cometadata/datacite-titles-descriptions-related-identifiers huggingface dataset:
DOI: 10.48577/jpl.cef9hh
title: Highlights of the Psyche Environmental Assurance Program

description: Environmental requirements for the Psyche missionwere established early in the program, and a comprehensiveenvironmental test and analysis implementation program wasdeveloped as the spacecraft design matured. Several designscope changes happened during development (for example,changed magnetometer design and vendor to an internationalinstitution), and the test program adjusted accordingly. Theenvironmental test program included numerous assembly-levelmission-qualifying tests, which fed into the system-levelenvironmental test program with focus on spacecraft levelverification. This paper describes the highlights of selectedportions of the assembly and system-level test program
DOI: 10.48577/jpl.eggchc
title: EELS: Towards Autonomous Mobility in Extreme Terrain with a Versatile Snake Robot with Resilience to Exteroception Failures

description: The discovery of ocean worlds such as Enceladus,Titan, and Europa motivates the development of resilient andadaptive autonomous mobility systems to enable the next era ofspace exploration. To explore these environments, we proposeExobiology Extant Life Surveyor (EELS): the first large-scale(4 lm long with 400 Nm peak torque) snake robot. The largescaleachieved by using a screw-based active skin mechanism todecouple motion and shape control. Autonomous mobility forsuch a system remains an open problem due to its many Degreesof Freedom (DoFs), complex terrain interactions, and intermittentlocalization failures in GPS-denied perceptually degradedenvironments. We propose NEO, an autonomy architecture forversatile robot for mobility in unknown extreme environments.In particular, we discuss the resilience capabilities of NEOthat achieves closed-loop tracking performance by leveragingexteroception when available but can also operate with proprioceptiononly, leading to resiliency against localization failuresvia graceful degradation in performance rather than unsafebehaviors. Furthermore, we also implement classical shapebasedgaits, such as sidewinding. A quantitative hardwareevaluation of exteroceptive leader-follower gait is performedindoors on synthetic ice along with qualitative results of fielddeployment of the proprioceptive leader-follower in extremeenvironments of icy and sandy terrains with mobility-stressingelements such as trenches, undulations, and steep slopes. Wepresent a set of lessons learned from field deployments with asummary of challenges and open research problems.Video: www.rohanthakker.in/eels-neo-autonomy.html
DOI: 10.48577/jpl.ktthad
title: Thermal Technology Advancements for Extended-Duration Lunar Operation

description: This paper describes ten innovations to enable multi-day/night operability/survivability of lunar instruments/systems. Extended-duration lunar operation is highly challenging due to the 50-100 K temperatures during the (15 Earth day) lunar night and the 350-400 K temperatures (at low-to-mid latitudes) during the (15 Earth day) lunar day. The ten thermal innovations described herein include: (1) thermally-switched enclosures (TSE); (2) parabolic reflector radiators (PRR); (3) spacerless MLI (SMLI); (4) low conductance thermal isolators (LCTI); (5) reverse-operation DTE thermal switches (ROD-TSW); (6) extended duration ROD-TSW (ES-ROD-TSW); (7) miniaturized ROD-TSW (mini-ROD-TSW); (8) miniaturized loop heat pipes (mini-LHP); (9) Vectran tension cables (VTC); and (10) lunar magnetometer thermal enclosures (LMTE). These ten innovations were developed at JPL under the PALETTE, ARTEMIS, and ROD-TSW projects. PALETTE is funded by NASA GCD, while ARTEMIS/ROD-TSW were funded by JPL. Also described herein are several lunar mission infusion opportunities including two that are already manifested (FSS, LuSEE-night) and a few that could eventually be developed/flown (LCRT, LGN, LTV, et. al).
DOI: 10.48577/jpl.bl3ugp
title: Demonstration of Non-Regenerative Pseudo-Noise Ranging in Parker Solar Probe and DART Missions

