properties of an anti-reflective (AR) coated fused-silica optical substrate. Testing and optical measurements were performed in vacuum in the Boeing Contamination Effects Test Facility (CETF). The test and measurement procedures are described herein. Measurement results are presented showing the change in transmittance characteristics as a function of contaminant deposit thickness and vacuum-ultraviolet (VUV) exposure levels. The results show an initial degradation in the transmittance of the contaminated sample. This is followed by a partial recovery in transmittance as the sample is exposed to additional VUV radiation. The results also show a loss of transmittance in the ultraviolet portion of the spectrum and an increase in transmittance in the infrared portion of the spectrum. Thin-film interference analysis indicates that some of the observed transmittance results can be successfully modeled, but only if the contaminant film is assumed to have the complex index of refraction of SiO2 rather than DC-704 silicone oil. Post-test Scanning Electron Microscope (SEM) scans of the test sample indicate the formation of contaminant islands and the presence of a thin uniform contaminant film on the sample.
This paper documents thruster plume induced contamination measurements from the PIC (Plume Impingement Contamination) and SPIFEX (Shuttle Plume Impingement Flight Experiment) flight experiments. The SPIFEX flight experiment was flown on Space Shuttle mission STS-64 in 1994. Contamination measurements of molecular deposition were made by XPS (X-ray Photo Spectroscopy). Droplet impact features were also recorded with SEM (Scanning Electron Microscope) scans on Kapton and aluminum foil substrates. The PIC flight experiment was conducted during STS-74 in 1996. Quartz Crystal Microbalances (QCMs) measured contaminant deposition from U.S. and Russian thruster firings. Droplet impact observations were made with SEM scans of the Shuttle RMS (Remote Manipulator System) camera lens. These flight experiments were successful in providing measurements of plume induced contamination as well as droplet impact damage. These measurements were the basis of the plume contamination models developed for the International Space Station (ISS).
This paper documents International Space Station (ISS) external contamination observations and surface assessments covering Flights 1A/R through 6A. These observations are based on imaging from ISS missions, as active external contamination monitoring is not present in the configuration at this time. Imaging from ISS missions is a critical resource as it records the condition of ISS surfaces and helps identify visible signs of surface degradation. The observations are divided into three main sections; the first section covers the Functional Cargo Block (FGB - Russian Segment), the second section covers the Service Module (SM - Russian Segment), and the third section covers the U.S. Segment (Node 1 and Primary Mating Adapters 1 and 2). This distinction is important as materials selection, design and contamination control procedures differ between the FGB and Service Module on the Russian Segment and the U.S. Segment. Numerous observations of FGB self-contamination have been made through ISS imaging obtained during Shuttle flights. These observations were not surprising as external contamination studies conducted during the Shuttle-Mir (Phase I) Program showed extensive contamination induced by the Russian hardware. The impact of FGB induced contamination on ISS sensitive surfaces was mitigated due to FGB on-orbit time vacuum baking the Russian hardware prior to the deployment of ISS contamination sensitive hardware. Service Module impacts on ISS hardware were mitigated with a combination of changes in materials selection and on-orbit vacuum baking as there would be less on-orbit time before deployment of sensitive surfaces. While changes were made to materials selection, self-contamination observations have also been made on the Service Module. At this point, the U.S. Segment appears to be largely free of self-induced contamination. This confirms predictions made during the design and integration phase. Observed darkening and degradation of surfaces on the U.S. Segment is limited to a few areas and due to interactions with the on-orbit environment.
KEYWORDS: Molecules, Scattering, Optical spheres, Contamination, Space operations, Data modeling, Resolution enhancement technologies, Error analysis, Thermal modeling, Monte Carlo methods
This paper documents the development and validation of a new return flux model for the International Space Station (ISS). This model has been developed to augment current ISS external contamination modeling tool capabilities. The model is capable of characterizing return flux from ISS molecular emission sources. These sources include materials outgassing, vacuum venting, propellant purging and thruster firings. The BGK method (named after its authors: Bhatnagar, Gross and Krook1) was selected for modeling ambient scatter. This method was used to reduce computational times, as the ISS geometric models used for external contamination modeling may contain up to 40,000 surface elements. The model has been validated by comparison with analytical results and with results from the ESA COMOVA software. Validation with on-orbit flight experiment data will be conducted when adequate experimental data is available. Previously flown experiments (i.e., REFLEX) have not produced data with high enough fidelity to validate this model. The model has been applied to the ISS to characterize return flux from the European Columbus module onto its own payload locations. Analysis results indicate the return flux contribution to ESA payload surfaces will be small, but not negligible.
A study was conducted by Boeing-Houston to determine how the morphology and surface porosity of various materials and coatings used for ISS applications will influence the way contaminant molecules condense and deposit on sensitive optical and thermal control surfaces. The coatings used for these studies included: (1) clad aluminum, which served as a baseline reference material; (2) Silver Teflon film, which is used as a reflective surface for the ISS passive radiators' (3) Chromic Acid Anodized Aluminum, which is used as a thermal control coating for the ISS debris shields; (4) Sulfuric Acid Anodized Aluminum, which is used as a thermal control coating for the ISS truss elements, and Z-93P potassium silicate paint, which is used as a white reflective coating for the ISS active thermal radiators. The results of this study have shown that surface morphology, surface porosity, and surface texture greatly influence the way in which liquid silicone contaminant films condense in a vacuum environment and deposit on ISS materials and surface coatings.
A series of external contamination measurement were made on the Russian Mir Space Station. The Mir external contamination observations summarized in this paper were essential in assessing the potential system level impact of Russian Segment induced external contamination onto the Internal Space Station (ISS). Mir contamination observations include results from a series of flight experiments: CNES (Centre National d'Etudes Spatiales) Comes-Aragatz, retrieved NASA camera bracket, EuroMir '95 ICA (Instrument Comrade Active), and the Russian Astra-II. Results from these experiments were studied in detail to characterize the Mir induced contamination. In conjunction with Mir contamination observations, Russian materials samples were delivered to the U.S. for condensable outgassing rate testing. These test results were essential in the identification and characterization of Mir contamination sources. Once Mir contamination sources were identified and characterized, activities to assess the implications to ISS were implemented. As a result of these efforts, and in conjunction and collaboration with scientists at RSC-Energia in Russia, modifications in Russian materials selection and usage were implemented to control induced external contamination and mitigate risk to ISS.
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