cometadata/datacite-titles-descriptions-related-identifiers huggingface dataset:
DOI: 10.48577/jpl.u9ftgs
title: Electric Propulsion for the Psyche Mission: A New Trajectory and Path to Launch

description: NASA’s Psyche mission launched on October 13th, 2023, and began its 6-year cruise to the metallic asteroid Psyche, the largest metal asteroid in the solar system. The yearlong launch delay necessitated a redesign of the cruise and orbital trajectories from the original plans, and this caused significant changes to the way the electric propulsion system will be used during the mission. The total cruise duration increased from 3.6 to 5.7 years compared to the 2022 launch case, and the system will now be operated for much longer at the lower power levels. The design of the electric propulsion system accommodated these differences with no hardware or software changes, and although the planned system usage is very different an updated thruster life validation analysis demonstrated that there is still significant life margin. Final subsystem testing prior to launch was successfully accomplished, and the spacecraft was loaded with 1085.5 kg of xenon propellant.
DOI: 10.48577/jpl.u1hzn9
title: To Boldly Go Where No Robots Have Gone Before – Part 1: EELS Robot to Spearhead a New One-Shot Exploration Paradigm with in-situ Adaptation

description: Historically, robotic space exploration has been conducted in a sequence of incrementally more sophisticated missions, starting from flyby and orbiting, followed by simple landing and roving missions, and eventually complex robotic missions involving long-range driving, drilling, or sample return. The benefit of this approach is that capabilities can be specifically designed for narrowly defined environmental conditions. For example, the development and V&V of the complex robotic functions of the Mars rover Perseverance, such as the autonomous driving and the sampling and caching system, were heavily informed by the environmental knowledge brought by previous Mars missions. However, now that NASA is destined to explore a multitude of more challenging worlds, we will likely not enjoy the luxury of sending a series of spacecraft to the same destination due to the budgetary constraints, scarcity of flight opportunities, and the extensive cruise time to the Outer Solar System and beyond. We argue that a new robotic exploration paradigm will be needed, which replaces an incremental exploration campaign with a single-shot mission where a robot or a team of robots adapts its behavior after arrival and increasingly elevates the level of behavioral complexity as it learns about the new environment. A key enabler of such adaptive one-shot exploration is highly versatile robotic hardware combined with onboard intelligence. We developed a snake-like versatile and intelligent robot, namely Exobiology Extant Life Surveyor (EELS), which would enable access to the subsurface ocean of icy moons by descending into an erupting vent, such as the ones on Enceladus. By combining its high-DOF mechanical system (Gildner, et al. 2024), the active skin propulsion system (Marteau, et al. 2024), and the new adaptive autonomy software framework called NEO Autonomy (R. Thakker, M. Paton, et al. 2023), ) we demonstrated by numerous lab and field tests that EELS can locomote in a wide range of environmental conditions, including sand-covered surface, undulating ice, high-slope snow, and vertical glacial hole, by switching between wildly different mobility gaits. It is particularly notable that EELS made ~1.5 m fully autonomous vertical descents in natural ice holes on Athabasca Glacier in Canada. This paper first highlights the limitations of the current incremental exploration paradigm and builds an argument for the adaptive, one-shot exploration paradigm by drawing insights from a number of flight and research projects. It will then provide a broad overview of the vision, technologies, scientific impacts, capabilities, and field test results of EELS, while the three companion papers (Gildner, et al. 2024), (Marteau, et al. 2024), and (R. Thakker, M. Paton, et al. 2023) provides the detailed description of the hardware, active skin propulsion, and autonomy systems of EELS, respectively.
DOI: 10.48577/jpl.w4krbm
title: Performance dryout limits of oscillating heat pipes: a comprehensive theoretical prediction from an analytical approach and experimental determination

