cometadata/datacite-titles-descriptions-related-identifiers huggingface dataset:
DOI: 10.48420/26935324
title: Processed single cell RNA-seq data for manuscript "HAND1 level controls the specification of multipotent cardiac and extraembryonic progenitors from human pluripotent stem cells"

description: Processed single cell RNA-seq (scRNA-seq) data (10xGenomics Flex) and metadata from Lynch et al. The EMBO Journal 2025, https://doi.org/10.1038/s44318-025-00409-0, stored in Loom format. The loom file includes wild-type (WT) and HAND1-null (KO) cells ("colAttrs/condition"). Metadata also includes the day/timepoint of differentiation ("colAttrs/day"), the assigned cell type ("colAttrs/cellType") and the SCENIC regulon AUC scores for each cell ("colAttrs/regulonAUC").
DOI: 10.21985/n2-cb08-qp88
title: Data for "Large Language Models for Machine-Readable Citation Data"
DOI: 10.48577/jpl.zcpjgy
title: Preliminary Design of the Robotic Pickup, Install, and Encapsulation Subsystem for CCRS

description: No abstract available.
DOI: 10.48577/jpl.ydhcxt
title: From One Unit Tech Demo to Three Unit Class D Constellation: Operations Lessons from RainCube to INCUS DAR

description: INvestigation of Convective UpdraftS (INCUS) is a NASA Earth Venture Mission (EV-M) managed by JPL for the Colorado State University (CSU) PI. The INCUS mission will be comprised of a constellation of three observatories, each consisting of the spacecraft bus, and the Dynamic Atmospheric Radar (DAR). One observatory will also host the Dynamic Microwave Radiometer (DMR), based on the TEMPEST-D technology demonstrator. DAR is an evolution of RainCube (Radar In a Cubesat), with 7-beam cross-track scanning capability. The three observatories will fly in low-Earth-orbit (LEO) in a train formation to make measurements of tropical convective storms at three different times (0, 30 and 120 seconds). The temporal sampling of the DAR reflectivity profiles is used to measure reflectivity changes with time, allowing the detection of convective updrafts and the estimation of their transport of air and water between the surface and upper troposphere, known as Convective Mass Flux (CMF), and elucidates how this transport varies with storm type and throughout the storms’ lifecycles. The INCUS measurements will increase our understanding of how, when, where, and why storms form, and will allow us to better model and predict the role of convective storms in current and future climates.
DOI: 10.48577/jpl.uda86z
title: Radio Transmitter Development to Support multi-Gbps Satellite Downlinks in Ka-band

description: Advancements in spaceborne remote sensing technology have significantly increased the amount of data generated onboard spacecraft, necessitating a robust downlink system capable of much higher rates than previously required. For the NASA/ISRO Synthetic Aperture Radar (NISAR) mission the Jet Propulsion Laboratory (JPL) has developed a Ka-band Modulator (KaM) variant of the Universal Space Transponder (UST) product line to support 2000 Msps downlink from a single radio using Offset QPSK (OQPSK) modulation in the Earth Exploration Satellite Service (EESS) band from 25.5 to 27.0 GHz. The KaM has successfully completed its protoflight development campaign and flight models have been integrated onto the NISAR spacecraft, awaiting its launch. The KaM is a Software-Defined Radio (SDR) that offers the flexibility to change all aspects of the RF modulation to channel coding without altering the underlying hardware. This paper describes aspects of the design/implementation trade space to achieve higher data rates on the KaM while meeting transmission band spectral limitations. We explore the use of higher-order modulation schemes such as 8PSK and 16APSK, which can substantially increase data throughput within the available 1500 MHz bandwidth of the EESS band. Performance simulations and prototype radio-based characterization tests demonstrate that with firmware updates, the KaM can be upgraded to support data rates up to 3000 Msps using 8PSK modulation and 4000 Msps using 16APSK modulation. By employing a dual polarization downlink scheme using 16APSK, the updated radio could enable downlink rates of up to 8000 Msps for future missions with much greater downlink volume requirements. Link analyses are presented for Low Earth Orbit science satellites comparing the data rates against station coverage time to NASA’s Near Space Network (NSN) and possible daily downlink volumes. A feasibility study is presented that evaluates high-rate lunar downlinks, pairing KaM technology with proposed Lunar Exploration Ground Sites (LEGS) considering current high-power amplifiers and antenna technology. Additionally, future Mars surface terminal links are analyzed to explore the viability of high-rate relay communications from the Martian surface to future Mars relay orbiters.
DOI: 10.48577/jpl.3lca7m
title: Structural Equation Modeling for Efficient Mission Formulation

