cometadata/datacite-titles-descriptions-related-identifiers huggingface dataset:
DOI: 10.48577/jpl.grmhhb
title: Two Steps Forward: Evolving Psyche’s Fault Protection Validation Post-Launch Slip

description: On October 5th, 2023, the Psyche Mission is targeted to launch to the large metallic asteroid (16) Psyche that will be exploring the exposed core material of a differentiated planetesimal-class asteroid. This unique NASA Discovery-class Mission combines a Solar Electric Propulsion (SEP) Chassis from Maxar Technologies with JPL’s contribution of avionics, flight software, and fault protection design. The Psyche Fault Protection (FP), implemented as autonomous algorithms, can detect, isolate, respond to, and recover from off-nominal conditions that may prevent mission success.The FP Verification and Validation (V&V) campaign involved numerous types of testing including FP infrastructure, monitor & response end-to-end (E2E) functionality, scenario testing, and stress and robustness testing across both high and low-fidelity venues. Due to delays in system level software testing, Psyche had to reschedule its original launch window from July 2022 to October 2023. This paper focuses on how the V&V campaign was scoped and executed prior to the launch slip and then improved after the launch slip. Adaptations included testing a comprehensive E2E regression test suite by targeting updates made to the GNC FP design, a streamlined data execution that employed variance of initial conditions and a consistent test procedure, and a robust and efficient data review strategy including tooling to automate checks. By capitalizing on the additional time, resources, and insights gained from Psyche’s launch slip, the Fault Protection V&V campaign benefited from a more comprehensive and rigorous validation process. This paper captures the knowledge and processes employed to validating Psyche’s Fault Protection design such that future FP V&V campaigns can benefit from more robust testing.
DOI: 10.48577/jpl.dw9vb9
title: Revolutionary Deployable Parabolic Reflector for Ka, W, and G-band Operation for Earth Science Mission

description: A solution for wide bandwidth high frequency (up to 240GHz) deployable reflector is needed to enable a new type of low-cost and platform-versatile Earth Science missions. Deployable mesh reflectors are limited to a maximum frequency of 60GHz due to the mesh limitations (i.e. surface accuracy and reflectivity). Leveraging on a revolutionary deployable solution, the proposed antenna can operate at frequencies up to 240GHz with an overall surface root mean squared error of 31 microns. In this paper, we are assessing the feasibility of this reflector to operate at 238.5GHz. A Ka- and W-band dual-band deployable reflector is proposed achieving excellent efficiency of 69% and 63% at Ka- and W-band.
DOI: 10.48577/jpl.xmfnie
title: Europa Clipper Tones

description: The Europa Clipper mission will study Europa, Jupiter’s moon. Europa Clipper downlink communications will typically be X-band and Ka-band telemetry. However, there are a few key scenarios in the mission where telemetry will not close the link: Jupiter Orbit Insertion (JOI) and some safe modes. At these times, the spacecraft will utilize Multiple Frequency Shift Keying (MFSK) tones for downlink communications with Earth.The safe mode scenario is new for MFSK tones. During safe mode, tones will provide early visibility into the spacecraft's health with a Deep Space Network (DSN) 34-m antenna before telemetry is available to a 70-m antenna. This early visibility will provide the spacecraft operations team with more information for spacecraft recovery. The Europa Clipper tones architecture is designed to support ground visibility into different types of spacecraft events and status in the two usage scenarios, JOI and safe mode.The tone design is flexible and tone selection criteria can be updated easily in flight. The safe mode scenario has low received signal power due to Europa Clipper’s distance from Earth. This is a challenging scenario and results in longer integration times being needed by the ground tones detection system. The design, testing, and planned operations of Europa Clipper tones are discussed and contrasted with past tones designs, including beacon tones and Mars EDL tones.
DOI: 10.48577/jpl.lzosz8
title: Demonstration of Non-Regenerative Pseudo-Noise Ranging in Parker Solar Probe and DART Missions

description: 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 transceiver 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 semi-continuously over a course of two weeks for the Double Asteroid Redirection Test (DART) mission using X-band only. Although in the past 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. 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.gnguc4
title: Radar-Based Range Estimation in Cis-Lunar Space via Fade-Resistant Signals and Algorithms

