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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 1,639 records · Page 91
All sourcesNASA NTRSDOE OSTI
NASA NTRS2013

Aerodynamic and Acoustic Flight Test Results for the Stratospheric Observatory for Infrared Astronomy

As part of the Stratospheric Observatory for Infrared Astronomy (SOFIA) program, a 747SP airplane was modified to carry a 2.5 meter telescope in the aft section of the fuselage. The resulting airborne observatory allows for observations above 99 percent of the water vapor in the atmosphere. The open cavity created by the modifications had the potential to significantly affect the airplane in the areas of aerodynamics and acoustics. Several series of flight tests were conducted to clear the airplanes operating envelope for astronomical observations, planned to be performed between the altitudes of 39,000 feet and 45,000 feet. The flight tests were successfully completed. Cavity acoustics were below design limits, and the overall acoustic characteristics of the cavity were better than expected. The modification did have some effects on the stability and control of the airplane, but these effects were not significant. Airplane air data systems were not affected by the modifications. This paper describes the methods used to examine the aerodynamics and acoustic data from the flight tests and provides a discussion of the flight test results in the areas of cavity acoustics, stability and control, and air data.

SOFIA↗
NASA NTRS2014

Aerodynamic and Acoustic Flight Test Results and Results for the Stratospheric Observatory for Infrared Astronomy

As part of the Stratospheric Observatory for Infrared Astronomy program, a 747SP airplane was modified to carry a 2.5-m telescope in the aft section of the fuselage. The resulting airborne observatory allows for observations above 99 percent of the water vapor in the atmosphere. The open cavity created by the modifications had the potential to significantly affect the airplane in the areas of aerodynamics and acoustics. Several series of flight tests were conducted to clear the operating envelope of the airplane for astronomical observations, planned to be performed between the altitudes of 35,000 ft and 45,000 ft. The flight tests were successfully completed. Cavity acoustics were below design limits, and the overall acoustic characteristics of the cavity were better than expected. The modification did have some effects on the stability and control of the airplane, but these effects were not significant. Airplane air data systems were not affected by the modifications. This paper describes the methods used to examine the aerodynamics and acoustic data from the flight tests and provides a discussion of the flight-test results in the areas of cavity acoustics, stability and control, and air data.

SOFIA↗
NASA NTRS2013

Giving Birth to the James Webb Space Telescope: Part 2

The ASP concludes its inside look at the James Webb Space Telescope (JWST) with the second half of a two-part Astronomy Beat. In the previous issue (110), John Mather described the early days of the Webb project, including budget constraints and the challenge of designing an observatory that was completely impossible to build withold technologies. Now that the instruments are mostly complete, John looks at what remains to do prior to launch.

