cometadata/datacite-titles-descriptions-related-identifiers huggingface dataset:
DOI: 10.6084/m9.figshare.24302719
title: Calibrated Data _Blockchain Plattforms' Governance Engagement

description: This is a calibrated QCA dataset based on 14 blockchain platforms. GEN_ENG indicates high generative governance engagement, EVA_ENG indicates high evaluative governance engagement, ACC indicates easy access to decision rights (thus ~ACC indicates relatively higher thresholds of access to decision rights), VISI indicates high process visibility, AUTO indicates protocol automation, INCEN1 indicates high incentives for developers and miners (thus, ~INCEN1 indicates low incentives for developers and miners), INCEN2 indicates high incentives for other stakeholders other than developers and miners (thus, ~INCEN2 indicates low incentives for other stakeholders).
DOI: 10.5281/zenodo.8436866
title: Ionospheric Connection Explorer (ICON) conjugate maneuver data used in Harding et al. (2023, submitted)

description: This dataset provides the processed ICON-MIGHTI neutral winds and ICON-IVM ion drifts that were used in the study by Harding et al. (2023, submitted). Users are welcome to contact me with any questions.
DOI: 10.5281/zenodo.8436865
title: Ionospheric Connection Explorer (ICON) conjugate maneuver data used in Harding et al. (2023, submitted)

description: This dataset provides the processed ICON-MIGHTI neutral winds and ICON-IVM ion drifts that were used in the study by Harding et al. (2023, submitted). Users are welcome to contact me with any questions.
DOI: 10.34740/kaggle/dsv/6678890
title: Global Crypto Currency Price Database
DOI: 10.48514/s52c-mh37
title: PERILS 2023 Mobile Mesonet, Sounding, Pod Data
DOI: 10.5281/zenodo.8436904
title: Membrna

description: Private repo!
description: Viva B carajo!
DOI: 10.6084/m9.figshare.24297205
title: Source_ Data_file.xlsx

description: Experimental data for the paper entitled "Operando Li metal plating diagnostics via MHz band electromagnetics"
DOI: 10.6084/m9.figshare.24297205.v1
title: Source_ Data_file.xlsx

description: Experimental data for the paper entitled "Operando Li metal plating diagnostics via MHz band electromagnetics"
DOI: 10.6084/m9.figshare.24297205.v2
title: Source_ Data_file.xlsx

description: Experimental data for the paper entitled "Operando Li metal plating diagnostics via MHz band electromagnetics"
DOI: 10.48577/jpl.dgqwcrrf
title: NASA Data and Models to Support Marine Carbon Dioxide Removal

description: No abstract available.
DOI: 10.48577/jpl.iaagxn
title: Multi-Platform Small Satellite Dynamics Testbed

description: The Small Satellite Dynamics Testbed (SSDT) at the NASA Jet Propulsion Lab (JPL) is a facility dedicated to the verification and validation of small satellite guidance, navigation, and control (GNC) hardware and software. The combination of the SSDT with NASA JPL’s Formation Control Testbed (FCT) provides a testbed for close-proximity operations between small satellites and larger, traditional spacecraft. Previously, the SSDT housed a single thrusting air-bearing platform that affords position control on a planar surface and rotational control about the axis perpendicular to the translation plane. This work outlines the design modifications to the previous air-bearing platform and implements the design to two planar air-bearing platforms. The extension to two planar air-bearing platforms enables testing of close-proximity operations between two small satellites. This work on the SSDT platforms may be combined with the capabilities of the FCT’s larger thrusting planar air bearings to produce a multi-platform testbed for close proximity operations between multiple small satellites and multiple traditional satellites. Consequently, this work fundamentally transforms the capabilities of the SSDT to enable multi-platform research and development.
DOI: 10.48577/jpl.og9btj
title: Assurance Guidance for Space Mission use of Data-Driven Machine Learning