description: Abstract — There is renewed interest in human and robotic exploration of the Moon, as exemplified with NASA’s Artemis mission starting in 2024, Russia’s M1 crewed lunar flyby in 2029, and China’s Crewed Lunar Mission 1 in 2030. In addition, robotic exploration has produced a profusion of lunar orbiters, landers and other spacecraft of multi-national origin that need to be detected, monitored and characterized to ensure the safety of future missions, as well as for general cis-lunar situational awareness. In this paper we describe several promising radar-based ranging algorithms that are currently being tested using 34 meter Beam-Waveguide antennas of the Deep Space Network at the NASA Goldstone facility in California. These algorithms rely on week reflected echoes that do not require a co-operative transponder on the spacecraft, hence can be used to detect and characterize non-cooperative or lost spacecraft, as well as near-earth asteroids and other objects of interest in the cis-lunar environment. The algorithms described and evaluated here utilize radar echoes received from the decommissioned geo-synchronous NOAA satellite GOES-11, and rely on precisely timed amplitude-modulated frequency ramps that are less sensitive to deep fades in the received radar signals to first detect the presence of the echo via short-term FFTs, then determine the start-time via the application of zone-filtered inverse FFTs to minimize noise and reconstruct the received time-sequence. The reconstructed frequency-ramp is further analyzed by extracting the beat-note generated by the round-trip delay with frequency proportional to the round-trip light time, and compared with PN-coded ranging techniques to evaluate the potential improvement over conventional correlation-based ranging techniques.
DOI: 10.48577/jpl.mswn6a
title: Sample Retrieval Lander Preliminary Surface Thermal Design

description: The Sample Retrieval Lander (SRL), an element of the planned Mars Sample Return (MSR) Campaign, is scheduled for a launch in July 2028 and a landing on the Mars surface in October 2030. The solar-powered Lander would operate for 235 Sols (from Ls = 40 degrees to Ls= 150 degrees) during the surface phase of the mission. The primary goal of the Lander would be to transfer sample tubes containing Mars atmosphere, rock and regolith samples from NASA’s Mars 2020 Perseverance Rover into the Orbiting Sample (OS) portion of the Mars Launch System (MLS). The Lander would eject the Mars Launch System, a two-stage rocket designed to place the OS into orbit around Mars, at the end of the surface mission. This paper presents the preliminary surface thermal design of the SRL Lander.
DOI: 10.48577/jpl.noka3u
title: Advances in Microvalve and Micro Pre-concentrator Technology for the Space Atmosphere Monitor Instrument: From Research to the International Space Station

description: This paper delves into the iterative evolution of microelectromechanical system (MEMS) Microvalve (MV) and pre-concentrator (PC) generations designed for the Spacecraft Atmosphere Monitor (S.A.M.) instrument, a critical component of the International Space Station’s (ISS) air quality monitoring system. Covering design, simulation, and characterization, this paper includes the latest generation of PC and MV that meets and exceeds all key performance requirements of S.A.M. Deployed on the ISS in 2023, MV XXI exemplifies ongoing advancements in MV technology for space applications.
DOI: 10.48577/jpl.ngvcne
title: Development and Execution of the Mars 2020 Perseverance Rover’s Sampling Strategy

description: A primary objective of NASA’s Mars 2020 Perseverance rover mission is to collect and store a scientifically compelling set of geologic samples from the martian surface for possible return to Earth. If returned, these samples would enable years of scientific investigation and discovery with more capable instrumentation than can be sized for a Mars rover. To maximize the efficiency and science return of sampling operations on Mars, the Mars 2020 Science Team developed a minimum set of required observations to be performed at each sampling site. These observations provide a consistent set of sample characterization and documentation and include use of Perseverance’s remote and proximity science instruments and are compiled in the Standardized Observation Protocol (or STOP List). STOP List observations, along with other required activities that enable engineering/robotic arm operations, were assembled into a strategically developed product called the Sampling Sol Path (SSP). The SSP outlines a sol-by-sol (daily) order of events at a sampling site, starting with the initial drive to the site, acquisition of engineering and STOP List observations, sample coring and processing, and drive away. The purpose of the SSP and STOP List is to ensure consistency and repeatability across sampling events, inform planning constraints and activity dependencies, and minimize tactical decision-making during operations.While the intent and overall format of the SSP remain constant, it is an evolving strategic operations product, responding to the evolving science and engineering needs to support sampling operations in Jezero crater. Despite the efficiency and repeatability enabled by the strategic SSP products, no two sampling events have looked the same on Mars. The SSP defines the absolute minimum set of activities and sols required to complete each sampling event. This strategy allows flexibility to insert additional opportunistic science observations throughout the sol path, as long as these additions remain within the scope and sol allocation of Perseverance’s current science campaign. The SSP will continue to be utilized for the collection of Perseverance’s remaining samples to maximize operational efficiency while also allowing opportunities for discovery-driven science
DOI: 10.48577/jpl.ss1zy8
title: Prometheus: An Io Plume Sample Return Concept

