2022 IEEE Aerospace Conference (AERO)最新文献

{"title":"Lessons Learned from the Implementation of DOORS for the SUDA Instrument on Europa Clipper","authors":"W. Frank, S. Haselschwardt, S. Lev-Tov","doi":"10.1109/AERO53065.2022.9843236","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843236","url":null,"abstract":"Requirements management software can be useful, although the application of it on a project can be detrimental and time-consuming if not well implemented. The Dynamic Object-Oriented Requirements System (DOORS) software is one tool that is used for managing space-based systems requirements and their verifications. The SUrface Dust Analyzer (SUDA) team at the Laboratory for Atmospheric and Space Physics (LASP), part of the Europa Clipper mission being managed and built by the Jet Propulsion Laboratory (JPL), is using DOORS to manage this effort. This work details the SUDA Systems Engineering team's experience and lessons learned as they set up the requirements and verification database, managed the database contents, and worked around the limitations found with DOORS. In particular, decisions made early on can have significant unforeseen consequences that lead to large inefficiencies. Here we consider some of those decisions and their impacts as well as offer recommendations to inform future implementation of this software.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"146 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123256333","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Investigation of Mirror Satellite Concept to Provide Augmented Lighting for Dim Space-Based Objects","authors":"D. Dombrowski, Collin Gwaltney, Major Robert Bettinger","doi":"10.1109/AERO53065.2022.9843696","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843696","url":null,"abstract":"The imaging and inspection of Resident Space Objects (RSOs) is an increasingly important mission as space-faring nations and commercial enterprises alike seek to develop means to repair and refuel satellites, as well as de-orbit RSOs in order to reduce orbital debris. The lighting conditions for imaging and inspection are not always advantageous for a repair/refuel satellite, therefore, the use of mirror satellites to reflect solar energy is proposed to illuminate dimly lit RSOs. In terms of a general concept of mission operations, the primary solar reflector satellites would reside in sun-synchronous Earth orbits and be configurable to illuminate RSOs or secondary reflector satellites in a variety of different orbital regimes for imaging and/or inspection by repair and refueling satellites conducting proximity maneuvers near the RSO. In the 1980's and 1990's, many of the world's space-faring nations were conducting research into the use of mirror satellites for reflecting solar energy back onto Earth in order illuminate large urban areas, emergency operations, or farming to enhance photosynthesis. The Russian Znamya project began to test these ideas with two large satellites placed in orbit in the mid-1990's, though only one was successful. These mirror designs used extremely sparse apertures; however, they still are reported to have reached luminosities equivalent to several full moons and serve as an early proof of concepts for space-based mirrors. Research into the application of space-based solar reflectors has largely remained dormant for the past two decades. Recent advancements in membrane optics and large deployable structures have made solar reflector technology a feasible solution to enable modern inspection requirements. The proposed research seeks to further space-based mirror research through numerical simulation techniques to determine basic techniques and procedures for augmented lighting proximity operations. The effectiveness of mirror satellites in reflecting solar energy to target RSOs will be examined for a variety of orbital conditions for both the mirror satellites and RSOs. Factors that will be considered are the mirror satellite's effective range, magnitude and consistency of target illumination, and appropriate orbital geometries. The research will advance the ongoing development of satellite servicing and space domain awareness (SDA) missions within the near-Earth orbital domain. The analytical focus on using dedicated mirror satellites to provide sources of augmented illumination is novel and could enable unique lighting opportunities to improve the current characterization of both natural and man-made objects in the near-Earth space environment. The output of this research will be a quantification of the benefits of a space-based mirror satellite constellation for satellite servicing and SDA missions.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114960889","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Error Correction System Based on COTS Microcontrollers Working in Redundancy","authors":"R. M. França, Érico L. Marques, Tiago S. Da Silva, V. Parro","doi":"10.1109/AERO53065.2022.9843682","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843682","url":null,"abstract":"This paper presents the implementation, testing and analysis of an error detection and correction architecture for critical systems based on majority voting of several commercial off-the-shelf (COTS) microcontroller units (MCU). The architecture is based on at least three MCUs operating simultaneous and exchanging information by a controller area network (CAN) bus without the concept of master and slave. All MCUs must run the same software and maintain a Health Table with relevant information regarding each other. They can only differentiate themselves by a unique identifier set by hardware or by software at compile time. At any point during the code execution a vote involving all MCUs can be initiated to verify a result. The vote always uses only three of the system MCUs to try to reach a majority. This allows high