description: The performance limits of oscillating heat pipes (OHP) have been the subject of research in recent years, in order to understand their limitations and allow their broad application in the aerospace field. The present work describes the experimental determination of the performance dryout limits for an additively-manufactured oscillating heat pipe geometry, filled with R-134a and R-123, as well as the performance limits theoretical predictions using a recently developed analytical approach. Thermal experiments were carried out using a constant temperature cold-plate approach at three cold plate temperatures, allowing the OHP device to reach steady state for each power step. Results show good agreement of performance limits predictions with experimental data for both working fluids R-134a and R-123, opening the way for the analytical framework to be used in the design and development of oscillating heat pipes.
DOI: 10.48577/jpl.3kndoy
title: Space Telemetry Analysis with PyContract

description: PyContract is a Python library for trace analysis, also characterized as an internal DSL (Domain-Specific Language). It combines flavors of state machines and rule-based programming, supporting states that can carry data, thus allowing for monitoring of events that carry data. The fact that it is a Python library offers full expressiveness, and access to a vast amount of libraries, which becomes useful for realistic situations. This is in this paper illustrated by its real life application to data analysis of telemetry logs obtained during testing of NASA’s Europa Clipper flight computer. The mission will place a spacecraft in orbit around Jupiter in order to perform a detailed investigation of its moon Europa. The analysis includes not only verifying functional correctness but also, and especially, performance analysis such as execution times and rates of change. This includes generation of data in table format and visualization as graphs. The important message is that runtime verification and data analysis are closely related topics, which can only be addressed with highly expressive specification languages.
DOI: 10.48577/jpl.ayfyrs
title: SMAP-Reflectometry: Dataset, Calibration and Sensitivities to Geophysical Parameters of Compact Polarimetric GNSS-R

description: The Soil Moisture Active Passive (SMAP) mission was conceived to provide collocated radar and radiometry measurements at L-band to estimate surface soil moisture at moderate spatial resolutions (9 km). Months after its launch, the radar suffered an anomaly that prevented its nominal operation. This was seen as an opportunity to change its central frequency to GPS L2C (1.227 GHz) [1], [2]. Since then, the SMAP radar receiver is a polarimetric Global Navigation Satellite System – Reflectometer (GNSS-R), collecting for the first time from space two orthogonal polarization components of a GNSS reflection. Initial analyses were conducted using the ratio between the two SMAP linear polarizations (Horizontal, H, and Vertical, V) [1], [3], [4], and preliminary analysis using full polarimetry (i.e., H, V, right and left-hand circularly polarized, RHCP and LHCP, respectively) where performed in [5] by synthetically composing the circular polarization components from the cross correlation of the complex voltages of the H and V channels. Recently, the authors of this abstract continued the work in [5] providing a complete mathematical definition of the polarimetric scenario defined of the SMAP-Reflectometer (SMAP-R) [6].
DOI: 10.48577/jpl.rusw8m
title: AIRS, the first of the hyperspectral satellite sounders: Breakthroughs in technology and science

description: No abstract available.
DOI: 10.48577/jpl.ke7iqw
title: The Enhanced Lander Vision System for Mars Sample Retrieval Lander Entry Descent and Landing

description: As part of the Mars Sample Return Campaign, the Sample Retrieval Lander (SRL) would receive a set of Martian rock samples collected by the Perseverance rover and send them into Mars orbit for later recovery and return to Earth. SRL is being designed to perform pin-point landing within 60 m of a pre-selected landing target without relying on a landing Doppler radar sensor. Building on the successful landing of Perseverance that demonstrated terrain relative navigation using the Lander Vision System (LVS), SRL’s Enhanced Lander Vision System (ELViS) would function as the primary integrated navigation sensor system during Entry, Descent, and Landing. ELViS would provide horizontal position, altitude, and 3D velocity estimates to the Guidance and Control system, from the heading alignment subphase of hypersonic entry to 50 m altitude above the ground. This paper describes the ELViS preliminary flight design for SRL, including concept of operations, hardware, and software architecture, as well as the expected navigation performance.
DOI: 10.48577/jpl.r9vpcm
title: Applying Assume-Guarantee Contracts with Pacti for Specifying and Analyzing System-level Functionality in Aerospace