Giving↗
NASA NTRS2019

Loftid Aeroshell Engineering Development Unit Structural Testing

NASA’s Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology was selected for a Technology Demonstration Mission under the Space Technology Mission Directorate in 2017. HIAD is an enabling technology that can facilitate atmospheric entry of heavy payloads to planets such as Earth and Mars using a deployable aeroshell. The deployable nature of the HIAD technology allows it to avoid the size constraints imposed on current rigid aeroshell entry systems. This enables use of larger aeroshells resulting in increased entry system performance (e.g. higher pay-load mass and/or volume, higher landing altitude at Mars). The Low Earth Orbit Flight Test of an Inflatable Decelerator (LOFTID) is currently scheduled for late-2021. LOFTID will be launched out of Vandenberg Air Force Base as a secondary payload on an Atlas V rocket. The flight test features a 6m diameter, 70-deg sphere-cone aeroshell and will provide invaluable high-energy orbital re-entry flight data. This data will be essential in supporting the HIAD team to mature the technology to diameters of 10m and greater. Aeroshells of this scale are applicable to potential near-term commercial applications and future NASA missions. Currently the LOFTID project has completed fabrication of the engineering design unit (EDU) inflatable structure (IS) and the flexible thermal protection system (F-TPS). These two components along with the rigid nose and center body comprise the HIAD aeroshell system. This EDU aeroshell is the precursor to the LOFTID aeroshell that will be used for flight. The EDU was built to verify the design given the subtle differences between the LOFTID aeroshell and past aeroshell designs that have been fabricated under the NASA HIAD project. To characterize the structural performance of the LOFTID aeroshell design, three structural tests will be performed. The first test to be conducted is static load testing, which will induce a uniform load across the forward surface of the aeroshell to simulate the expected pressure forces during atmospheric entry. The IS integrated with the rigid center body will first be tested alone to provide data for analytical model correlation, and then the F-TPS will be integrated for a second series of static load testing of the full aeroshell system. Instrumentation will be employed during the test series to measure component loads during testing, and a laser scanner will be used to generate a 3D map of the aeroshell surface to verify that the shape of the structure is acceptable at the simulated flight loads. After static load testing, pack and deployment testing will be conducted multiple times on the integrated system to demonstrate the aeroshell’s ability to fit within the required packed volume for the LOFTID mission without experiencing significant damage. Finally, the aeroshell will undergo modal testing to characterize its structural response. This presentation will discuss the setup and execution of each of the three tests that the EDU aeroshell will undergo. In addition, initial results of the testing will be presented outlining key findings as LOFTID moves for-ward with fabrication of the flight aeroshell.

Swanson, G. T.↗
NASA NTRSDate not supplied

Design of a Crossflow Attenuated Natural Laminar Flow Flight Test Article

This abstract includes preliminary information on the computational design and analysis of a flight test article. The flight test aims to experimentally validate the new Crossflow Attenuated Natural Laminar Flow (CATNLF) design method in a flight environment. The CATNLF design method uses geometry shaping to produce specific pressure distributions that enable laminar flow on vehicle components with high sweep and high Reynolds numbers by attenuating the crossflow growth that typically leads to premature transition on such components. The flight test article design is scheduled to be completed at the end of 2019, with model fabrication beginning in early 2020.Design results presented in this abstract are representative of the final test article. The final paper will be updated to include the finalized test article geometry and analysis.

Michelle N. Lynde↗
NASA NTRSDate not supplied

Parametric Studies of Human Mars Entry, Descent, and Landing Systems

This paper will present a parametric analysis for entry, descent, and landing (EDL) concepts, enabling rapid systems assessment and tradespace exploration. The entry system uses a hypersonic inflatable aerodynamic decelerator (HIAD) technology. The baseline system includes elements for Mars aerocapture (AC) and EDL segments of the mission. The mission concept of operations (ConOps) begins at Mars arrival in a polar inclination. After performing an aerocapture (AC) maneuver into a pre-defined Mars parking orbit, the AC HIAD is jettisoned. The rest of thevehicle stays in the parking orbit for up to one year. The EDL sequence starts with a deorbit burn at the apoapsis of the parking orbit. After hypersonic entry with the EDL HIAD, the entry system uses a supersonic retropropulsion maneuver to slow the vehicle for the descent and landing segments of the mission. The vehicle will maintain a constant velocity of 2.5 m/s for 5 seconds prior to landing.The system includes a Mars Ascent Vehicle (MAV), Mars Descent Module (MDM), and two HIADs. The MDM includes a primary structure, tanks, engines, and radiators. The primary structure is an aluminum-lithium (Al-Li)cruciform design similar to the structural design of the Apollo Lunar Module. The cruciform planform layout results in four outer bays, with adequate volume in the corners between outer bays to package four landing gears. The central bay is reserved for packaging the MAV and the recessed MAV engines. Two of the outer bays accommodate main propellant tanks, with one LOX and one CH4 tank in each bay. The two remaining outer bays each house four rocket engine systems and associated support structure. Each HIAD comprises an inflatable structure, flexible thermal protection system, gas, and gas generators. The HIAD design used in this study is a stacked-toroid concept with pairing loop straps and radial/chevron straps. The baseline system lands a 20-t payload on the Mars surface. It is assumed the vehicle arrives at 6.2 km/s relative velocity at 90° inclination and is captured to a 1-Sol parking orbit.The baseline design includes many assumptions such as margins, arrival state, ConOps options, parking orbit, physical dimensions, propellant options, and technology concepts. The impact of these parameters are quantified through systems-level sensitivity analyses, which capture the global impact—not at a component level—but at the systems level. The systems-level sensitivities expose major design drivers and importance of each assumption for a design.Through tradespace exploration, a wide range of systems parameters are examined and compared for several feasible design options. Studies have been completed for the following input parameters: payload mass, propellant options, AC/EDL ballistic coefficient, lander thrust to weight ratio (T/W) (surrogate for the maximum EDL g’s),engine specific impulse (Isp), parking orbit, and inclination.The final paper will present and discuss the parametric approach used in the study. It will also include the results of recent systems analyses, sensitivity analyses, and tradespace exploration