description: We report on our experience developing guidance for assurance personnel on how to assure data-driven Machine Learning (ML) systems to be used in the space domain. The impetus for this work stems from the rapid advancement of ML techniques, the positive results of which are inspiring even relatively risk-averse space missions to seek their use. However, assurance personnel, charged with assessing the adequacy of processes and practices followed during space mission developments, are often unfamiliar with these techniques, and lack matured standards to guide their assessments.
DOI: 10.48577/jpl.yyzrdz
title: UST-Lite Direct Waveform Sampling Software-Defined Radio for Spaceflight Applications

description: The Universal Space Transponder (UST) product line developed at the Jet Propulsion Laboratory offers Software-Defined Radio (SDR) solutions for various spaceflight applications. The UST-Lite is the latest product offering that provides a more miniaturized radio package with cutting-edge processing capabilities and features by taking advantage of recent advancements in digital processing and sampling technology. Parts selection and design guidelines follow JPL flight practices suitable for missions with high reliability requirements (e.g., Discovery or New Frontiers class), but the radio could also be adapted for use on SmallSat missions given its reduced power consumption, volume, and mass compared to other JPL radios. The main digital processor is implemented with a Swift Processor Module (SPM) developed in collaboration with JPL’s Common Instrument Electronics task. The SPM uses a Kintex UltraScale FPGA (XQRKU060) with two mezzanine card slots to house application-specific circuit cards such as digital samplers, interface electronics, or additional processors. The UST-Lite uses mezzanine cards with high-speed digital samplers to directly sample and synthesize waveforms. With such direct waveform sampling approach, component counts can be drastically reduced while avoiding the use of baseband and intermediate frequency (IF) waveforms. The higher digital processing capability, coupled with expandable access to multiple high-speed samplers, allow the UST-Lite to support up to four simultaneous communication bands. The first version of the UST-Lite is targeted at supporting a quad-band link: S/Ka-band proximity, and X/Ka-band Earth communications simultaneously. This paper will provide an overview of the UST-Lite quad-band radio and its key design features, as well as optional configurations that are adaptable and configurable for mission needs. Test results from the prototype radio will be presented, as well as potential design modifications being considered for the next design revision. The current plan is to achieve TRL-5/6 by mid 2023.
DOI: 10.48577/jpl.lgikkk
title: Multi-Project Telemetry-based Digital Twin Environment for Space-Mission Development, Analysis, and Operations

description: Real-time telemetry-based, 3D situational-awareness visualizations for deep space and earth-orbiting missions have proven to be vital during all mission phases from project for- mulation, mission development, design, verification, and post- launch operations. These visualizations play key roles in sending flight system health and status to engineers and communicat- ing mission goals to stakeholders and the public. This real- time telemetry-based visualization technology has been used for many previous NASA/JPL missions including Mars 2020, Mars Science Laboratory (MSL), Low-Density Supersonic Deceler- ator (LDSD), NASA’s Soil Moisture Active Passive (SMAP), Galileo, and many NASA/JPL robotic systems research and development projects. Despite the number of missions that use these visualizations to carry out mission operations, there currently exists no multi-project environment. The current development model of building new and unique telemetry vi- sualization software systems for each new mission is extremely cost-ineffective. In this paper, we, from JPL’s Mission Control Systems Section, introduce Theia, our multi-project space mis- sion telemetry-based visualization system which we offer as a low-cost, easily configurable, multi-project system inspired by our recent work on the Entry, Descent, and Landing (EDL) sequence for the Mars 2020 Perseverance Rover mission. The Theia telemetry visualization system is an end-to-end solution that listens to a real-time telemetry or simulation data source, processes, packages, and streams that data through secure WebSockets to multiple simultaneously connected web browser clients executing our TheiaJS 3D visualization engine. TheiaJS presents the data to the user through an interactive 3D in- terface, extendable as required by individual missions. We describe Theia’s complete system design and architecture, the construction and rendering of a flight-system Digital Twin, and the data pipeline needed to accurately and continuously update the Digital Twin and its environment. We illustrate Theia’s use using historical data from two previous missions: Mars Science Laboratory (MSL) and Mars Perseverance Rover 2020, as well as data from future missions such as NISAR and Psyche. In addition, we discuss challenges, system verification, validation, and integration with predictive models and analysis tools. We further explore Theia as the core of a fully integrated real-time flight mission analysis and visualization environment.
DOI: 10.48577/jpl.n8kvzo
title: Deep Space Relay Architecture for Communications and Navigation