description: No abstract available.
DOI: 10.48577/jpl.2zulg9
title: Exoplanet: Revising the Mass and Radius of a High-Demand JWST Super Earth Target

description: No abstract available.
DOI: 10.48577/jpl.vdi4u3
title: Time-resolved electron temperature of a low power Hall thruster

description: Time-dependent behavior of electrons can be critically important to Hall thruster discharge behavior. Fast Optical Emission Spectroscopy (FastOES) is a non-invasive diagnostic capable of measuring the time-resolved electron temperature of the plasma. The FastOES approach splits the collected light and isolates two distinct wavelengths that are detected by photomultiplier tubes, and amplified to a measurable signal. These measured emission lines are paired with a collisional-radiative model to determine time-resolved electron temperature. Using this technique, the FastOES results show that the electron temperature exhibits both temporal and spatial variations within the Hall thruster. There is a dynamic relationship between the electron temperature and the discharge current, with the electron temperature consistently exhibiting an out-of-phase relationship in correlation with the discharge current. Additionally, a loose scaling relationship was identified, providing valuable insights into the complex interplay within Hall thruster plasmas.
DOI: 10.48577/jpl.8nkh5g
title: A Demand Access System for Deep Space Operations

description: No abstract available.
DOI: 10.48577/jpl.5ko1yz
title: DART: Navigating to Obliteration

description: No abstract available.
DOI: 10.48577/jpl.nsm8ao
title: Updated inventory of Titan Organics

description: No abstract available.
DOI: 10.48577/jpl.bny44k
title: Softgoods Finite Element Analysis Applied to High-Precision Starshade Structure

description: This paper develops softgoods modeling methodology for high-precision structures by advancing finite element techniques. These techniques are applied to the specific challenges of the starshade technology. High-precision petal structure for starshade includes optical shield made of softgoods materials. Optical shield is a flexible membrane-like structure used to make the structure opaque and for micrometeoroid protection. On-orbit thermoelastic structural deformation of softgoods will pull on petal optical edges and increase petal optical edge distortion. Petal optical edge distortion to micrometer level is tied to optical interference stability, which uses optical destructive interference to significantly reduce star bright light before entering the telescope. This destructive interference is a part of instrument contrast performance, which is important for easier exoplanet discoveries. This research indicates that finite element analysis can be applied for analysis on-orbit shape stability of high-precision deployable structures. Starshade technology is developed by National Aeronautics and Space Administration’s Jet Propulsion Laboratory/ California Institute of Technology as a part of NASA’s Exoplanet Exploration Program. This paper describes various aspects of starshade, followed by detailed modeling approaches and the initial results.
DOI: 10.48577/jpl.xbc1yg
title: Navigation Systems Analysis: Low Cost Design and Implementation of a Security Event Logging Framework.

description: In this paper we examine design approaches and techniques to implement a low-cost Security Event Management (SEM) logging framework based on our experience deploying such systems on our mission-critical network. This is a crucial part of our efforts for the implementation and protection of mission critical flight systems used by the Mission Design and Navigation Section at NASA’s Jet Propulsion Laboratory. Spacecraft Navigation is the result of a complex interplay between numerous teams, performed on our Multi-Mission Navigation (MMNAV) Ground Data System. This paper reviews the process used to design fault tolerance and robustness into the security architecture, the goal of which is the protection of the users of the system from hostile external threats, while making their experience on the system as user-friendly and efficient as possible over the entire lifecycle of the system. Deriving from fault tolerant design concepts of fail-gently and independent failure, we focus particularly on the implications of examining and protecting the evolution of this system over time. Viewed especially against the backdrop of principles seen from Time Based Security, the design goal is a robust system that is secure from its implementation to its disposition. From this clear need for a secure, robust, high-reliability/high-availability computational environment to support navigation data processing, we have designed Security Information Event Management (SIEM) into the MMNAV Ground Data System. From system requirements, user, and administrator feedback, we developed a model for SEM for the overall system. Working with open-source software, an iterative approach was employed to capture and observe user actions and data flows, store such logs in a secure manner, and then implement a system to review and monitor such logs accordingly in real time. The goal was to have a means to examine the current security state of the entire Navigation Ground Data System as it evolved over time. While numerous security vendors will provide such ‘services’ or ‘appliances’ at a high price, we desired an affordable system that we designed and understood from the ground up under our control. This paper discusses the challenges of implementing this SIEM in a low cost, but robust framework – using the open source tools of Syslog-NG, Elasticsearch, and Kibana to create a system allowing real-time monitoring of our secure Ground Data System. We hope that this can serve as an excellent example for future missions with similar needs.
DOI: 10.48577/jpl.og4ctq
title: Multipath Fading in Space Communications: Applications, Challenges and Opportunities