description: The purpose of the NASA Pre-Phase A project life cycle phase is, “To produce a broad spectrum of ideas and alternatives for missions from which new programs/projects can be selected, and to determine the feasibility of [the] desired system, develop mission concepts, draft system-level requirements, assess performance, cost, and schedule feasibility; identify potential technology needs, and scope.”[1].In this early stage of planning NASA's science missions, a key goal is to maximize "science per dollar" efficiency. This means making the most out of limited financial resources. To achieve this, it's crucial to define the minimum science requirements necessary for the mission. If these requirements are too ambitious, the mission's "science per dollar" efficiency drops, and valuable scientific opportunities might be missed. Overly ambitious science requirements can also lead to unnecessary cost risks, jeopardizing the mission proposal's success and reducing the overall scientific return. Therefore, it's essential to strike a balance in setting these requirements. Another crucial part of early mission planning is efficiently identifying the essential science requirements to ensure maximum efficiency of the formulation effort itself.This paper presents a versatile framework for efficiently identifying minimum science requirements using Structural Equation Modeling (SEM). This approach is applicable across all five divisions of NASA’s Science Mission Directorate: Astrophysics, Biological and Applied Sciences, Earth Science, Heliophysics, and Planetary Science. Additionally, we share initial results from implementing this method in early mission concept formulation at the Jet Propulsion Laboratory.
DOI: 10.48577/jpl.qb8duj
title: Enabling Novel Mission Operations and Interactions with ROSA: The Robot Operating System Agent

description: The advancement of robotic systems has revolutionized numerous industries, yet their operation often demands specialized technical knowledge, limiting accessibility for non-expert users. This paper introduces ROSA (Robot Operating System Agent), an AI-powered agent that bridges the gap between the Robot Operating System (ROS) and natural language interfaces. By leveraging state-of-the-art language models and integrating open-source frameworks, ROSA enables operators to interact with robots using natural language, translating commands into actions and interfacing with ROS through well-defined tools. ROSA's design is modular and extensible, offering seamless integration with both ROS1 and ROS2, along with safety mechanisms like parameter validation and constraint enforcement to ensure secure, reliable operations. While ROSA is originally designed for ROS, it can be extended to work with other robotics middle-wares to maximize compatibility across missions. ROSA enhances human-robot interaction by democratizing access to complex robotic systems, empowering users of all expertise levels with multi-modal capabilities such as speech integration and visual perception. Ethical considerations are thoroughly addressed, guided by foundational principles like Asimov's Three Laws of Robotics, ensuring that AI integration promotes safety, transparency, privacy, and accountability. By making robotic technology more user-friendly and accessible, ROSA not only improves operational efficiency but also sets a new standard for responsible AI use in robotics and potentially future mission operations. This paper introduces ROSA’s architecture and demonstrates first mockup operations in a Martian analog terrain. For the benefit of the community, the ROSA framework has been made publicly available.
DOI: 10.48577/jpl.vdppts
title: The Ganymede Laser Altimeter (GALA) on the Jupiter Icy Moons Explorer (JUICE) Mission

