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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 163 records · Page 9
All sourcesNASA NTRSDOE OSTI
NASA NTRS2014

On-Orbit Measurement of Next Generation Space Solar Cell Technology on the International Space Station

On-orbit measurements of new photovoltaic (PV) technologies for space power are an essential step in the development and qualification of advanced solar cells. NASA Glenn Research Center will fly and measure several solar cells attached to NASA Goddards Robotic Refueling Mission (RRM), expected to be launched in 2014. Industry and government partners have provided advanced PV devices for evaluation of performance and environmental durability. The experiment is completely self-contained, providing its own power and internal data storage. Several new cell technologies including Inverted Metamorphic Multi-junction and four-junction cells will be tested.

robotic refueling mission↗
NASA NTRS2023

Assessment of Coated Particle Fuels for Space Nuclear Power and Propulsion Systems: A Report for the NESC Nuclear Power & Propulsion Technical Discipline Team

This study evaluates terrestrial reactor fuel forms, with an emphasis on the coated particle fuel capability under development by interagency reactor programs, for application to space reactor systems of interest to NASA. A comprehensive review of coated particle fuel readiness and qualification status has been performed. Possible derivative fuel forms based on coated particle fuel manufacture technologies are identified and assessed for fission surface power, nuclear electric propulsion, and nuclear thermal propulsion systems. Assessments for terrestrial coated particle and historic fuels were compared for each system allowing for relative risk and common fuel qualification needs to be identified.

Fission Surface Power↗
DOE OSTI2024

Advanced Manufacturing Techniques and Compositions of High Entropy Alloys for Nuclear Applications

In line with the objectives of the Department of Energy, Office of Nuclear Energy, Advanced Materials and Manufacturing Technologies (AMMT) program, this work focuses on new materials development and qualification research and development for next-generation, high-temperature nuclear reactors. High entropy alloys (HEAs) have the potential to serve in these extreme environments of next-generation nuclear reactors because of their unique phase transformation pathways and nanoscale and mesoscale microstructures. The current work focuses on understanding such nuclear-energy-relevant HEAs through a detailed literature survey, selected experimental work, and developing a decision matrix with criteria for the identification of HEAs that may have the most impact and value for further examination.

36 MATERIALS SCIENCE↗
NASA NTRS1982

The OSTA-1 scientific payload - Scientific results from the second flight of the Shuttle

The qualification, operation, and results from the first Office of Science and Technology Assessment payload, flown on board the second Shuttle mission, are detailed. Among the experiments were a Shuttle Imaging Radar-A, which recorded 1000 m of 70 mm film of 50 km swaths of the earth's land and ocean surface. The multispectral IR radiometer permitted the acquisistion of 400,000 ten-channel spectral over the wavelength interval 0.5-2.35 microns, including rock and soil identifications which are correlated with economically significant geologic materials. The ocean color experiment involved an eight channel optical mechanical scanner to detect ocean water color changes due to the presence of phytoplankton. Air pollution was measured by radiometer in the 4.50-4.83 micron regions, and an asymmetry in CO concentration was found between the northern and sourthern hemispheres. Only five seconds of surface and meteorological data were collected by the FILE package, while the one successfully used film cassette on a lightning recording experiment revealed discharges among convective storm systems. A rerunning of unsuccessful experiments and new instrumentation for future Shuttle missions are indicated.

Taranik, J. V.↗
NASA NTRS2018

Space Qualified 200-Watt Q-band Linearized Traveling-Wave Tube Amplifier

L3 Technologies Electron Devices Division, (L3 EDD) and L3 Technologies Narda Microwave West (L3 NMW), are completing space-flight qualification for a 200-watt Q-band linearized channelized traveling-wave tube amplifier (LCTWTA) capable of over 5 GHz instantaneous bandwidth in a conduction-cooled package. This paper will discuss the LCTWTA performance, manufacturing and flight qualification test results.

