Sandia and Space Nuclear Systems Launch Safety
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Clayton, Daniel James↗
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SFM - Sandia Fireball Model
SAND2022-13231 O Sandia Fireball Model is used in the assessment of liquid propellant fireballs in the source term analysis for space nuclear systems launch safety. Sandia National Laboratories is a multimission laboratory managed and operated by National Technology & Engineering Solutions of Sandia, LLC, a wholly owned subsidiary of Honeywell International Inc., for the U.S. Department of Energy’s National Nuclear Security Administration under contract DE-NA0003525.
Powers, Dana↗
Supercritical Brayton Power Conversion with a Direct Cooled Reactor for Space Power
To achieve future goals in space exploration a long life, compact power system will be necessary, and nuclear power sources are a promising option. The goal of this project is to achieve mass optimization with a supercritical Brayton Cycle coupled to a direct-cooled nuclear reactor. It is critical to minimize the total mass of this system because of space launch costs. The total mass involves both the components’ masses as well as the fuel mass which is related to system efficiency. This paper discusses a project in which a detailed reactor model is integrated with a carefully constructed cycle model in order to simultaneously optimize the design of these two aspects of the system. Component models are discussed as well as an initial optimization study. A robust, simple recuperated Brayton cycle model is complete and is in the process of integration with a developing reactor model. Preliminary observations of the cycle model have led to the conclusion that there will be an optimum point between a large recuperator and small reactor with high system efficiency, and a large reactor and small recuperator with low recuperator mass for any given radiater size. Once the reactor model is integrated into the cycle optimization, the tradeoffs between the sizes of the radiator, recuperator, and reactor will be further investigated and an optimum system mass will be apparent.
21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS↗
Supercritical Brayton Power Conversion with a Direct Cooled Reactor for Space Power
To achieve future goals in space exploration a long life, compact power system will be necessary, and nuclear power sources are a promising option. The goal of this project is to achieve mass optimization with a supercritical Brayton Cycle coupled to a direct-cooled nuclear reactor. It is critical to minimize the total mass of this system because of space launch costs. The total mass involves both the components’ masses as well as the fuel mass which is related to system efficiency. This paper discusses a project in which a detailed reactor model is integrated with a carefully constructed cycle model in order to simultaneously optimize the design of these two aspects of the system. Component models are discussed as well as an initial optimization study. A robust, simple recuperated Brayton cycle model is complete and is in the process of integration with a developing reactor model. Preliminary observations of the cycle model have led to the conclusion that there will be an optimum point between a large recuperator and small reactor with high system efficiency, and a large reactor and small recuperator with low recuperator mass for any given radiater size. Once the reactor model is integrated into the cycle optimization, the tradeoffs between the sizes of the radiator, recuperator, and reactor will be further investigated and an optimum system mass will be apparent.
21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS↗
Mass optimization of a supercritical CO 2 Brayton cycle with a direct cooled nuclear reactor for space surface power
A long life, reliable, and compact surface power system will be necessary to achieve future goals in space exploration. This application uniquely requires the system to be optimized with respect to mass because system mass directly drives the space launch cost associated with transporting the system to its desired location. In this study, a supercritical CO 2 Brayton cycle coupled to a direct-cooled nuclear reactor was designed and optimized for mass. Robust models were developed for each Brayton cycle component in order to model the cycle performance. The three most massive components of this cycle are the radiator-based heat rejection system (subsequently referred to as the “radiator”), recuperator, and reactor. Mass correlations for the recuperator and radiator were established through interactions with component experts from industry and national labs. A reactor model was developed to predict the minimum mass reactor that satisfies neutronic and thermal limitations for given cycle conditions. The system optimization explores tradeoffs between the reactor, recuperator, and radiator sizes in order to identify the least massive system that will satisfy the power (40 kWe) and life (10 yr) requirements. To explore the effects of turbine inlet temperature on system mass, three types of microtube and shell recuperator technologies were considered: baseline stainless steel (which is consistent with the industry partner’s current designs), stainless steel with non-heritage tube sizes (which requires further development of manufacturing techniques), and Inconel (which is not a current/legacy design). Both stainless steel designs have a temperature limit of 823 K, which limits the turbine inlet temperature to 900 K. The baseline stainless steel design results in a combined mass of 738 kg. The stainless steel design allowing for non-heritage tube sizes reduces the combined mass to 674 kg (a 9% improvement). The Inconel design leads to an optimal turbine inlet temperature of 1120 K and reduces the combined mass to 391 kg (a 47% improvement). Furthermore, the interesting conclusion from this study include: (1) radiator mass dominates the total mass, and this drives the cycle to relatively high heat rejection temperatures resulting in a compressor inlet state point that is not close to the vapor dome; thus, the typical advantages of an sCO 2 system are not realized, and a working fluid with a higher critical temperature may be more suitable, and (2) neutronic limitations cause the reactor size to be relatively unaffected by the power level.