description: The Ganymede Laser Altimeter (GALA) on the Jupiter Icy Moons Explorer (JUICE) mission, is in charge of a comprehensive geodetic mapping of Europa, Ganymede, and Callisto on the basis of Laser range measurements. While multiple topographic profiles will be obtained for Europa and Callisto during flybys, GALA will provide a high-resolution global shape model of Ganymede while in orbit around this moon based on at least 600 million range measurements from 2 an altitude of 500 km above the surface. By measuring the diurnal tidal deformation of Ganymede, which crucially depends on the decoupling of the outer ice shell from the deeper interior by a liquid water ocean, GALA will obtain evidence for (or against) a subsurface ocean on Ganymede and will provide constraints on the ice shell thickness above the ocean. In combination with other instruments, it will characterize the morphology of surface units on Ganymede, Europa, and Callisto providing not only topography but also measurements of surface roughness on the scale of the laser footprint, i.e. at a scale of about 50 m from 500 km altitude, and albedo values at the laser wavelength of 1064 nm. GALA is a single-beam laser altimeter, operating at a nominal frequency of 30 Hz, with a capability of reaching up to 48 Hz. It uses a Nd:YAG laser to generate pulses with pulse lengths of 5.5±2.5 ns. The return pulse is detected by an Avalanche Photo Diode (APD) with 100 MHz bandwidth and the signal is digitized at a sampling rate of 200 MHz providing range measurements with a sub-sample resolution of 0.1 m. The instrument was developed in collaboration of institutes and industry from Germany, Japan, Switzerland, and Spain. JUICE, conducted under responsibility of the European Space Agency (ESA), was successfully launched in April 2023 and is scheduled for arrival at the Jupiter system in July 2031. The nominal science mission including multiple close flybys at Europa, Ganymede, and Callisto, as well as the final Ganymede orbit phase will last from 2031 to 2035. In May 2023 GALA has completed its Near-Earth Commissioning, showing full functionality of all units. Here we summarize the scientific objectives, instrument design and implementation, performance, and operational aspects of GALA.
DOI: 10.48577/jpl.tsaah6
title: Enhancements of FLEX Hyperspectral Data Compression using High-Performance Embedded Space Computing

description: This paper describes the enhancement of a data compression computing system that operates on imaging spectrometer data. The implementation is part of the focal plane interface electronics-digital (FPIE-D) and includes AMD System-on-Chip (SoC) Zynq-based and KU060-based versions. JPL imaging spectrometers can acquire data with 640, 1280, or 3000 cross-track positions with 328 or 480 bands at up to 216 images per second. Uses for imaging spectrometer data include studying the mineral dust cycle, methane detection, analysis of biodiversity, and fire detection.
DOI: 10.48577/jpl.aufxrw
title: ANALYSIS OF ELECTRIC PROPULSION PROPELLANT TYPE FOR CREWED MARS MISSIONS

description: An analysis of alternative Hall thruster propellants to xenon for a crewed Mars mission using nuclear electric/chemical propulsion is performed. Xenon, the preferred propellant when considering storage density and Hall thruster performance, is not readily available in the quantities needed for this mission, creating significant mission planning challenges. Therefore, this analysis considers the use of more available propellants and multiple storage strategies. This includes gaseous and cryogenic storage of krypton and argon and solid storage of zinc. The 1.8 MW Compass vehicle design and mission planning for a 2039 opposition class mission to Mars is utilized as a reference. A framework is developed to re-design the reference vehicle and recalculate the mission for each propellant type. The results indicate that cryogenic krypton or argon, and zinc may be feasible replacements to xenon for this mission. This result is largely driven by the comparable storage density/tank weight of these propellants to standard xenon. The low storage density of gaseous krypton and argon, coupled with launch vehicle mass/volume requirements, leads to the inability to meet mission requirements. The key limitations of this analysis and outstanding development challenges are discussed in the context of the EP system and each alternative propellant. The framework developed in this work is extendable to analyze any Hall thruster propellant for crewed Mars missions.
DOI: 10.48577/jpl.tcdsxo
title: First Year of Psyche Electric Propulsion Cruise Operations

description: This paper presents a review of operations and performance for the electric propulsion (EP) system on the Psyche spacecraft during the first year of the mission. After a successful initial checkout phase, the EP system has been in near continuous operation since late March, 2024, the beginning of a roughly six year long Cruise phase. Usage statistics to date on all four thrusters and both power processing units (PPUs) are presented. Notable trends in electrical and thermal performance of the thrusters, feed system, and PPUs are shared along with unexpected observations and risk mitigation activities. The propellant gauging method is reviewed and a to-date trending of xenon mass with uncertainty is presented. Improvements to the spacecraft momentum management strategy made since launch are detailed alongside measured total torque on the spacecraft during thrusting. The new thruster switching plan for the rest of the six year Cruise and an operations-centric propellant budgeting strategy are presented for the first time here.
DOI: 10.48577/jpl.y6sxxc
title: Dshell-DARTS: A reusability-focused multi-mission aerospace and robotics simulation toolkit