Traveling-Wave Tube Amplifier↗
NASA NTRS2018

Space Qualified 200-Watt Q-Band Linearized Traveling-Wave Tube Amplifier

L3 Technologies Electron Devices Division, (L3 EDD) and L3 Technologies Narda Microwave West (L3 NMW), are completing space-flight qualification for a 200-watt Q-band linearized channelized traveling-wave tube amplifier (LCTWTA) capable of over 5 GHz instantaneous bandwidth in a conduction-cooled package. This paper will discuss the LCTWTA performance, manufacturing and flight qualification test results.

Q-band↗
NASA NTRS2010

Reliability and Qualification of Hardware to Enhance the Mission Assurance of JPL/NASA Projects

Packaging Qualification and Verification (PQV) and life testing of advanced electronic packaging, mechanical assemblies (motors/actuators), and interconnect technologies (flip-chip), platinum temperature thermometer attachment processes, and various other types of hardware for Mars Exploration Rover (MER)/Mars Science Laboratory (MSL), and JUNO flight projects was performed to enhance the mission assurance. The qualification of hardware under extreme cold to hot temperatures was performed with reference to various project requirements. The flight like packages, assemblies, test coupons, and subassemblies were selected for the study to survive three times the total number of expected temperature cycles resulting from all environmental and operational exposures occurring over the life of the flight hardware including all relevant manufacturing, ground operations, and mission phases. Qualification/life testing was performed by subjecting flight-like qualification hardware to the environmental temperature extremes and assessing any structural failures, mechanical failures or degradation in electrical performance due to either overstress or thermal cycle fatigue. Experimental flight qualification test results will be described in this presentation.

PRTs↗
NASA NTRS2007

Throttling Impacts on Hall Thruster Performance, Erosion, and Qualification for NASA Science Missions

With the SMART-1, Department of Defense, and commercial industry successes in Hall thruster technologies, NASA has started considering Hall thrusters for science missions. The recent Discovery proposals included a Hall thruster science mission and the In-Space Propulsion Project is investing in Hall thruster technologies. As the confidence in Hall thrusters improve, ambitious multi-thruster missions are being considered. Science missions often require large throttling ranges due to the 1/r(sup 2) power drop-off from the sun. Deep throttling of Hall thrusters will impact the overall system performance. Also, Hall thrusters can be throttled with both current and voltage, impacting erosion rates and performance. Last, electric propulsion thruster lifetime qualification has previously been conducted with long duration full power tests. Full power tests may not be appropriate for NASA science missions, and a combination of lifetime testing at various power levels with sufficient analysis is recommended. Analyses of various science missions and throttling schemes using the Aerojet BPT-4000 and NASA 103M HiVHAC thruster are presented.

Dankanich, John W.↗
NASA NTRS1988

Pyrotechnic system failures: Causes and prevention

Although pyrotechnics have successfully accomplished many critical mechanical spacecraft functions, such as ignition, severance, jettisoning and valving (excluding propulsion), failures continue to occur. Provided is a listing of 84 failures of pyrotechnic hardware with completed design over a 23-year period, compiled informally by experts from every NASA Center, as well as the Air Force Space Division and the Naval Surface Warfare Center. Analyses are presented as to when and where these failures occurred, their technical source or cause, followed by the reasons why and how these kinds of failures persist. The major contributor is a fundamental lack of understanding of the functional mechanisms of pyrotechnic devices and systems, followed by not recognizing pyrotechnics as an engineering technology, insufficient manpower with hands-on experience, too few test facilities, and inadequate guidelines and specifications for design, development, qualification and acceptance. Recommendations are made on both a managerial and technical basis to prevent failures, increase reliability, improve existing and future designs, and develop the technology to meet future requirements.