flexibility regarding what units are used in the voting process. An error tracking system allows MCUs that are injecting too many errors to be isolated, so the system always uses only the most reliable units for the final vote. Once a majority is reached, all units can compare their own results to it and correct themselves if an error was detected. A real implementation of this architecture was created using four ARM-M4 MCUs for testing and use in an academic CubeSat. A flexible software implementation is presented and allows an error verification to be executed as many times as needed and in any number of variables. For different votes with different variables to be completely independent of each other, each votable variable needs to have its own Health Table. By creating a flexible Health Table structure in software, it's possible to add or remove votable variables easily, and to use the exact same voting function for any of them. The messages exchanged by CAN bus contains information regarding the sender, destination, message type and variable to vote, allowing the same message structure to be re-used. Combined with several internal security mechanisms, the system can detect faulty messages and keep operating even if the CAN bus itself corrupts the messages. To test the architecture and its implementation, an error generator was created using a pseudorandom number generator (PRNG). Each MCU can generate corrupted results for the vote process according to an individual user-defined probability. This allowed several test cases to be prepared, where the error rate was increased individually for each MCU in increments of 5%. Starting with only one MCU generating errors, and then adding the others one-by-one until all four were generating errors. The task chosen for the MCUs was to calculate the first one hundred prime numbers. Each test case was repeated a hundred times to reduce the PRNG influence over the test result. The different test cases and results are presented and analyzed. The architecture proposed proved itself fully functional, allowing the system to detect and correct most of the errors injected by the MCUs.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115039583","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Lunar Rover Localization Using Craters as Landmarks","authors":"L. Matthies, S. Daftry, S. Tepsuporn, Yang Cheng, Deegan Atha, R. M. Swan, Sanjna Ravichandar, M. Ono","doi":"10.48550/arXiv.2203.10073","DOIUrl":"https://doi.org/10.48550/arXiv.2203.10073","url":null,"abstract":"Onboard localization capabilities for planetary rovers to date have used relative navigation, by integrating combinations of wheel odometry, visual odometry, and inertial measurements during each drive to track position relative to the start of each drive. At the end of each drive, a “ground-in-the-loop” (GITL) interaction is used to get a position update from human operators in a more global reference frame, by matching images or local maps from onboard the rover to orbital reconnaissance images or maps of a large region around the rover's current position. Autonomous rover drives are limited in distance so that accumulated relative navigation error does not risk the possibility of the rover driving into hazards known from orbital images. In practice, this limits drives to a few hundred meters between GITL cycles. Several rover mission concepts have recently been studied that require much longer drives between GITL cycles, particularly for the Moon. This includes lunar rover mission concepts that involve (1) driving mostly in sunlight at low latitudes, (2) driving in permanently shadowed regions near the south pole, and (3) a mixture of day and night driving in mid-latitudes. These concepts include total traverse distance requirements of up to 1,800 km in 4 Earth years, with individual drives of several kilometers between stops for downlink. These concepts require greater autonomy to minimize GITL cycles to enable such large range; onboard global localization is a key element of such autonomy. Multiple techniques have been studied in the past for onboard rover global localization, but a satisfactory solution has not yet emerged. For the Moon, the ubiquitous craters offer a new possibility, which involves mapping craters from orbit, then recognizing crater landmarks with cameras and/or a lidar onboard the rover. This approach is applicable everywhere on the Moon, does not require high resolution stereo imaging from orbit as some other approaches do, and has potential to enable position knowledge with order of 5 to 10 m accuracy at all times. This paper describes our technical approach to crater-based lunar rover localization and presents initial results on crater detection using 3-D point cloud data from onboard lidar or stereo cameras, as well as using shading cues in monocular onboard imagery.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122322709","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Survey, Evaluation, and Advancement of Sample Sensing Techniques for Future Missions","authors":"J. T. Costa, L. Sanasarian, V. Sanigepalli, Sherman Lam, L. Stolov, J. Palmowski, R. Kancans, L. P. Tosi, Eric Roberts, K. Kriechbaum","doi":"10.1109/AERO53065.2022.9843741","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843741","url":null,"abstract":"Honeybee Robotics (HBR) and NASA's Jet Propulsion Laboratory (JPL) have performed an extensive trade study of thirty-four approaches to sample detection, mass, and volume measurement to inform sampling system architectures for future missions. Seven concepts were prototyped and tested; two were selected for further development. This paper details the methods and findings of the study, the new sample sensing technology developed, and its application to future missions.