description: The Dshell-DARTS framework is a versatile simulationtoolkit designed for aerospace and robotics applications.Developed at NASA’s Jet Propulsion Laboratory (JPL), it supportshigh-fidelity simulations for a wide range of systems,including interplanetary, orbital, atmospheric, and surface vehicles,as well as robotic platforms. Dshell-DARTS integrateskey capabilities in support of these simulations, such as rigidand flexible multi-body dynamics, sensor simulation, collisionmodeling, terramechanics computations, and gravity and atmosphericmodeling. This paper outlines the challenges ofdeveloping a simulation framework capable of supporting suchdiverse domains and capabilities. Reusability is identified asa key feature in meeting these challenges, and some of thearchitectural choices adopted in Dshell-DARTS that enable andpromote reusable capability development are explored. Thisreusability-focused architecture reduces the need for bespokesimulation creation, which accelerates development and testing,and enhances robustness. The Dshell-DARTS framework hasbeen successfully used in numerous NASA missions, demonstratingits versatility in supporting complex and diverse missionrequirements.
DOI: 10.48577/jpl.kbzvms
title: MLGTT: An Open-Source Tool to Generate Camera-Relative Ground Truth for Monocular Localization (presentation)

description: No abstract available.
DOI: 10.34740/kaggle/dsv/10983183
title: gold_price_1990-2024
DOI: 10.48577/jpl.ro0pz8
title: SLIDES Dshell-DARTS: A reusability-focused multi-missionaerospace and robotics simulation toolkit

description: No abstract available.
DOI: 10.48577/jpl.rgiaa8
title: Acquiring Precision Doppler Measurements with Juno's Ka-band Translator for Increased Science

description: No abstract available.
DOI: 10.48577/jpl.6275hh
title: Mars Sample Recovery Helicopter Aerial Mode Commander Design Using Executable Models

description: No abstract available.
DOI: 10.48577/jpl.amacmi
title: Profiling Drizzle Drop Size Distributions and Air Motion with a G-Band Cloud Radar

description: No abstract available.
DOI: 10.48577/jpl.tbd1wv
title: eochemical Transformations of Gypsum under Multiple Environmental Settings and Implications for Ca-Sulfate Detection on Mars

description: Calcium sulfate minerals are found in multiple environments on Earth and Mars, with chloride (Cl) salts widely distributed on both planets. Low-temperature studies have explored geochemical processes including formation of transient liquid water and ion migration on Mars. Some Cl-salts (e.g., NaCl and CaCl2) can dissolve gypsum (CaSO4·2H2O) in certain environments, making gypsum-Cl salt interactions significant. Additionally, gypsum's geochemical transformation at high temperatures reveals dehydration pathways crucial for understanding Mars' aqueous history and potential for life. This study examines gypsum dehydration through (i) thermal analyses and (ii) interactions with Cl-salts over a temperature range of −90 to 400 °C. We applied three spectroscopic techniques (Raman, visible/near-infrared (VNIR), and mid-IR) plus X-Ray Diffraction (XRD) to analyze these samples under variable conditions. This study also provides a low-temperature spectral dataset for gypsum and gypsum-Cl salt mixtures, beneficial for orbital analyses. Our findings reveal that experimental (i) heating rates, (ii) temperature ranges, (iii) relative masses of gypsum and Cl-salts, and (iv) dehydration environments (e.g., in situ, in vacuum) influence Ca-sulfate phase formation. Although we find different results in some cases, this study demonstrates that changing experimental conditions affect the detectability and transformation of gypsum. Further, these results indicate that the geochemical environmental condition on Mars plays a role in gypsum's geochemical transformation to dehydrated components. This study also provides structural and chemical data for Ca sulfate assemblages from vibrational spectroscopy and XRD, which extends our knowledge of gypsum and related materials under variable conditions, thus aiding orbital and surface planetary analyses which may help to advance our understanding of planetary geochemistry on Mars.
DOI: 10.48577/jpl.fhsg4e
title: A Comparison of Navigation Methods Enabled by a Deep Space Relay Architecture