42 ENGINEERING↗
Doubling off-axis electron cyclotron current drive efficiency via velocity space engineering
For the first time, experiments on the DIII-D tokamak have demonstrated electron cyclotron current drive with more than double the conventional efficiency by tailoring the wave–particle interactions in velocity space using a novel ‘top launch’ geometry. Steering the EC waves to propagate nearly parallel to the resonance drives current more efficiently by (1) selective damping on electrons with higher parallel velocity v ||, and (2) longer absorption path to compensate for inherently weaker absorption at higher v ||. Experiments using a fixed-injection top launch system find an optimal velocity space interaction for maximum current drive efficiency at ρ ~ 0.5 where the ease of drawing out a high v || electron tail is balanced by sufficient absorption.
70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
Launch Accident Sequence Evaluation Program
SAND2024-09978O The Launch Accident Sequence Evaluation Program is used to calculate the source term for the consequence analysis involving a launch vehicle accident with a space nuclear system. Sandia National Laboratories is a multimission laboratory managed and operated by National Technology & Engineering Solutions of Sandia, LLC, a wholly owned subsidiary of Honeywell International Inc., for the U.S. Department of Energy’s National Nuclear Security Administration under contract DE-NA0003525.
Kalinich, Donald↗
An Optimization-Based Framework to Define the Probabilistic Design Space of Pharmaceutical Processes with Model Uncertainty
To increase manufacturing flexibility and system understanding in pharmaceutical development, the FDA launched the quality by design (QbD) initiative. Within QbD, the design space is the multidimensional region (of the input variables and process parameters) where product quality is assured. Given the high cost of extensive experimentation, there is a need for computational methods to estimate the probabilistic design space that considers interactions between critical process parameters and critical quality attributes, as well as model uncertainty. In this paper we propose two algorithms that extend the flexibility test and flexibility index formulations to replace simulation-based analysis and identify the probabilistic design space more efficiently. The effectiveness and computational efficiency of these approaches is shown on a small example and an industrial case study.
60 APPLIED LIFE SCIENCES↗
New Los Alamos space instrument goes for a spin
Scientists and engineers at Los Alamos National Laboratory are using a unique centrifuge facility to evaluate a flight-ready telemetry system for evaluating a nuclear weapons test missile launch. "The telemetry unit was designed and manufactured by Los Alamos' Intelligence and Space Research Division," said Telemetry Program Manager Myles Fitzgerald. "Telemetry is a data stream of information on temperature, acceleration, vibration, strain, all the conditions a system encounters during a test flight." Because a test missile flight ultimately ends with the test system completely destroyed, telemetry data from the flight must be collected by receiving stations along the flight path. "The purpose of the centrifuge test is to subject the electronics to a high gravitational load (G-load) that's representative of what the system will experience when re-entering the Earth's atmosphere," said weapons test engineer Alex Cusick.
45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEF↗
New Los Alamos space instrument goes for a spin
Scientists and engineers at Los Alamos National Laboratory are using a unique centrifuge facility to evaluate a flight-ready telemetry system for evaluating a nuclear weapons test missile launch. "The telemetry unit was designed and manufactured by Los Alamos' Intelligence and Space Research Division," said Telemetry Program Manager Myles Fitzgerald. "Telemetry is a data stream of information on temperature, acceleration, vibration, strain, all the conditions a system encounters during a test flight." Because a test missile flight ultimately ends with the test system completely destroyed, telemetry data from the flight must be collected by receiving stations along the flight path. "The purpose of the centrifuge test is to subject the electronics to a high gravitational load (G-load) that's representative of what the system will experience when re-entering the Earth's atmosphere," said weapons test engineer Alex Cusick.