Jamshid Samareh↗
NASA NTRS2017

A Framework for Extending the Science Traceability Matrix: Application to the Planned Europa Mission

One of the most critical functions of the systems engineering requirements process for a large multi-instrument science-driven space mission is to successfully communicate customer expectations into a comprehensive and traceable science requirements flowdown. These requirements are essential to communicating the constraints on the scope of the science investigations and clarifying how multiple instruments contribute to a given science goal. They also provide insight into how the science goals of the whole mission are affected by design choices. There is little specific guidance available on best practices for developing this science-driven flowdown. A unified Science Traceability Matrix (USTM) contains a significant amount of information that can be leveraged for that purpose, but the USTM was not designed to directly produce a complete science requirements flowdown. Thus, starting with the principles codified in a USTM, the authors propose a framework that directly maps into the requirements flowdown and supports broader systems engineering processes while retaining its meaning to the science team. This Science Traceability and Alignment Framework, or STAF, defines a set of common definitions and valid relationships to structure communication across the project. In addition, STAF populates a network of information that can be useful to support complex mission analysis activities such as fault protection. This work discusses the highest-level implementation of the STAF, the project-domain or P-STAF, which describes an approach to decomposing customer requirements into science requirements. The planned Europa Mission is used as a case study for the implementation of this framework and its potential benefits to a project.

Susca, Sara↗
NASA NTRS2024

Crew Health and Performance Integrated Data Architecture (CHP-IDA) TechPort May 2024

Future exploration missions to Mars will have increased need for crew autonomy. Crew Health & Performance (CHP) related data on the ISS is currently, manually downlinked and in disparate locations, which limits crew autonomy for future missions. The CHP-IDA project is developing a backend data system platform that grants the ability to seamlessly collect, store, process, and display CHP-related data for exploration missions. This platform allows for integration of data and advanced analytics that offer crew and ground teams better insight into the crew’s health and performance. It also enables applications that can improve the crew’s ability to provide more autonomous medical care during exploration missions. Data will be collected automatically to reduce crew and ground team time and effort and will synchronize across all in-mission vehicles, habitats, and ground as communication delay permits. The Human Research Program’s (HRP) Medical Data Architecture (MDA) project focused on this backend data architecture but for medical data only. The CHP-IDA project, a joint effort between HRP’s Exploration Medical Capability (ExMC) element and the Exploration Medical Integrated Product Team (XMIPT), expands this capability to all relevant CHP-related data. The additional inputs from nutrition, environment, exercise, radiation, and any other relevant sources will give more insight into crew’s health and performance. Currently, the Human Systems Engineering and Integration Division at Johnson Space Center (JSC) is designing the system. The team completed a system requirements review (SRR) in FY22 and now the focus is on core software development, testbed buildup, and use case scenario demonstration. An end-to-end demonstration with multiple data sources across CHP domains is schedule for the end of FY24 where all three focus areas will be displayed. Following this ground demo, the software will be completed, tested, and validated for flight.