description: No abstract available.
DOI: 10.48577/jpl.wuhqeb
title: Uncertainty reduction and quantification in computational thermodynamics

description: No abstract available.
DOI: 10.48577/jpl.8roitn
title: Multiphysics Level-Set Topology Optimization of a Rover Chassis for Extreme Cold Environments

description: Topology optimization is applied to design a lunar rover chassis to reduce thermal losses while maintaining adequate structural strength and stiffness. Space missions in extreme cold environments, such as the permanently shadowed regions (PSR) of the moon, are designed to reduce the power needed to maintain the minimum temperature for items that cannot operate at very low temperatures, such as electronic components. Energy consumed to maintain the temperature reduces the energy that could be used to operate instruments for improved science return. Consequently, it is essential to have an efficient thermal design while preserving the integrity of the structure. Given the design freedom it offers, topology optimization is an ideal candidate for such a task. In this work, the design of a rover chassis for extreme cold environments is investigated. The chassis is topologically optimized using the level-set method and moments-based meshfree finite element analysis with thermo-mechanical loads while the mass of the chassis is constrained to obtain a lightweight design. The main advantage of moment-based meshfree simulation is that it eliminates meshing-related bottlenecks, especially for large-scale multiphysics topology optimization problems. The objective function is defined as the weighted sum of thermal compliance and structural compliance. Several sets of weights are explored and the optimized designs are compared. The proposed methodology is reusable and extensible making it well-suited for a variety of designs for future space missions in extreme environments. The simulation and optimization tools that are developed in this study are available as a part of the software package, Intact.Generative from Intact Solutions.
DOI: 10.48577/jpl.dgj8yi
title: Spin-Carrying Quantum Centers in Wide-Band Gap Semiconductors as Magnetometry Sensors for Space Applications

description: No abstract available.
DOI: 10.48577/jpl.stogwa
title: Uranus Radiation Modeling: UMOD

description: No abstract available.
DOI: 10.48577/jpl.gm2map
title: A Validated Numerical Model of Deployment Accuracy and Repeatability of the Starshade Inner Disk Subsystem

description: No abstract available.
DOI: 10.48577/jpl.celvth
title: NASA’s Transform to Open Science (TOPS)

description: No abstract available.
DOI: 10.48577/jpl.ybfrzw
title: NASA Earthdata: Open Science Workflows Techniques

description: No abstract available.
DOI: 10.48577/jpl.oksytc
title: A Dedicated System for Multi-wavelength Monitoring of Space Weather from Young, Solar-type Stars

description: No abstract available.
DOI: 10.48577/jpl.qrgm8o
title: AIAA SciTech Psyche Panel - GNC

description: No abstract available.
DOI: 10.48577/jpl.xwpkxy
title: To Boldly Go Where No Robots Have Gone Before – Part 2: The Versatile Mobility of the EELS Robot for Robustly Exploring Unknown Environments