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122466248","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"HERMES Radio: Energy and Spectral Efficient Transmitter architectures for small satellites","authors":"Visweswaran Karunanithi, C. Verhoeven, C. Vaucher","doi":"10.1109/AERO53065.2022.9843200","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843200","url":null,"abstract":"As the complexity of nanosatellite missions have increased over time, the data generated on-board nanosatellites have increased multiple folds. As a result, there is a need to downlink large amounts of data. Multiple nanosatellite missions have started using spectral efficient modulation schemes recommended in DVB.S2 and DVB.S2X to make the best use of the available spectrum. One of the main challenges in adopting higher order modulation schemes is to power-efficiently upconvert and amplify the baseband signals. All the lost efficiency in converting the DC power to the RF output is dissipated as heat and the relatively small thermal mass of nanosatellites poses thermal management challenges. As a first step to addressing the challenge of improving the power efficiency of the communication module, optimization techniques to improve the Peak to Average Power Ratio (PAPR) of the modulation schemes (16/32-APSK) are discussed in this paper. The PAPR of 16-APSK reduces by ~2 dB by incorporating filtering techniques discussed in this paper. Further, a well-known efficiency and linearity enhancement technique; Out-phasing/LINC (Linear Amplification using Non-linear Components) is discussed. As a variant of the out-phasing architecture, a novel approach is proposed using two circularly polarized antenna to transmit the constant envelope signals in opposite polarizations and signal combining is performed at the receiver. Simulations results are used to demonstrate how higher efficiencies can be achieved using the proposed architecture.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"252 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122494870","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Mapping Earth's Dust-EMITting Regions from the ISS with the EMIT Imaging Spectrometer","authors":"B. Oaida, Amruta Yelamanchili, Christopher Wells, D. Thompson, R. Green, M. Bennett, D. Keymeulen, Thang Pham, Daniel P. Poe, Lena Siskind, Charlene Ung","doi":"10.1109/AERO53065.2022.9843581","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843581","url":null,"abstract":"The Earth Surface Mineral Dust Source Investigation (EMIT) is a Dyson-type imaging spectrometer which will operate from the EXPRESS Logistics Carrier (ELC) 1 platform of the International Space Station (ISS) starting in 2022 with the objective of mapping Earth's dust-EMITting land regions for the purpose of determining the composition of key constituent minerals and their impact on radiative forcing. Designed to operate for a minimum of one year, the EMIT instrument will collect over 50 Terabits of data representing billions of individual spectra for processing on the ground, significantly improving the state of knowledge about the composition and regional and global distribution of these key minerals. Acquiring, storing, processing and downlinking such large amounts of data requires a well-orchestrated planning effort in concert with an on-board high-performance computing embedded system. Adding to the challenge, and because the science requires a cloud-free measurement, significant effort has been expended in both attempting to predict the impact of clouds on the coverage as well as removing cloudy acquisitions on-board to reduce the pressure on the shared ISS downlink pipeline. In this paper we will explore the ways in which the EMIT mission design has been shaped by the performance requirements imposed by the science on data sufficiency and quality along with the constraints imposed by ISS operations and hardware limitations. Various sensitivity analyses are presented investigating the impact of ISS orbit altitude and seasonality on the coverage of the science target mask, along with data compression and throughput, cloudiness assumptions, and downlink data rate effects on on-board storage sizing and margins.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121910606","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Polarimeter to UNify the Corona and Heliosphere (PUNCH): Science, Status, and Path to Flight","authors":"C. Deforest, R. Killough, Sarah Gibson, Alan Henry, Traci Case, M. Beasley, G. Laurent, R. Colaninno, N. Waltham","doi":"10.1109/AERO53065.2022.9843340","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843340","url":null,"abstract":"PUNCH is a Small Explorer constellation mission in development for NASA's Heliophysics Division. PUNCH will image the transition zone between the outer reaches of the solar corona and the solar wind in the inner heliosphere, helping to unify the fields of solar physics and solar wind (space) physics. A constellation of four microsatellites (microsats) in Sun-synchronous LEO will produce deep field, continuous, 3D visible-light images of the corona and young solar wind from 6Rs to 180Rs in polarized visible light. A single Narrow Field Imager (NFI) on one microsat captures the outer corona from 6 Rs to 32 Rs, and three Wide Field Imagers (WFIs) on the remaining microsats capture from 20Rs to 180Rs. The instruments are matched and synchronized to operate as a single “virtual observatory”, with a 90-degree field of view centered on the Sun. The instruments use conventional lens optics and deep baffles to image the faint traces of visible sunlight that are Thomson-scattered by free electrons in the tenuous plasma of the outer corona and young solar wind. PUNCH includes polarized optics to produce 3D images using the polarization physics of the scattering. By bringing imaging science outward from the Sun and into the heliosphere, PUNCH fulfills its science objectives to (1) understand how coronal structures become the ambient solar wind, and (2) to understand the dynamic evolution of transient structures (such as CMEs) in the young solar wind. We briefly introduce the PUNCH science, describe fundamental trades that enabled the mission, and report current development status and the steps ahead toward on-orbit science operations.