description: Abstract—Delivery of radiometric data to Earth for tracking and navigation applications is an essential function of the telecommunications subsystem of a spacecraft. For deep space missions, both Doppler and ranging methods are used to determine the spacecraft distance from Earth and trajectory; together they provide a more accurate position estimate. While deep space missions usually use sequential tone ranging, an alternate type of ranging signal called pseudo-noise (PN) ranging can in theory offer increased performance over sequential tones in some conditions. In order to demonstrate in-flight feasibility of using PN ranging with the Frontier Radio deep space radio for the benefit of future missions, four independent tests of this function were conducted at both X-band and Ka-band frequencies for Parker Solar Probe (PSP) mission. Tests were also performed semicontinuously over a course of two weeks for the Double Asteroid Redirection Test (DART) mission using X-band only. Although Frontier Radio has been tested in flight for regenerative PN ranging capabilities, these are the first tests for non-regenerative PN ranging with a newer generation of Frontier Radio. Here described are the results of the demonstrations with respect to navigation data quality, radio frequency link analysis, and lessons learned in ground station operational logistics. Also described is a comparison of sequential tone ranging and PN ranging with consideration for how the theoretical performance compared to observed data; in particular, it was observed that the quality of the navigation data was comparable to that of sequential tone ranging in a low-statistics context. However, PN still has potential advantages in that it may under certain circumstances reduce the total required time to collect data. Future work is required to adequately characterize all the biases in the system, to determine optimal integration times and other configuration parameters, and to decide whether the performance of PN ranging meets the requirements of future missions.
DOI: 10.48577/jpl.fp9ub4
title: Contamination Control Modeling for Europa Clipper’s MASPEX Instrument Aperture Cover Deployment

description: Abstract— MASPEX (Mass Spectrometer for Planetary Exploration/Europa) is a mass spectrometer flying aboard the Europa Clipper mission to identify gases in the Europa exosphere. As a mass spectrometer looking for trace species, the instrument is highly sensitive to outgassing contamination. A single monolayer of a species of interest collected on MASPEX may impact the science measurement. MASPEX has a one-time deployable vacuum sealed door to protect it from outgassing contamination. The initial plan was to deploy the door after Jupiter Orbit Insertion (JOI), however it was proposed that the door open earlier in cruise to accommodate concerns about the door deployment mechanism operating at cold temperatures. As part of the assessment to determine if the aperture cover door could be opened early, the Contamination Control Engineering group at the NASA Jet Propulsion Laboratory was tasked with assessing the contamination levels expected to make it into the MASPEX inlet. The main contamination environments for MASPEX during cruise and JOI are outgassing and propellant droplets. Outgassing follows three transport mechanisms to deposit on sensitive surfaces; direct line of sight, reflected, and return flux. The JPL Contamination Control team evaluated the contamination environments and mechanisms and found that the primary vector for contamination to reach MASPEX on Europa Clipper is reflected flux. This presentation discusses the modeling approach used to predict outgassing deposition on MASPEX resulting from opening the aperture cover door earlier in cruise. The focus is on the impact of the thermal environment on spacecraft outgassing, the extended duration over which contamination accumulation can occur, and the orientation of the solar array inducing a reflective path for outgassing.
DOI: 10.48577/jpl.qeafom
title: Super-Resolution Based Topology Optimization for Rapid Generation of Low Mass Structural Designs

description: Mass is a primary design driver in NASA spacecraft applications, directly limiting the number of scientific instruments that can be flown within a mission architecture, especially in the case of interplanetary missions. Topology Optimization (TO) is an emerging physics-based computational design tool with the ability to address this need, generating designs often 15-20\% lighter than conventional design approaches. In general, the computational cost and run time of TO are directly correlated with the desired features resolution of the generated design.Unfortunately, the thin geometries required for many aerospace structures require high resolution finite element meshes to yield quality TO designs, resulting in high computational power needs coupled with long solution times. The ability to solve a "quick" coarse-scale TO problem and, using Machine Learning (ML), map the design to a corresponding fine-scale design could reduce a design cycle time from weeks to days.In this paper, we developed a novel approach of mapping a 2D coarse-scale TO design (which runs fast with minimal compute resources) to a 2D fine-scale design (which would normally require significantly more time and compute resources using TO). Conventional TO methodologies (in particular, the Solid Isotopic Material Penalization -- SIMP -- methodology) generate designs in a format similar to grayscale images, providing a direct link with computer vision-based ML.This methodology is therefore similar to an image sharpening task that can build upon classical approaches such as the Single Image Super Resolution (SISR) task. We explore and propose an attention-based SRResU-Net that leverages rapid coarse-scale TO designs to seed robust high resolution TO designs. To ensure feature retention during the coarse-scale design generation, the optimization algorithm is de-tuned to generate ``fuzzy" images.The results demonstrate that the proposed model enables 10x faster design generation than high resolution TO alone while maintaining comparable accuracy and performance.
DOI: 10.48577/jpl.idifr0
title: Enabling DTN in Spaceflight Systems: Integration of ION with the F Prime Flight Software Framework