description: Volcanic plumes on Io have been observed during every spacecraft encounter from Voyager to Juno. The material within the plume ejecta provides direct insight into Io’s composition in the form of volcanic gases and pyroclastic grains. Return of these ejecta materials would provide a window into Io’s origins and would represent the next logical step in sample return, and in the exploration of the Jupiter system. The Prometheus Io Sample Return mission concept proposes to collect a plume sample, supported by remote observations to provide scientific context. The Prometheus mission concept can be tailored to either a Discovery or New Frontiers scope, informed by both the Visions and Voyages (V&V) and Origins, Worlds, and Life (OWL) Decadal Surveys. In particular, it responds to the New Frontiers 5 objectives for an Io Observer mission. Additional science from the returned sample would address important questions related to the formation of the Solar System and Jupiter’s circumplanetary disk. To accomplish these objectives, the sample collection system (SCS) draws on the aerogel designs of Stardust and the Genesis sampling plates made of pure materials. A suite of remote sensing instruments supports the targeting and contextualization of plume samples. To safely collect the sample, the spacecraft must be capable of surviving the challenging radiation environment inside of Callisto’s orbit as well as the micrometeoroid and orbital debris (MMOD) environment when sampling Io’s plumes. These obstacles are overcome by applying flight-proven technologies from missions operating in similar environments: Juno, Europa Clipper, and Stardust. The flight system selected for the mission concept is a solar-powered Lucylike spacecraft bus with Stardust-like sample return capsule (SRC) which houses and deploys the SCS. Ram-facing Whipple shields protect the solar arrays and payload from the particles in the plume and a radiation vault protects spacecraft compute elements from Jupiter’s strong radiation environment. In this paper we first address the science rationale for the Prometheus mission and how this feeds into mission goals and objectives. We next describe a potential science payload alongside a concept of operations. We summarize the technical details of the mission concept and architectural options. Two trajectory options are discussed, one synergistically combining sample collection and complementary remote science and the other prioritizing the sample collection. Finally, the details of the baseline of the flight system and design trades are described.
DOI: 10.48577/jpl.h6vtpc
title: Horn Feed Assembly Modification for INCUS

description: INCUS (INvestigation of Convective UpdraftS) is an Earth Science project approved by NASA in 2022. The goal of the mission is to study in detail how water vapor and droplets move inside tropical storms and thunderstorms and understand their effects on weather and climate models. To carry out this study, the mission will use three almost identical SmallSats, each one equipped with a Ka-band radar heritage of Raincube. The deployable mesh reflector antenna is a new 1.6 m design provided by Tendeg. This paper presents the general architecture of the three observatories with particular emphasis on the radar antenna subsystem design. In particular, the design and fabrication of the feed assembly will be presented along with measured and calculated RF performance parameters. Modified horn designs based on the measurement observations will also be presented.
DOI: 10.48577/jpl.dhtze4
title: Thermal is the Plan, the Plan is Death: Deployment of the Mars2020 On-Board Planner

description: As the Mars 2020 rover mission has transitioned into use of an autonomous scheduling and execution framework known as “On-Board Planner” in October 2023, only one domain of its functionality has continued to produce complexity and churn in the flight and ground implementation. This parallel thread of thermal control for Mars2020’s actuators and instruments services a variety of use patterns in operations that must all be accommodated without substantially delaying or dropping activities, in support of On-Board Planner’s foundational objective to augment mission throughput by reducing energy use and increasing available time. If OBP stumbles, it’s fair to predict that the root cause will likely be related to thermal control. This paper discusses some of the design history and underlying reasoning for changes made since prior reporting, some of the fact patterns that breed different strategies for provisioning thermal configuration and what those strategies are, and flight data analysis of early flight operations.
DOI: 10.48577/jpl.wdvmh8
title: Driving Down Risk in the Psyche Fault Protection Design Post Launch Slip