Bement, Laurence J.↗
NASA NTRS2009

The Integrated Hazard Analysis Integrator

Hazard analysis addresses hazards that arise in the design, development, manufacturing, construction, facilities, transportation, operations and disposal activities associated with hardware, software, maintenance, operations and environments. An integrated hazard is an event or condition that is caused by or controlled by multiple systems, elements, or subsystems. Integrated hazard analysis (IHA) is especially daunting and ambitious for large, complex systems such as NASA s Constellation program which incorporates program, systems and element components that impact others (International Space Station, public, International Partners, etc.). An appropriate IHA should identify all hazards, causes, controls and verifications used to mitigate the risk of catastrophic loss of crew, vehicle and/or mission. Unfortunately, in the current age of increased technology dependence, there is the tendency to sometimes overlook the necessary and sufficient qualifications of the integrator, that is, the person/team that identifies the parts, analyzes the architectural structure, aligns the analysis with the program plan and then communicates/coordinates with large and small components, each contributing necessary hardware, software and/or information to prevent catastrophic loss. As viewed from both Challenger and Columbia accidents, lack of appropriate communication, management errors and lack of resources dedicated to safety were cited as major contributors to these fatalities. From the accident reports, it would appear that the organizational impact of managers, integrators and safety personnel contributes more significantly to mission success and mission failure than purely technological components. If this is so, then organizations who sincerely desire mission success must put as much effort in selecting managers and integrators as they do when designing the hardware, writing the software code and analyzing competitive proposals. This paper will discuss the necessary and sufficient requirements of one of the significant contributors to mission success, the IHA integrator. Discussions will be provided to describe both the mindset required as well as deleterious assumptions/behaviors to avoid when integrating within a large scale system.

Morris, A. Terry↗
DOE OSTI2024

Updated ASME design correlations and qualification plan for powder bed fusion 316H stainless steel

This report provides an update on the Advanced Materials and Manufacturing Technologies (AMMT) program effort to qualify Laser-Powder Bed Fusion (L-PBF) 316H stainless steel for use with the ASME Boiler & Pressure Vessel Code Section III, Division 5 rules. The report summarizes progress in testing and characterizing L-PBF material at elevated temperatures by providing preliminary design data for L-PBF 316H and by comparing the elevated temperature performance of the L-PBF material to wrought and conventional fusion welded 316H. The report then updates the initial AMMT qualification plan for L-PBF 316H, originally developed in 2023, to update the accelerated qualification strategy adopted in that plan to account for the new high temperature test data. The report also explores a few methods for further accelerating the qualification process using machine learning techniques to supplement the more conventional, empirical analysis methods typically used by ASME to correlate and extrapolate time-dependent material test data.

36 MATERIALS SCIENCE↗
NASA NTRS2009

Advanced Development Program for a 625 lbf thrust engine for Ares First Stage Roll Control System

NASA's new Ares Launch Vehicle will require twelve thrusters to provide roll control of the vehicle during the first stage firing. All twelve roll control thrusters will be located at the inter-stage segment that separates the solid rocket booster first stage from the second stage. NASA selected a mono propellant hydrazine solution and as a result awarded Aerojet-General a contract in 2007 for an advanced development program for an MR-80- series 625 Ibf vacuum thrust monopropellant hydrazine thruster. This thruster has heritage dating back to the 1976 Viking Landers and most recently for the 2011 Mars Science Laboratory. Prior to the Ares application, the MR-80-series thrusters had been equipped with throttle valves and not typically operated in pulse mode. The primary objective of the advanced development program was to increase the technology readiness level and retire major technical risks for the future flight qualification test program. Aerojet built on their heritage MR-80 rocket engine designs to achieve the design and performance requirements. Significant improvements to cost and lead-time were achieved by applying Design for Manufacturing and Assembly (DFMA) principles. AerojetGeneral has completed Preliminary and Critical Design Reviews, followed by two successful rocket engine development test programs. The test programs included qualification random vibration and firing lite that significantly exceed the flight qualification requirements. This paper discusses the advanced development program and the demonstrated capability of the MR-80C engine. Y;

Dawson, Matt↗
NASA NTRSDate not supplied

Development, Build and Certification of the Alternate Fecal Canister (AFC) Hardware for the NASA Exploration Toilet