description: JPL has developed a snake-like robot concept called Exobiology Extant Life Surveyor (EELS) that applies a highly versatile mobility architecture and intelligent risk-aware autonomy towards exploration of unknown and uncertain environments in the solar system, such as the vents of Enceladus. The first instantiation of the EELS robot concept is called EELS 1.0, a modular snake-like robot with shape control through high degree of freedom articulation and screw-based active skin propulsion. This paper outlines the design of the EELS system and provides preliminary results of surface mobility experiments using the hardware system and autonomy software in laboratory and field settings. Through these experiments aspects of the hardware design's versatility were demonstrated through successful short traverses through terrains with varied topography and material properties. Implementation challenges related to the unique hardware architecture and their resolutions are outlined. Limitations of the EELS hardware system and avenues for further development are also discussed.
DOI: 10.48577/jpl.6luwrm
title: EELS: Advanced Autonomy and Robotics Technology at JPL

description: No abstract available.
DOI: 10.48577/jpl.exyei8
title: Benchmarking Onboard Science Data Retrieval Algorithms on the Snapdragon Platform

description: The coming decade of planetary missions will havestringent data requirements. Optimizing limited bandwidth is amajor motivation for the use of onboard science data analysisalgorithms for deep space missions. Under the traditionalmission operations paradigm, all data is sent to Earth beforefollow-on activities are planned by ground operators. Thisoperational model creates challenges for time and bandwidthconstrained mission events. The Near Earth Asteroid Scout(NEAScout) mission is a prime example of a mission with thesechallenges. NEAScout is an interplanetary CubeSat manifestedon Artemis-1. The mission will use a solar sail to navigate to aNear Earth asteroid and perform flyby reconnaissance imaging.Vehicle size, configuration, trajectory and distance from Earthall impose bandwidth constraints. To minimize theselimitations, the Project decided to move image processingcapabilities onboard the spacecraft. This onboard sciencesoftware enables image calibration, image coaddition, imagesubtraction, data compression, downsampling and cropping allonboard the spacecraft. The goal is to reduce the data downlink,without compromising science contents. NEAScout utilizes theSPHINX computing platform, whose processing performance isakin to the RAD750, but tailored for CubeSat resources.Although sufficient to enable these sorts of algorithms, theSPHINX takes multiple minutes per image, which diminishesthe prospect of using image content for rapid responsereasoning. This effort ported, characterized and benchmarkedthe performance of the NEAScout science software on theSnapdragon platform, a next-generation higher performingprocessor. Between 10x and 200x processing time speedup wasachieved, depending on the image processing algorithm, with a50x speedup for a notional image processing pipeline. This workhighlights new performance baselines for onboard science dataprocessing algorithms which missions could expect to achievewith modern computing hardware. Future avionics computerswith Snapdragon processors would enable onboard science dataanalysis to be used in more time constrained mission scenariosand with larger onboard data sets.
DOI: 10.48577/jpl.wk1zu5
title: The Enhanced Lander Vision System for Mars Sample Return Lander Entry Descent and Landing

description: No abstract available.
DOI: 10.48577/jpl.kdne5k
title: Miniaturizing Mechanical Systems for CubeSats: Design Principles and Lessons Learned

description: No abstract available.
DOI: 10.48577/jpl.wvcsph
title: Vicarious Calibration of Orbiting Carbon Observatory 3

description: No abstract available.
DOI: 10.48577/jpl.2hb17v
title: A Suite of Analyses and Tools Used to Lower Risk and Maximize Mission Success of Space Systems

description: No abstract available.
DOI: 10.48577/jpl.9cubr3
title: High speed detection of single photons with superconducting nanowire detectors

description: No abstract available.
DOI: 10.48577/jpl.jtjqbn
title: Near-Simultaneous Observations of XCO2 and NO2 Over Megacities from OCO-3 and GEMS

description: No abstract available.
DOI: 10.48577/jpl.hijztg
title: Enhanced Lander Vision System (ELViS) Algorithms for Pinpoint Landing of the Mars Sample Retrieval Lander

description: No abstract available.
DOI: 10.48577/jpl.bj81e4
title: Europa Clipper Tour and Interplanetary Trajectory Mission Design: Analysis of Probability of Impact Requirements

description: No abstract available.
DOI: 10.48577/jpl.nygfbl
title: ECOSTRESS Science and Application Highlights

description: No abstract available.