45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEF↗
Constant Rate Production: DOE Approach to Meeting NASA Needs for Radioisotope Power Systems for Nuclear-Enabled Launches
The use of radioisotope power systems (RPSs) for nuclear-enabled National Aeronautics and Space Administration (NASA) missions is made possible through a long-standing arrangement between the Department of Energy (DOE) and NASA. The requirements for the power system come from NASA, but DOE performs the procurement, fueling, testing, and delivery. A challenge has been interplay between the schedule for RPS availability from DOE versus the schedule for competitively selected missions. By mutual agreement, the actual operations to procure an RPS and prepare it for fueling have always been delayed until the final selection of a mission. The timeline for a New Frontiers–class mission leaves approximately 5 to 6 years from the time of final mission selection to the actual launch date. The number of RPSs used for a New Frontiers–class mission can be one to three units. If one or two units are needed, the timeline from the decision point to the launch date is a challenge, but it is achievable. The activities taking place include manufacturing the power system, producing the fuel, and performing the assembly/testing and delivery operations. If the mission selected requires three RPSs, the logistics of accomplishing all activities during the 5–6 years is problematic. The challenge involves obtaining the necessary resources for plutonium production, heat source production, and assembly/testing operations. Typically, the time between RPS-enabled missions requires staffing reduction down to 65%–75% of peak staffing levels to reduce costs. Coupling the ~2 year duration needed for hiring, training, and obtaining the appropriate security clearances for the required staff with the requirement for the RPS to arrive at Kennedy Space Center 6 months before the launch erodes much of the 5–6 years available to comfortably support the use of three RPSs. To provide better support for NASA RPS missions, a different approach for the production of heat sources was devised—constant rate production. This involves a higher level of base capability at DOE national laboratories to provide a stabilized workforce. This will enable 10–15 heat sources to be produced annually and placed into a stable intermediate form to enable storage for up to several years leading to quick production of general purpose heat source modules when a mission is selected. The upfront production of 238 Pu is maintained so material is constantly in the pipeline. Production of key specialized components is also maintained using this model.
42 ENGINEERING↗
MULTI-MISSION THERMOELECTRIC GENERATOR ASSEMBLY TESTING AND LAUNCH OPERATIONS FOR MARS 2020
The Space Nuclear Power and Isotope Technologies (SNPIT) division at Idaho National Laboratory (INL) fuels, performs acceptance testing, and provides spacecraft integration support of Radioisotope Power Systems (RPS) in support of National Aeronautics and Space Administration (NASA) missions. Recently the SNPIT team completed assembly, testing and launch support of the Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) for the Mars 2020 Perseverance Rover mission.
07 ISOTOPE AND RADIATION SOURCES↗
MULTI-MISSION THERMOELECTRIC GENERATOR ASSEMBLY TESTING AND LAUNCH OPERATIONS FOR MARS 2020
The Space Nuclear Power and Isotope Technologies (SNPIT) division at Idaho National Laboratory (INL) fuels, performs acceptance testing, and provides spacecraft integration support of Radioisotope Power Systems (RPS) in support of National Aeronautics and Space Administration (NASA) missions. Recently the SNPIT team completed assembly, testing and launch support of the Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) for the Mars 2020 Perseverance Rover mission.