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122074406","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"3D Cloud-RAN Functional Split to Provide 6G Connectivity on Mars","authors":"Stefano Bonafini, C. Sacchi, F. Granelli, R. Bassoli, F. Fitzek, K. Kondepu","doi":"10.1109/AERO53065.2022.9843703","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843703","url":null,"abstract":"The Mars Helicopter Scout left a milestone in the history of the mankind by successfully completing the first flight on Mars. This achievement opens up to the possibility of having many unmanned aerial vehicles (UAVs) acquiring data from the Martian surface along with firmly anchored machines on ground, such as moving rovers or static landers. Moreover, it is no surprise that space agencies are also paving the way for the first human landing on the Red planet. In this context, it becomes needed to support future missions by providing connectivity to the whole Martian surface in order to allow in-situ wide band data exchange between nodes - user equipments (UEs) - composing the overall network. However, it seems tough to move common mobile terrestrial infrastructures on Mars and install them on-ground or implement them on limited-resource machines, as well as to guarantee everywhere and anytime on-demand connectivity. Thus, this paper will investigate the alternative solution of developing an autonomous Martian space ecosystem, through which globally inter-connect the UEs. UAVs and, eventually, high altitude pseudo satellites (HAPS), will act as radio unit (RU) and, partially, as distributed unit (DU) of a cloud radio access network (CRAN), while small satellites platforms, such as CubeSats (CS), placed in orbit will embark the majority of the computational load by performing the remaining DU and centralized unit (CU) functions. The proposed 3D network configuration, which looks towards a “Beyond 5G” infrastructure, or even 6G, will start by supposing very low Mars orbit (VLMO) in which CubeSats will be deployed. The design will then proceed through the installation process of CRAN on drones and CubeSats, while respecting strict latency and bandwidth requirements imposed by the Common Public Radio Interface standard (CPRI) at the fronthaul (FH) to allow low PHY-layer splitting options. A link-budget evaluation will then be proposed for the drone-to-Cubesat link. End-to-End (E2E) performance results will be shown in terms of coded BER between the UEs and the virtualized base station (BS), obtained by correlating the number of executable LDPC decoding iterations at CubeSat side and the signal-to-noise ratio (SNR) achievable over two specific areas of the Gale crater.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128783483","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Contamination Control Approach to Mitigating Radiation Induced Outgassing on Europa Clipper","authors":"Daniel Fugett, Carlos Soares, A. Wong, John Anderson, V. Ricchiuti, W. Hoey","doi":"10.1109/AERO53065.2022.9843223","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843223","url":null,"abstract":"NASA's Europa Clipper mission aims to conduct detailed reconnaissance of Jupiter's icy moon Europa and to investigate whether the moon could harbor conditions suitable for life. To perform these tasks Clipper will carry a suite of state-of-the-art scientific instruments, many of which are susceptible to the effects of molecular contamination and to interactions with the natural Jovian radiation environment. Recent ground testing conducted by the JPL Contamination Control group in the JPL Dynamitron particle accelerator (high-energy radiation source) has demonstrated that many common spacecraft materials exhibit significantly increased rates of molecular outgassing under exposure to high-energy radiation characteristic of the Europan environment [1]. This includes materials to be used in Clipper's thermal blankets and solar arrays, and subsequent free-molecular transport analyses showed that the increases in expected outgassing attributable to radiation would lead to exceedances of molecular deposition requirements for several of Clipper's instruments during the planned mission. The JPL Contamination Control group and the Europa Clipper project investigated testing and analysis refines in parallel with project mitigations strategies to protect Clipper's instruments. Refinements included improving the outgassing testing configuration and performing higher fidelity free-molecular flow analyses of instrument interiors. The project mitigations investigated include developing and testing alternate thermal blanket materials with a lower outgassing response under radiation and developing contamination shields that block line-of-sight between outgassing source surfaces and sensitive instrument surfaces. These mitigations were considered and coordinated with the impacted instrument teams such that any updates to the instrument requirements, available operation mitigations, or science robustness could be considered holistically. A combination of these strategies applied uniquely to each instrument proved most effective at mitigating predicted increases in molecular deposition caused by radiation induced outgassing. This approach demonstrates a novel method of identifying, assessing, and mitigating radiation induced outgassing that will be relevant to future space exploration missions with exposure to high-radiation environments.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129278292","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}