description: In this paper we will present an integration of Delay Tolerant Networking (DTN) within the F Prime flight software framework.Delay/Disruption Tolerant Networking technology was designed and developed to address communication challenges in deep space environments characterized by long propagation delay and discontinuous connectivity where contemporaneous end-to- end data paths may not always be present. The Interplanetary Overlay Network (ION), an implementation of DTN, had its first in-flight demonstration on the EPOXI spacecraft in 2008. ION has been deployed and operating on the ISS, supporting science commanding and delivery between onboard instruments and ground investigators. ION has also been demonstrated on the Korea Pathfinder Lunar Orbiter (KPLO) mission with the Deep Space Network (DSN) and on the Morehead State University’s 21-meter antenna. As DTN technology continues to demonstrate its potential for mission-critical communications, focus on mission infusion is gaining substantial momentum both inside and outside of NASA.F Prime is an open-source flight software (FSW) framework that makes use of reusable software components to provide flight projects with an extensible and modular FSW architecture. F Prime has allowed for rapid development and deployment of FSW on instruments, CubeSats, and technology demonstrations such as ISS-RapidScat, ASTERIA, and Ingenuity Mars Helicopter. By implementing DTN uplink and downlink as discrete F Prime components, DTN can be enabled on existing F Prime projects with significantly reduced developmental effort.We will describe the architecture and technical approach of how we integrated ION with F Prime to enable future mis- sions to participate in space-based DTN networks and leverage automated capabilities for reliable store-and-forward, routing, transport of command, telemetry, event reporting, and file transfer between the flight deployment and ground. This integration will be the basis for future upgrades that will introduce advanced networking capabilities for end-to-end security and data streaming such as video and audio playback in near real- time.
DOI: 10.48577/jpl.rxrnuz
title: Math is Instrumental: An Analysis of Multi-Decade Space Flight Science Instrument Cost Performance

description: Abstract—The development and operation of scientific instruments is of critical importance to advancing our understanding of the universe and our own planet. Many Earth orbiting satellites carry advanced instruments which collect data on our atmosphere, oceans, and land. Other Earth orbiting satellites carry instruments to look out into our solar system to study the sun, moon, other planets and moons, asteroids, comets, or even other distant galaxies. Instruments flying on these satellites are often so sensitive they can measure individual photons or x-rays emitted from light years away. Finally, there are spacecraft enduring long journeys in deep space to distant celestial bodies carrying instruments to observe, touch, or even land and explore these distant regions of the solar system. Together, all these instruments support a wide range of scientific research which are used to advance all the major scientific disciplines of astrophysics, planetary science, heliophysics, and Earth science. This paper presents an analysis of trends in instrument development cost growth for over 100 launched scientific instruments, and examines potential factors that influence instrument cost growth. Comparisons and statistical tests were performed and specific factors that contribute to cost growth were examined and categorized by frequency of occurrence. This analysis shows areas to focus on if space agencies wish to more effectively plan and implement their instrument development projects.
DOI: 10.48577/jpl.nztnvv
title: 2023 EELS Field Test at Athabasca Glacier as an Icy Moon Analog Environment