07 ISOTOPE AND RADIATION SOURCES↗
Spectroscopic Characterization of Key Aromatic and Heterocyclic Molecules: A Route toward the Origin of Life
To gain information on the abiotic synthesis of the building blocks of life from simple molecules, and their subsequent chemical evolution to biological systems, the starting point is the identification of target species in Titan-like planets; i.e., planets that resemble the primitive Earth, as well as in Earth-like planets in the habitable zone of their star, namely planets where life can be already originated. In this scenario, molecular spectroscopy plays a crucial role because spectroscopic signatures are at the basis of an unequivocal proof for the presence of these target molecules. Thanks to advances in many different techniques and NASA’s successful Kepler exoplanet transit mission, thousands of diverse planets outside of our solar system have been discovered. The James Webb Space Telescope (JWST), scheduled to be launched in 2018, will be very helpful in the identification of biosignature gases in Earth-like planets’ atmospheres and prebiotic molecule signatures in Titan-like atmospheres, by observing their absorption during transits. Although the search for key-target molecules in exoplanet atmospheres can be carried out by the JWST Transit Spectroscopy in the infrared (IR) region (0.6–29 μm wavelength range), opportunities for their detection in protostellar cores, protoplanetary disks, and on Titan are also offered by interferometric high spectral and spatial resolution observations using the Atacama Large Millimeter/submillimeter Array. In the present work, target molecules have been selected, and their spectroscopic characterization presented in view of supporting their infrared and complementary millimeter/submillimeter-wave spectral observations. In detail, the selected target molecules include: (1) the three-membered oxygen-containing heterocycles, oxirane and protonated oxirane; (2) the cyclopropenyl cation and its methyl derivative; (3) two examples of ortho- and peri-fused tri-cyclic aromatic rings, i.e., the phenalenyl cation (C{sub 13}H{sub 9}{sup +}) and anion (C{sub 13}H{sub 9}{sup -}); and (4) uracil, a specific RNA base.
79 ASTRONOMY AND ASTROPHYSICS↗
X-Ray Imaging and Spectroscopy Mission
The X-Ray Imaging and Spectroscopy Mission (XRISM) is a joint mission between the Japan Aerospace Exploration Agency (JAXA) and the National Aeronautics and Space Administration (NASA) in collaboration with the European Space Agency (ESA). In addition to the three space agencies, universities and research institutes from Japan, North America, and Europe have joined to contribute to developing satellite and onboard instruments, data-processing software, and the scientific observation program. XRISM is the successor to the ASTRO-H (Hitomi) mission, which ended prematurely in 2016. Its primary science goal is to examine astrophysical problems with precise, high-resolution X-ray spectroscopy. XRISM promises to discover new horizons in X-ray astronomy. It carries a 6 × 6 pixelized X-ray microcalorimeter on the focal plane of an X-ray mirror assembly (Resolve) and a co-aligned X-ray CCD camera (Xtend) that covers the same energy band over a large field of view. XRISM utilizes the Hitomi heritage, but all designs were reviewed. The attitude and orbit control system was improved in hardware and software. The spacecraft was launched from the JAXA Tanegashima Space Center on 2023 September 6 (UTC). During the in-orbit commissioning phase, the onboard components were activated. Although the gate valve protecting the Resolve sensor with a thin beryllium X-ray entrance window was not yet opened, scientific observation started in 2024 February with the planned performance verification observation program. The nominal observation program commenced with the following guest observation program beginning in 2024 September.
Astronomy and AstroPhysics↗
Pandora Telescope Isolation Systems Engineering Project
The collective imagination of humanity has always been captured by the possibility of other habitable planets. Only with recent advances in spacecraft and our understanding of astrophysics, has it become possible to study the atmospheres of planets orbiting stars other than our sun, also known as extrasolar planets or exoplanets. We know from the Keplar Space telescope, launched in the early 1990s, that there are more planets than stars in the Milky Way. The Transiting Exoplanet Survey Satellite, TESS, will continue the search for exoplanets outside our solar system. Two other well know telescopes with the capability to study exoplanets are the James Webb Space Telescope (JWST) and Hubble Space Telescope (HST). Together they provide full spectral coverage to do short deep dives into planets of interest, but tasking these satellites is both expensive and hard to obtain. A new mission dedicated to the characterization of exoplanets and the stars they orbit is needed to fill the gap.
42 ENGINEERING↗
Modular space vehicle boards, control software, reprogramming, and failure recovery
A space vehicle may have a modular board configuration that commonly uses some or all components and a common operating system for at least some of the boards. Each modular board may have its own dedicated processing, and processing loads may be distributed. The space vehicle may be reprogrammable, and may be launched without code that enables all functionality and/or components. Code errors may be detected and the space vehicle may be reset to a working code version to prevent system failure.
33 ADVANCED PROPULSION SYSTEMS↗