description: This paper discusses an evolvable deep space relay architecture that provides communications and navigation services for spacecraft in the Mars vicinity and in the inner-planets region. The deep space relay orbiter(s) are expected to be placed in strategic Mars heliocentric orbits that would mitigate the Mars superior conjunction problem for optical communications, and at the same time provide a good geometry for deep space navigation services. The study involves a multidisciplinary optimization of the relay architecture, such that the relays are optimal in their roles as both communication services provider and navigation services provider. One key objective of this paper is to investigate the deep space relay configuration that best improves the data return of optical communications with Mars users. Under the right geometric conditions, the relays will help to break up a long signal path into two shorter signal paths (2 hops), and to increase the Sun-Earth-Probe (SEP) and Sun-Probe-Earth (SPE) angles. This avoids long outages of the optical link during the Earth-Mars synodic period and helps to reduce the sky radiance noise that incidents onto the telescope, which in turn ensures that the pulse position modulated (PPM) optical link operates in a signal-power dominated, 1/range2 regime instead of a noise power dominated, 1/range4 regime, thus greatly improving the data return. On the navigation side, the deep space relay orbiters and Earth combine to form a space-based Deep Space Network (SDSN) with good geometric diversity for the space service volume that covers the Mars vicinity and the inner-planets region. This paper investigates the feasibility of using radiometric and/or optometric measurements between users at various locations within this space volume and the various assets in the SDSN for three-dimensional (3-D) kinematic positioning of the crewed or uncrewed user spacecraft.
DOI: 10.48577/jpl.teyppb
title: Design of Vector-Vortex Coronagraphs for Exoplanet Science using a Six Meter Space Telescope

description: In this paper, we present a concept for an active, 6-meter space telescope (6MST) for space-based general astrophysics and consider its potential for coronagraphy. The telescope operates in spectral regions from ∼100 nm up to 2 µm, thus having the range comparable to LUVOIR and HabEx in the longer wavelength end but extending the range up to the shorter wavelength end of Spitzer. It utilizes a vector-vortex coronagraph for exoplanet work. We evaluate the impact of Primary Mirror (PM) segment gaps on the 20% broadband contrast floor when a charge 4 or charge 6 vortex mask and two 64x64 actuators sequential Deformable Mirrors (DM’s) are used in the coronagraph, and compare the performance of a Lyot-mask and a pupil apodization mask relative to one another.
DOI: 10.48577/jpl.ujtfbc
title: Human-Autonomy Teaming for Supervised Scientific Exploration: A Pilot Study in the Wild

description: Recent robotic competitions such as the DARPA SubT Challenge have spurred novel robotic autonomy capabilities. Among these capabilities, the NeBula autonomy solution was deployed during the 2022 NASA BRAILLE field campaign to verify its ability to perform in extreme terrain. Here we describe a pilot user study investigating different interfaces and interaction modalities for real-time supervisory control of robot teams in a scientific exploration scenario. We deployed a VR-based interface and an on-screen, browser-based interface during a field campaign at the Lava Beds National Monument (CA, USA). During this field test, the terrestrial Valentine cave (a lava tube) served as a proxy for planetary subsurface environments. We tasked the human-robot team to explore, map, and locate objects of interest using varying levels of autonomy support. Here, we present first insights based on raw NASA TLX scores for four tested conditions and motivate the need for further experiments with larger participant numbers in order to obtain more statistically significant results. We further note the challenges and limitations of large-scale, real-world deployments and raise questions that could lead to valuable insights for the preparation of future planetary missions.
DOI: 10.48577/jpl.wml20k
title: Reshaping Earth: How the TOPEX and Jason satellites revolutionized oceanography and redefined climate science