On longer range exploration missions, the mass and volume of critical hardware and consumables that will be needed to support crew will pose a big stowage challenge. This includes the hardware needed for the collection and storage of human metabolic waste. The amount of stowage needed for this hardware both before (empty) and after (full) use will be a significant burden on the overall spacecraft habitable volume, layout, and design. To help with this challenge, the National Aeronautics and Space Administration (NASA) has developed a collapsible canister for the collection and containment of fecal deposits. The Alternate Fecal Canister (AFC) is an alternative to the exploration toilet hard-sided fecal canister. The AFC is collapsible in its empty state which is a volume benefit to smaller vehicles on longer missions. In addition, the use of lighter-weight materials provides a reduction in mass of the overall container. This paper will provide a summary of the AFC design including final flight design and build, acceptance and qualification testing completed, final certification and delivery and forward plans for a technology demonstration with the exploration toilet on the International Space Station (ISS). In addition, a summary of issues and final resolution encountered during flight build and testing will also be provided. As part of the acceptance and certification process for AFC, the hardware was also put into several rounds of odor testing with the support of the White Sands Test Facility (WSTF). The details, planning and anomalies identified during odor testing will also be summarized in this paper. Finally, a brief overview of potential future design upgrades including changes to address any crew feedback from the ISS demonstration will be discussed.

Fecal Canister↗
NASA NTRSDate not supplied

Development, Build and Certification of the Alternate Fecal Canister (AFC) Hardware for the NASA Exploration Toilet

On longer range exploration missions, the mass and volume of critical hardware and consumables that will be needed to support crew will pose a big stowage challenge. This includes the hardware needed for the collection and storage of human metabolic waste. The amount of stowage needed for this hardware both before (empty) and after (full) use will be a significant burden on the overall spacecraft habitable volume, layout, and design. To help with this challenge, the National Aeronautics and Space Administration (NASA) has developed a collapsible canister for the collection and containment of fecal deposits. The Alternate Fecal Canister (AFC) is an alternative to the exploration toilet hard-sided fecal canister. The AFC is collapsible in its empty state which is a volume benefit to smaller vehicles on longer missions. In addition, the use of lighter-weight materials provides a reduction in mass of the overall container. This paper will provide a summary of the AFC design including final flight design and build, acceptance and qualification testing completed, final certification and delivery and forward plans for a technology demonstration with the exploration toilet on the International Space Station (ISS). In addition, a summary of issues and final resolution encountered during flight build and testing will also be provided. As part of the acceptance and certification process for AFC, the hardware was also put into several rounds of odor testing with the support of the White Sands Test Facility (WSTF). The details, planning and anomalies identified during odor testing will also be summarized in this paper. Finally, a brief overview of potential future design upgrades including changes to address any crew feedback from the ISS demonstration will be discussed.

Fecal Canister↗
NASA NTRSDate not supplied

Development, Build and Certification of the Alternate Fecal Canister (AFC) Hardware for the NASA Exploration Toilet

On longer range exploration missions, the mass and volume of critical hardware and consumables that will be needed to support crew will pose a big stowage challenge. This includes the hardware needed for the collection and storage of human metabolic waste. The amount of stowage needed for this hardware both before (empty) and after (full) use will be a significant burden on the overall spacecraft habitable volume, layout, and design. To help with this challenge, the National Aeronautics and Space Administration (NASA) has developed a collapsible canister for the collection and containment of fecal deposits. The Alternate Fecal Canister (AFC) is an alternative to the exploration toilet hard-sided fecal canister. The AFC is collapsible in its empty state which is a volume benefit to smaller vehicles on longer missions. In addition, the use of lighter-weight materials provides a reduction in mass of the overall container. This paper will provide a summary of the AFC design including final flight design and build, acceptance and qualification testing completed, final certification and delivery and forward plans for a technology demonstration with the exploration toilet on the International Space Station (ISS). In addition, a summary of issues and final resolution encountered during flight build and testing will also be provided. As part of the acceptance and certification process for AFC, the hardware was also put into several rounds of odor testing with the support of the White Sands Test Facility (WSTF). The details, planning and anomalies identified during odor testing will also be summarized in this paper. Finally, a brief overview of potential future design upgrades including changes to address any crew feedback from the ISS demonstration will be discussed.