description: A deep space relay architecture for communicationand navigation was developed in two previous papers. Thebaseline architecture, consisting of a Mars leading and a Marstrailing relay, was designed to mitigate the Mars conjunctionproblem for optical communication while enabling deep spacetrilateration for inner solar system users. An expanded versionof the architecture added a Mars halo relay which improved thearchitecture’s data throughput and navigation potential.This paper further defines the navigation component of thearchitecture. Previous analysis assumed trilateration withidealized, instantaneous one- and two-way range measurements.Here, four realistic methods for deep space ranging are definedand compared: two-way ranging from a node, two-way rangingfrom a user, one-way broadcast ranging, and one-way point-topoint ranging. Tradeoffs in accuracy, latency, and complexityare discussed. Pseudo-noise ranging approaches compatiblewith each measurement mode are identified and a link analysisis performed to assess measurement accuracy, determine userservice volumes, size relay hardware, and plan operationsstrategies. Idealized measurement assumptions are dispensedwith to develop the concept of a “deep space trilateration”algorithm, in which the measurement models incorporate signalpropagation time, the motion of nodes and users, and processingdelays, which are all non-negligible effects at deep spacedistances. A “deep space joint doppler and ranging” algorithmis also developed to assess the benefits of incorporating bothrange and doppler information into a navigation solution.The navigation merits of the deep space relay architecture werepreviously assessed with a dilution of precision (DOP) analysis.On its own, the DOP simulation captured the intrinsic geometricquality of the architecture for trilateration but did not fullycapture user-achievable positioning accuracy. This paperestimates user navigation performance with a more rigorousfilter-based simulation. The simulation implements the deepspace trilateration and joint doppler and ranging algorithms foreach measurement method and accounts for measurement,clock, and ephemeris errors. The accuracy and timeliness ofsimulated user position estimates are compared across eachnavigation method for a variety of inner solar system users.
DOI: 10.48577/jpl.9yzlev
title: KAZR-CloudSat analysis of snowing profiles at the North Slope of Alaska: implications of the satellite radar blind zone

description: Spaceborne radars provide near-global observations of clouds and precipitation, but ground 19 clutter can result in a satellite radar blind zone as high as 2 km above the surface. As 20 a result, satellite radars may underestimate snowfall from shallow clouds and incorrectly 21 flag snow virga as snowfall at the surface. Ground-based radar observations provide in22 valuable tools to assess satellite observations of clouds and precipitation. This study in23 vestigates snowfall regimes using observations from 2011-2021 at the Department of En24 ergy Atmospheric Radiation Measurement North Slope of Alaska atmospheric observa25 tory. Snowfall events identified in the Ka-band ARM Zenith Radar (KAZR) are sepa26 rated into regimes based on the cloud/precipitation layer characteristics: deep snowfall, 27 shallow snowfall, and snow virga. The shallow snowfall regime accounts for nearly half 28 of the regime occurrence (48%) followed by snow virga (28%) and deep snowfall (23%). 29 However, more than half (62%) of the shallow snowfall is likely under-estimated and/or 30 undetected within the satellite radar blind zone. Snow virga is incorrectly flagged as snow31 fall for 7% of the total annual occurrence, but increases to 12% in October. The KAZR 32 regimes and vertical structure are qualitatively compared to collocated CloudSat obser33 vations with snow certain/possible flags; the deep and shallow snowfall regime show sim34 ilarities between the ground-based and spaceborne radar observations . An assessment 35 of observable snowfall occurrence and accumulation at varying reflectivity thresholds in 36 KAZR and CloudSat provide a reference for detection characteristics for current and planned 37 spaceborne radars.
DOI: 10.48577/jpl.heb2dl
title: Dimming the Sun (DimSun) using Controllable Swarm of Smallbody Regolith Particles

description: Global warming due to the rising levels of greenhouse gases in the atmosphere is an existential threat to humanity. This paper focuses on geoengineering using space-based solar radi- ation management. The DimSun mission concept will reduce solar insolation by 1.2% using a controlled dust cloud, made with small body regolith particles, at Solar Radiation Pressure (SRP)-balanced Sun–Earth Lagrangian L1 point. This will achieve the United Nations’ Paris Agreement target of limiting the temperature increase to 1.5◦C above pre-industrial levels during the 21st century. This will give humanity some time to permanently reduce the global levels of greenhouse gases.In this paper, we present the calculations for the size and location of the dust cloud and the key technologies necessary to enable this mission concept. In the future, once global greenhouse gas levels are permanently reduced, this method can be reversed by deactivating the control spacecraft, causing the dust cloud to disperse away from Earth within 100 days.