description: Humans are reshaping the Earth. Not just the climate of Earth, but the planet itself. As the Earth warms due to human interference with the climate, the oceans absorb this extra heat and glaciers and ice sheets melt, causing the oceans to rise. Covering more than two thirds of the planet's surface, it means the rising oceans are literally changing the shape of the planet we call home. Since the early 1990s, a series of satellites (e.g., TOPEX-Poseidon, followed by Jason-1, Jason-2, and then Jason-3) has captured this change with remarkable accuracy. Built to measure changes in sea level, these satellites have revolutionized our understanding of the oceans, especially how the oceans store and redistribute heat around the planet, and now provide one of the most important records of how fast our climate is changing. The unprecedented success of these missions has led to the development of the Jason-CS/Sentinel-6 Mission, under a US-European collaboration, that will ensure another full decade of sea level observations. This mission includes two satellites launched 5 years apart, with the first satellite Sentinel-6 Michael Freilich launched in November 2020. In the beginning of the altimetry era, the largest uncertainties had to do with orbit determination, more recently things like radiometer stability have become important and perhaps the current and ongoing technical issues have more to do with increasing resolution and temporal sampling. This paper will summarize the history and evolution of the science, mission and technology development and programmatic mechanisms fueled by a global collaboration to achieve and sustain this crucial and unprecedented climate data record.
DOI: 10.48577/jpl.9yerof
title: Ground Terminal Evaluation for Deployable Optical Receiver Aperture (DORA)

description: Deployable Optical Receiver Aperture (DORA) is developed jointly by Jet Propulsion Laboratory (JPL) and Arizona State University (ASU). The project aims to reach Gigabits per second (Gbps) connectivity at a distance of hundreds to thousands of kilo- meters. Such connectivity will contribute to the LunaNet communication network consisting of multiple cislunar orbital and surface assets including astronauts, landers, rovers, instruments and the Lunar Gateway as well as other lunar orbiters. In this paper, we evaluated the Optical Ground Terminal (OGT) for the DORA project. A two-axis gimbal is used to control the outgoing laser pointing and tracking when the OGT receives the incoming laser. A similar multi-panel optical receiver as the DORA payload [1] is implemented as a part of the OGT. The developed DORA software module for the gimbal and Angle of Arrival (AoA) algorithm will enable autonomous tracking of the satellite by receiving and analyzing the AoA data. The ground experiment emulated a ground-satellite scenario between the OGT and the DORA payload. The pointing accuracy of the gimbal system has been evaluated by performing time and frequency domain analyses of the jitters data collected from indoor and open-air experiments. Due to atmospheric effects, the average beam divergence was found to increase in the open-air test with a distance of 34.69 m. Greater fluctuations were observed in the open-air beam divergence measurements comparing to indoor tests. We observed and analyzed fluctuations in beam size, beam position, and intensity distribution within the beam due to atmospheric inhomogeneities with digital image processing techniques. Keywords: Deployable Optical Receiver Aperture (DORA), Optical Ground Station (OGT), Angle of Arrival (AoA), Position Sensitive Detector (PSD), Degree of Freedom (DoF), Free Space Optical Communication (FSOC).
DOI: 10.48577/jpl.c7i8c6
title: Enceladus Vent Explorer Mission Architecture Trade Study