Fecal Canister↗
NASA NTRS2008

Optical Communications from Planetary Distances

Future planetary campaigns, including human missions, will require data rates difficult to realize by microwave links. Optical channels not only provide an abundance of bandwidth, they also allow for significant size, weight, and power reduction. Moreover, optical-based tracking may enhance spacecraft navigation with respect to microwave-based tracking. With all its advantages, optical communications from deep space is not without its challenges. Due to the extreme distance between the two ends of the link, specialized technologies are needed to enable communications in the deep space environment. Although some of the relevant technologies have been developed in the last decade, they remain to be validated in an appropriate domain. The required assets include efficient pulsed laser sources, modulators, transmitters, receivers, detectors, channel encoders, precise beam pointing technologies for the flight transceiver and large apertures for the ground receiver. Clearly, space qualification is required for the systems that are installed on a deep space probe. Another challenge is atmospheric effects on the optical beam. Typical candidate locations on the ground have a cloud-free line of sight only on the order of 60-70% of the time. Furthermore, atmospheric losses and background light can be problematic even during cloud-free periods. Lastly, operational methodologies are needed for efficient and cost effective management of optical links. For more than a decade, the National Aeronautics and Space Administration (NASA) has invested in relevant technologies and procedures to enable deep space optical communications capable of providing robust links with rates in the order of 1 Gb/s from Mars distance. A recent publication indicates that potential exists for 30-dB improvement in performance through technology development with respect to the state-of-the-art in the early years of this decade. The goal is to fulfill the deep space community needs from about 2020 to the foreseeable future. It is envisioned that, at least initially, optical links will be complemented by microwave assets for added robustness, especially for human missions. However, it is expected that as optical techniques mature, laser communications may be operated without conventional radio frequency links. The purpose of this paper is to briefly review the state-of-the-art in deep space laser communications and its challenges and discuss NASA-supported technology development efforts and plans for deep space optical communications at JPL.

Laser Communications↗
NASA NTRS2007

Design, Qualification, and On Orbit Performance of the CALIPSO Aerosol Lidar Transmitter

The laser transmitter for the CALIPSO aerosol lidar mission has been operating on orbit as planned since June 2006. This document discusses the optical and laser system design and qualification process that led to this success. Space-qualifiable laser design guidelines included the use of mature laser technologies, the use of alignment sensitive resonator designs, the development and practice of stringent contamination control procedures, the operation of all optical components at appropriately derated levels, and the proper budgeting for the space-qualification of the electronics and software.

Hovis, Floyd E.↗
NASA NTRSDate not supplied

NASA’s Exploration and In-Space Services (NExIS) Division OSAM-1 Propellant Transfer Subsystem Progress through FY 2024

The National Aeronautics and Space Administration (NASA) Exploration and In-Space Services (NExIS) Division of Goddard Space Flight Center (GSFC) has been developing technology to robotically refuel both heritage and recently developed satellites on-orbit funded through NASA’s Space Technology Mission Directorate (STMD). The On-orbit Servicing, Assembly, and Manufacturing 1 (OSAM-1) mission, formerly known as Restore-L, developed a system to refuel a satellite in space and assemble a communications antenna. By demonstrating these capabilities, the mission would advance never-before tested technologies for use in future missions (by NASA, other government organizations, and private industries). The purpose of this paper is to capture the lessons learned from the hardware development of the OSAM-1 Propellant Transfer System (PTS) that are highly relevant for the ISAM community. This paper covers a review of in-space servicing extensibility and critical technologies that were being developed within NExIS, focusing on the fluid transfer refueling technology within the framework of the OSAM-1 PTS. An overview of the technology demonstration servicing mission via the OSAM-1 Space Vehicle is provided as an extension of the technology development progress reported in 2018, 2019 and 2020. The general objectives, challenges, and key technologies are presented as an introduction to the context of the OSAM-1 mission, and a precursor to the OSAM-1 PTS specific development status. Final assembly, qualification, and functional tests along with installation and acceptance testing of the Hose Management Assembly (HMA) and Propellant Transfer Assembly (PTA) are discussed. Technology development, challenges, lessons learned, along with installation and testing results are discussed, with particular focus on the OSAM-1 assemblies including the PTA and HMA. In addition, testing utilizing the integrated flight simulator test setups will be summarized. The OSAM-1 PTS made great strides in advancing in-space refueling technology; however, there are unfinished development efforts remaining. This paper concludes with a brief summary of the technology shortfalls (gaps) that remain in the key areas of in-space fluid transfer.

ISAM↗