description: The Psyche Mission is a NASA Discovery-class Mission to explore (16) Psyche, a large metallic asteroid that orbits the sun between 2.5 and 3.3 au. The spacecraft bus is a repurposed earth-orbiting telecommunication satellite bus developed by Maxar, combined with Avionics and software developed by JPL. To ensure this earth-orbiting spacecraft bus can survive the lengthy journey into deep space, a robust fault protection function was designed, implemented, and tested. Originally scheduled for July 2022, the launch date was postponed to October 2023 due to delays during system-level testing of the spacecraft. By the time the launch slip was announced, the fault protection design was fully implemented in software, and the V&V program was nearly complete. Consequently, the team found themselves with an additional year of unplanned development time, which provided the unique opportunity to revisit parts of the fault protection design, implementation, and V&V strategy prior to launch, while incorporating lessons learned from the previous year of testing.This paper provides an overview of the efforts taken to drive down risk in the Psyche fault protection design after the launch slip. These efforts can be split into three categories: additional “deep dive” analyses targeting higher risk areas of the design, improvements to the design and implementation that resulted in software changes, and the development of a rich set of high-fidelity risk reduction test cases meant to validate the fault protection function. This paper discusses the motivating concerns that drove each of these efforts and explains how lessons learned were incorporated into the post-launch slip development work. It summarizes the analyses that were spawned and explains the methods that were used to constrain and complete each analysis. It captures the trades made when deciding which design changes and software bug fixes to implement, and describes the processes used to implement and verify those changes in an agile manner. Finally, the paper captures the brainstorming process for devising a set of risk reduction tests used to improve confidence in the fault protection design, and validate its performance over a wide range of scenarios.
DOI: 10.48577/jpl.soza6t
title: Measuring Earth’s Energy Imbalance with “Space Balls”

description: The presented research aims at refining the “Space Balls” mission concept, which is in its infancy of formulation and aims to obtain high-accuracy estimates of Earth’s Energy Imbalance (EEI), the globally and annually integrated net radiative flux at the top-of-the-atmosphere (TOA). The measurement of net radiative flux is facilitated through sensing radiation pressure accelerations acting on a (or multiple) near-spherical low-Earth orbiting spacecraft(s). While an accelerometer at the center of the spacecraft senses the non-gravitational orbit perturbations, the absorbing-reflecting spacecraft skin represents the detector itself, translating the impact of radiation pressure force into sensible accelerations. As with any observing system, this idea faces a multitude of technological and scientific challenges, such as related to the spacecraft characteristics themselves. The shape and thermo-optical properties are crucial for establishing a proportional relationship between impinging photons and the induced acceleration. Another difficulty arises from confounding forces and effects that may impede on radiation pressure acceleration, such as drag. To simulate and assess associated uncertainty, we develop a simulation environment based on Monte, a high-fidelity orbit navigation and mission design software. EEI represents the rate of planetary heat uptake in response to anthropogenic and natural radiative forcings and feedbacks and drives climate change as we see and feel it. Existing radiometers measure the incoming and outgoing radiative fluxes at TOA, but their uncertainties are too large to derive the residual net radiative flux with sufficient accuracy. This direct EEI measurement would be unprecedented and a vital piece in quantifying and better understanding global climate change. The overall feasibility of this approach has been demonstrated in the late 1970’s (Cactus accelerometer on Castor satellite), but a dedicated EEI mission does not exist to this day. The capabilities of accelerometers are now at a stage where this measurement might become feasible at the required accuracy and precision.
DOI: 10.48577/jpl.yl9lnl
title: Web-based 3D Visualization for Flight Mission Network Cybersecurity Analysis

description: The Cyber Analysis Visualization Environment (CAVE) software system is a collaboration between the Systems Engineering and Mission Systems and Operations Divisions at JPL. CAVE is an easy to use, model-based cyber threat visual- ization, analysis, and assessment platform designed to respond to the growing threat of cyber attacks targeting space missions. CAVE was originally designed and developed as a Python- based desktop application with integrated 3D visualization, user interface, and a cyber analysis engine, before a recent redesign to the current client/server web-based application architecture. This new client/server web application architecture allows users to use CAVE on multiple platforms, requiring minimal or no software installation on their local systems while still allowing for a level of customizability at the user level. CAVE’s client/server architecture ensures that sensitive or proprietary data always resides securely on the CAVE analysis server, thereby avoiding the storage of any sensitive data on the end user‘s local machine. At the high level, the CAVE web server exposes a REST API to allow the web GUI to communicate with the analysis engine. The web server has user authentication capabilities, and restricts access to model data based on the assigned group of the authenticated user. The server is architected with a plugin structure in mind for analyses, so that anyone opting to deploy the CAVE server can easily write and deploy additional model analyses. Model data is stored in a Mongo database and delivered to the client via authenticated HTTPS request. The client handles all interactions with the web server and provides feedback to the user on the status of server requests. CAVE’s web-browser user interface provides an intuitive, 3D presentation of complex network models, containing both physical and virtual network assets, which allows mission cybersecurity engineers to easily swap between a selection of visual layouts and execute a variety of cybersecurity analyses algorithms designed to help users better understand possible network vulnerabilities and defenses. This web-based user interface model allows for ease of expansion and potential future additions to the user experience, including real- time collaboration and sharing capabilities, and the interactive exploration of large cybersecurity datasets. In this paper we present CAVE’s software architecture and use cases, and discuss CAVE’s value as an intuitive tool for cyber threat identification and assessment.