Courtney M Schkurko↗
DOE OSTI2018

Toward Super Hot EGS: The Newberry Deep Drilling Project

Newberry Volcano in Central Oregon is an extensively studied volcano that contains one of the largest geothermal heat reservoirs in the western United States. The detailed characterization of this continental volcanic system reveals it is an excellent choice for drilling a well that will reach temperatures greater than 450°C at relatively shallow depths (< 5000 m). The main purpose of the Newberry Deep Drilling Project (NDDP) is to test the feasibility of super-hot EGS where super critical fluid can be produced with a higher energy compared to conventional EGS. NDDP will be located at an idle geothermal exploration well, NWG 46-16, drilled in 2008 on the western flank of the volcano. The project has several main goals: test EGS above the critical point of water; collect samples of rocks within the brittle-ductile transition zone; investigate volcanic hazards; study geomechanics in plastic rock and test technology for drilling, well completion, and geophysical monitoring. The well NWG 46-16, now 3500 m deep and 340-374°C at bottom, will be deepened another 1000 to 1300 m to reach 500°C into the supercritical region, and potentially approaching the brittle-ductile transition or even zones of partial melt. The original well was drilled with lost circulation zones only at very shallow depth and the temperature profile indicates conductive heat flow. Compared to other super-hot geothermal projects worldwide, this well would return more materials (cuttings, core and fluids) with more predictable drilling conditions, thus providing a suite of data near and across the brittle-ductile transition in silica-rich rocks. The well will be completed with casing and cement designed and tested to withstand the abuses of thermal cycling, hydraulic and thermal stimulation, and flow of supercritical fluids. Geothermal, volcanic, geophysical, and engineering information gained will be widely applicable to other magmatically active areas throughout the Pacific Rim and beyond.

EGS, supercritical, Newberry Volcano, brittle-duct↗
DOE OSTI2015

The Roles and Developments needed for Diagnostics in the ITER Fusion Device

Harnessing the power from Fusion on earth is an important and challenging task. Excellent work has been carried out in this area over the years with several demonstrations of the ability to produce power. Now, a new large device is being constructed in the south of France. This is called ITER. ITER is a large-scale scientific experiment that aims to demonstrate a possibility to produce commercial energy from fusion. This project is now well underway with the many teams working on the construction and completing various aspects of the design. This device will carry up to 15 MA of plasma current and produce about 500 MW of power, 400 MW approximately in high energy neutrons. The typical temperatures of the electrons inside this device are in the region of a few hundred million Kelvin. It is maintained using a magnetic field. This device is pushing several boundaries from those currently existing. As a result of this, several technologies need to be developed or extended. This is especially true for the systems or diagnostics that measure the performance and provide the control signals for this device. A diagnostic set will be installed on the ITER machine to provide the measurements necessary to control, evaluate and optimize plasma performance in ITER and to further the understanding of plasma physics. These include amongst others, measurements of the plasma shape, temperature, density, impurity concentration, and particle and energy confinement times. The system will comprise about 45 individual measuring systems drawn from the full range of modern plasma diagnostic techniques, including magnetics, lasers, X-rays, neutron cameras, impurity monitors, particle spectrometers, radiation bolometers, pressure and gas analysis, and optical fibres. These devices will have to be made to work in the new and challenging environment inside the vacuum vessel. These systems will have to cope with a range of phenomena that extend the current knowledge in the Fusion field. One amongst them is the parasitic effect of the neutrons on the while all the performing with great accuracy and precision. The levels of neutral particle flux, neutron flux and neutron fluence will be respectively about 5, 10 and 10,000 times higher than the harshest experienced in today's machines. The pulse length of the fusion reaction-or the amount of time the reaction is sustained-will be about 100 times longer. (authors)

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2017

Mobile Manipulation and Survey System for H-Canyon and Other Applications across the DOE Complex - 17309