description: JPL is developing a versatile and highly intelligent robot called EELS (Exobiology Extant Life Surveyor) that would enable access to subsurface oceans and near-surface liquid reservoirs through existing conduits, such as the vents at the south pole of Enceladus or the putative geysers on Europa. In an ongoing project, we have prototyped two versions of the EELS robot and extensively tested them on various environments, such as snowy slopes, ice surfaces, and vertical ice walls in a walk-in freezer. In September 2023 we performed field tests on Athabasca Glacier, part of the Columbia Ice Field in Canada, as terrestrial analogs to the surfaces and subsurface of icy moons. This paper provides a fresh and comprehensive written record of the test campaign, which had four major goals: 1) vertical mobility, 2) surface mobility, 3) science instrument tests, and 4) terramechanics experiments. The robot successfully made a ~1.5 m descent in a vertical icy hold called moulins and demonstrated surface mobility on icy surface with undulations and slopes. The capillary electrophoresis (CE) instrument built to the form factor of an EELS module was tested in flowing water on the glacier and successfully demonstrated automated sampling and in-situ analysis. The terramechanics experiments were performed on horizontal and vertical surfaces, which would inform future development. 3D LiDAR scans of multiple supraglacial and englacial features were acquired. In this paper we report the outcomes of the four tests and discuss their implications for potential future icy missions. The field test also demonstrated EELS’s ability to support Earth science missions. Another potential near-term follow-on could be a technology demonstration on the Moon.
DOI: 10.48597/p7ne-rt97
title: Ammonia at Rörvik

description: Measurement of Ammonia at Rörvik
DOI: 10.48597/pn3g-x579
title: Aerosol_light_backscattering_coefficient at Puy de Dôme

description: Measurement of Aerosol_light_backscattering_coefficient at Puy de Dôme
DOI: 10.48597/pz4f-xj6g
title: Precipitation_amount at Preila

description: Measurement of Precipitation_amount at Preila
DOI: 10.48597/q2cv-wjvt
title: Nitrate at Aspvreten

description: Measurement of Nitrate at Aspvreten
DOI: 10.48577/jpl.wmyxya
title: A Novel Autonomous Lunar Self-Localization Technique Based on Local Surrounding Horizon Mask

description: Due to the absence of vegetation, season, weather, and artificial human-made structures, the surrounding horizon mask (SHM) at each location on the Moon remains unchanged. Because the lunar surface temperature is higher than the cold sky, the SHM signature can be extracted distinguishably using an onboard infrared sensor or camera. This process can be completed quickly and independently of lighting conditions, regions, and lunar phases. The fact that landscapes at the lunar South Pole are full of features and lack oceans and plateaus helps create the SHM at each location with a unique signature. Modeling and constructing SHMs for the Lunar South Pole using NASA’s LOLA Digital Elevation Map has started since 2019 to support several lunar architecture studies. A simple correlation or matching of the user’s SHM with the precomputed SHM of a known region can pinpoint the user’s location. This paper investigates the feasibility of using local SHM to identify the location and orientation of a surface user. Numerical simulations of local SHM, including random tilting biases and instrument errors, are implemented. Our preliminary results show that, with appropriate instrument calibration and performance, the average self-localization errors can be a few meters to tens of meters, and the average orientation errors are within half a degree.
DOI: 10.48577/jpl.vtauon
title: Star Formation at Low Metallicity: James Webb Space Telescope results from imaging and spectroscopy

description: No abstract available.
DOI: 10.48597/s3gf-rhb2
title: Nitric_acid at Vavihill

description: Measurement of Nitric_acid at Vavihill
DOI: 10.48597/sntr-5b2g
title: Particle_number_size_distribution at Aspvreten

description: Measurement of Particle_number_size_distribution at Aspvreten
DOI: 10.48597/sr6x-dmnf
title: Particle_number_concentration at Barrow

description: Measurement of Particle_number_concentration at Barrow
DOI: 10.48597/sv4s-65kj
title: Cloud_condensation_nuclei_number_concentration at Hyytiälä

description: Measurement of Cloud_condensation_nuclei_number_concentration at Hyytiälä
DOI: 10.48597/sv4s-kndb
title: Heavy metals at Irafoss

description: Measurement of Heavy metals at Irafoss
DOI: 10.48597/t7n3-ez9h
title: Nitrate at Rörvik

description: Measurement of Nitrate at Rörvik
DOI: 10.48597/tgsc-tqse
title: Sulphate_corrected at Sepstrup Sande

description: Measurement of Sulphate_corrected at Sepstrup Sande
DOI: 10.48597/tt2e-tgu8
title: Nitric_acid at Aspvreten

description: Measurement of Nitric_acid at Aspvreten
DOI: 10.48597/tzdx-rmx5
title: Particle_number_concentration at Barrow