description: This paper presents the architecture trade study for the Enceladus Vent Explorer (EVE) mission concept, which would enable access to the potentially habitable subsurface ocean of Enceladus by traveling down the vent. A previous study (Ono et al. 2017) found that such a mission is technically feasible except for an extreme case where the largest vent on Enceladus has a diameter &lt; 10 cm. However, the study did not investigate whether the EVE mission is implementable within realistic constraints on launch mass, cost, and risk in the foreseeable future. Our team performed a mission architecture trade study to determine whether an implementable mission architecture exists. The trade study considered alternatives in instrumentation, mobility systems, sampling strategies, landing location, and the number of spacecraft elements. As a result, we found that EVE is implementable within Flagship mission launch mass and cost constraints but that the probability of mission success is low because of high environmental uncertainty. Our study highlights the criticality of future work along two thrusts. First, EVE would benefit from the continued development of several key technologies, including high-power tethers, miniaturization of instrumentation for chemical and biological analysis, autonomous mobility, and precision landing. Second, the substantial uncertainties in Enceladus environment conditions need to be reduced to have high confidence in mission success. We recommend that, regardless of mission-specific scientific goals, future missions to Enceladus should collect data to reduce the uncertainty in several key environmental parameters in order to reduce risk for a future vent exploration mission like EVE.
DOI: 10.48577/jpl.rqkpk5
title: 2023 IEEE Aerospace conference SRH paper

description: We present the Sample Recovery Helicopter (SRH) element that serves as the primary backup for tube retrieval as part of the Mars Sample Return (MSR) Campaign. SRH was officially incorporated into MSR in July 2022. Concept of operations, aerial and ground mobility, manipulation, avionics, thermal and telecom will be described in the context of SRH’s Mission Concept Review held in June 2022. The summarized ConOps of SRH is as follows: 1. SRH will ride along with the Sample Retrieval Lander to Mars and will deploy onto the surface. 2. SRH will perform mapping flights to aid in localization during the nominal mission. 3. SRH flies, and lands close to the tube sample depot. 4. SRH drives towards the selected sample tube and acquires it using a manipulator. 5. SRH + sample then take off, fly and land a safe distance from the lander. 6. SRH drives towards the lander and drops the sample tube onto the lander’s robotic arm workspace. SRH drives away from the robotic arm workspace. 7. The lander’s robotic arm picks up the tube from the ground and places it inside the rocket. 8. Process repeats, go to step 3.
DOI: 10.48577/jpl.7sinoj
title: Perseverance Rapid Traverse Campaign

description: Over the first 13 months of the Mars 2020 mission,the Perseverance rover traversed nearly 5 km along the JezeroCrater floor. Near the end of that period, the Science teamwas anxious to relocate to the ancient Delta region near thecrater rim, over 5 km away. A Rapid Traverse Campaign wasplanned that would prioritize use of Perseverance’s autonomousnavigation software to drive at an unprecedented high paceand minimize science activities. The Rapid Traverse Campaignstarted in March 2022 and lasted 31 Martian days. Duringthe campaign, Perseverance drove over 5 km in 24 drives,during which its autonomy software planned 94.8% of its overalldriving, enabling it to set several new planetary rover drivingrecords. Perseverance exceeded the longest daily drive distancerecord achieved by a previous planetary rover (219 meters byOpportunity in 2005) 11 times and set new records for thelongest multi-sol drive distance in a single plan (528.7 meters)and the longest continuation drive record of 699.9 meters byoperating without human drive path input during 3 sols ofdriving. This paper details the planning and execution of theRapid Traverse Campaign.
DOI: 10.48577/jpl.iaahhs
title: Towards a Model-Based Product Development Process from Early Concepts to Engineering Implementation

description: Current and future space exploration missions face challenges due to increasing technical complexity, schedule pressure, and development inefficiencies due to discontinuities in the overall system development life cycle. The impacts of these development inefficiencies are exacerbated when larger and more complex trade spaces need to be managed while encompassing the different architecture topologies and implementation options necessary to converge on a more optimal system design. This paper will discuss how Model Based Systems Engineering, specifically digital twin pipelines, can be beneficial to the product development lifecycle in a Model Based Engineering Environment. Such an approach brings modeling earlier into the design cycle, supports more perceptive system trades, and systematic qualification. Maintaining a consistent set of system models that evolve with the maturity of the design provides an integrated and collaborative development environment that will inform detailed requirements derivation and implementation decisions towards a more capable and efficient system design.