The Nuclear and Applied Robotics Group (NRG) at the University of Texas at Austin is leading a team of university, industry, and national lab partners to develop and deploy a mobile manipulation and survey system for the H-Canyon Air Exhaust (CAEX) tunnels. Since the 1950's, these tunnels have connected Savannah River's nuclear chemical separations facilities to a terminus of sand filters. The tunnel must be periodically inspected. The conditions are harsh: 30+ mph air flow, acid vapors, alpha contamination, high beta and gamma dose, uneven floor surfaces, small entry port, obstacle debris, 'muddy' paths, standing water, and overhead obstacles. Since 2003, 5 crawlers have been deployed to inspect the tunnel with sufficient but limited success. Thus, H-Canyon provides an opportunity to develop and deploy a more robust system adhering to the notion of Multi-user / Multi-use (Mu2) in which a system is developed to complete a particular mission, but designed to maximize its extended use (multiple missions, locations, operators, etc.). Previous deployments provide a set of experiences upon which to learn and build. The environment is challenging and representative of other envisioned scenarios across the national nuclear complex. This paper reviews the history of system deployment into H-Canyon, the lessons learned from these experiences and then derives the requirements that will drive a 3 year effort to develop and deploy a system for H-Canyon inspection and other missions. The paper then concludes with a summary of technologies that enable a path to a functional prototype based on the current conceptual solution. This examination of available technologies and remaining technological gaps can assist the client in assessing the risk associated with proposed development and the range of application possible with a delivered functional prototype. (authors)

61 RADIATION PROTECTION AND DOSIMETRY↗
DOE OSTI2019

Panel Session 51: Idaho Transuranic Waste Challenges, Solutions and Implications for the Future (3/5)

This panel focused on the retrieval, characterization, treatment, certification, and shipping of transuranic (TRU) waste at the Idaho National Laboratory (INL) Site, Idaho, USA. The INL began receiving TRU waste from offsite generators (primarily the Rocky Flats Plant in Colorado, USA) beginning in 1954. Until 1970, the INL Site disposed of barrels, boxes, and other debris in a shallow, unlined landfill. Beginning in 1970, the INL Site began storing TRU waste on an asphalt pad, which was then covered with several feet of soil. This practice continued until the late 1980's at which time a large air support building was erected over the waste. In the mid-to-late 1990's, the air support building was removed and a massive building was constructed over the entire dirt mound. Contractors retrieved the waste from the early 2000's through February 2017 to support an Idaho Settlement Agreement milestone that required the retrieval of 65,000 cubic meters of TRU waste and removal from Idaho. This panel focused on the Idaho Transuranic Waste Challenges, Solutions and Implications for the Future. The Idaho Transuranic Waste Program includes buried and stored waste retrieval and processing of contact- and remote-handled transuranic waste. Over the duration of the program, the Idaho site has conducted targeted retrieval of buried waste from the 1950's and 1960's; designed, permitted, built, operated, and completed the mission of a facility to process 65,000 cubic meters of waste; and shipped more than 57,000 cubic meters of waste to WIPP. Presentation proposed: Transuranic Waste Challenges and Solutions (Hoss Brown, Fluor Idaho, LLC (USA), John McCoy, Fluor Idaho, LLC (USA), James Malmo, US DOE (USA), Doug Pruitt, Department of Energy Idaho Field Office (USA), Kenneth Princen, US DOE (USA))

12 MANAGEMENT OF RADIOACTIVE AND NON-RADIOACTIVE W↗
DOE OSTI2024

MICROREACTOR APPLICATIONS, RESEARCH, VALIDATION, AND EVALUATION (MARVEL) REACTOR ? STATUS, CONSTRUCTION, AND TESTING

The paper presents the current status of the Microreactor Applications, Research, Validation, and Evaluation (MARVEL) microreactor design, qualification testing, fabrication, and high-level construction schedule. An overview of initial criticality, low power physics testing, and start-up testing is included, as well as an overview of the envisioned processes in which end-users can engage the project for access to operational data or specific demonstrations. Designed by the Idaho National Laboratory (INL) under the auspices of the US Department of Energy’s Microreactor Program for construction and operation at the INL, MARVEL is a small, fully functional advanced reactor with UZrH fuel and thermal output of 85 kW. It offers a unique opportunity for scaled demonstrations that can dramatically accelerate the design, licensing, and deployment of commercial microreactors for power production or process heat applications. MARVEL’s objective is to build a small liquid-metal thermal reactor at the INL to demonstrate design and operating processes for microreactors, microgrid integration, and process heat applications. MARVEL finished 90%-final-design in September 2023 and completed an independent project assessment in early 2024. Fabrication of long-lead components and fuel, safety analysis review, and procurement for construction are underway. MARVEL assembly and construction will start in 2025 and fuel loading is expected in mid- 2027. Initial criticality will be performed in a dry condition in late 2027, followed by loading of NaK coolant and start-up testing. Approximately six months later, release for unrestricted operations will enable subsequent testing of microreactor characteristics, microgrid integration and select heat extraction applications.