description: Measurement of Particle_number_concentration at Barrow
DOI: 10.48597/ugv9-uyfr
title: Ammonia at Aspvreten

description: Measurement of Ammonia at Aspvreten
DOI: 10.48597/unwk-c2fx
title: Aerosol light scattering at Puy de Dôme

description: Measurement of Aerosol light scattering at Puy de Dôme
DOI: 10.48597/ur5h-8qzq
title: Aerosol_optical_depth at Ryori

description: Measurement of Aerosol_optical_depth at Ryori
DOI: 10.48597/v52y-qse9
title: Inorganics in precipitation at Sepstrup Sande

description: Measurement of Inorganics in precipitation at Sepstrup Sande
DOI: 10.48577/jpl.mexcq3
title: High-Efficieny All-Metal Metasurface Antenna Design for Space Applications

description: The demand for medium and high-gain antennas in space exploration is steadily increasing, but traditional designs, like parabolic reflector antennas, do not always align with the objectives of low-profile and cost-effective designs. Metasurface (MTS) antennas present an innovative alternative, leveraging cylindrical surface waves and modulated boundary conditions for improved performance. However, dielectric substrates in harsh space environments can be problematic. An all-metal design is less susceptible to thermal fluctuations and radiation induced changes in dielectric properties. Previous research has introduced non-optimized metallic designs. This paper outlines the impedance boundary conditions and design considerations for fully metallic MTS antennas with high efficiency, comparing isotropic and anisotropic designs. The design process includes creating an impedance database and optimizing modulation parameters for enhanced efficiency.
DOI: 10.48577/jpl.tgj1zh
title: Europa Clipper Solar Array Mass Simulator (SAMS) Development for Spacecraft Dynamics Testing

description: The Europa Clipper Spacecraft has two large solar arrays that will not be integrated with the Spacecraft until after all environmental testing is complete and the Spacecraft has shipped to the launch site. This deviation in flight test configuration was driven by the development timeframe of the solar arrays as well as the Europa Clipper ATLO schedule, but posed many challenges to the mechanical team responsible for the modal, vibration, acoustics, and separation system testing of the Spacecraft. To accommodate the late delivery of the flight solar arrays, Solar Array Mass Simulators (SAMS) were developed to be used during the Spacecraft dynamic test campaigns. The SAMS are single panel aluminum honeycomb structures with aluminum face sheets that are mounted to the flight solar array struts. The SAMS were designed to have a first bending mode that matches the flight solar arrays and have an equivalent mass. The SAMS were a necessary component for the system modal and dynamics tests as the solar arrays represent significant mass and stiffness of the Spacecraft and are major contributors to primary modes of the system. The SAMS underwent their own dynamics qualification tests in which a major failure occurred during a sine test, resulting in a rework of both panels. Testing was successful following the rework of the panel and the SAMS were delivered to JPL for Spacecraft testing. The inclusion of SAMS instead of the flight solar arrays posed several challenges to the Spacecraft test as SAMS has significantly different modal content besides the first bending mode, and much less damping than the flight solar arrays. These differences required JPL to implement analysis and test strategies to ensure Spacecraft dynamics test objectives were met while considering the safety of hardware and personnel. The overall approach have been documented and accounted for in the test plans and limiting strategies for the system test, performed in November 2023.
DOI: 10.48597/xdw8-4cn4
title: Sulphate_corrected at Esrange

description: Measurement of Sulphate_corrected at Esrange
DOI: 10.48597/y49a-y6p5
title: Precipitation_amount at Irafoss

description: Measurement of Precipitation_amount at Irafoss
DOI: 10.48597/ycxg-3qv4
title: Ammonium at Rörvik

description: Measurement of Ammonium at Rörvik
DOI: 10.48597/yj6z-3sd6
title: Aerosol_absorption_coefficient at Barrow

description: Measurement of Aerosol_absorption_coefficient at Barrow
DOI: 10.48597/ykh3-pqd8
title: Vanadium at Irafoss

description: Measurement of Vanadium at Irafoss
DOI: 10.48597/ynj2-stes
title: Particle_number_concentration at Barrow

description: Measurement of Particle_number_concentration at Barrow
DOI: 10.48597/yx4m-8ekd
title: Precipitation_amount at Irafoss

description: Measurement of Precipitation_amount at Irafoss