22 GENERAL STUDIES OF NUCLEAR REACTORS↗
DOE OSTI2014

Development and Demonstration of an OWC Power System

The objectives of this Department of Energy (DOE) effort were to finalize the engineering design of a turbine and diffuser assembly, complete the scaled mechanical testing of the new blade articulation control mechanism and other critical components, to finalize the detailed design of a nominal 350 kWe turbine that will be used in an Oscillating Water Column (OWC), Wave Energy Converter System (WEC), and to assist Oceanlinx Limited in the installation and ocean water testing of the complete system.

16 TIDAL AND WAVE POWER↗
NASA NTRS1976

ADP correspondence system: Unsolicited proposal evaluation tracking application

A complete description of a correspondence control system, designed to be used by non-ADP clerical personnel is provided. In addition to operating instructions, sufficient design and conceptual information is provided to allow use or adaption of the system in related applications. The complete COBOL program and documentation are available.

Greene, W. A.↗
NASA NTRS1977

A closed life-support system for space colonies

In 1975, a system design study was performed to examine a completely self-contained system for a permanent colony of 10,000 inhabitants in space. Fundamental to this design was the life support system. Since resupply from earth is prohibitive in transportation costs, it was decided to use a closed system with the initial supply of oxygen coming from processing of lunar ores, and the supply of carbon, nitrogen and hydrogen from earth. The problem of life support was treated starting with the nutritional and metabolic requirements for the human population, creating a food and water chain sufficient to supply these demands, adding the additional requirements for the animal and plant sources in the food chain, feeding back useful waste products, supplying water as required from different sources, and closing the loop by processing organic wastes into CO2. This concept places the burden of the system upon plants for O2 generation and waste processing the CO2 generation.

Johnson, R. D.↗
NASA NTRS1979

Design, fabrication and test of graphite/polyimide composite joints and attachments for advanced aerospace vehicles

The design and evaluation of built-up attachments and bonded joint concepts for use at elevated temperatures is documented. Joint concept screening, verification of GR/PI material, fabrication of design allowables panels, definition of test matrices, and analysis of bonded and bolted joints are among the tasks completed. The results provide data for the design and fabrication of lightly loaded components for advanced space transportation systems and high speed aircraft.

Koumal, D. E.↗
NASA NTRS1989

Thermal design of the Galileo bus and Retro Propulsion Module

The Galileo spacecraft (S/C) consists of an Orbiter and Probe which have instruments to investigate the chemical composition and physical state of Jupiter's atmosphere, the Jovian satellites and the structure and physical dynamics of the Jovian magnetosphere. Galileo was at the Kennedy Space Center (KSC) preparing for a May 1986 launch at the time of the Challenger accident. The delay and an incraease in mission time has decreased the Radioisotope Thermoelectric Generator power output significantly. A change to the Inertial Upper Stage from the more powerful Centaur G-Prime has resulted in a trajectory that requires gravity assists once by Venus and twice by earth. The resulting peak solar intensity of this roundabout trajectory is more than twice the previous design value for the direct trajectory. Galileo was returned to the Jet Propulsion Laboratory (JPL) from KSC in February 1987 to begin the rework of the S/C thermal design. Verification of the thermal redesign was completed in the JPL 25' space simulator in August and November of 1988. This paper summarizes the thermal design and redesign of the Bus and Retro Propulsion Model.

Avila, A.↗