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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 289 records · Page 16
All sourcesNASA NTRSDOE OSTI
NASA NTRS2018

Computer Programming Resources 2018

The document is a compilation of Computer Programming resources. It is geared toward front-end and back-end web development. It specializes on an ongoing project to create a website for the Safety and Mission Assurance Directorate. The Quality Assurance System (QAS) is intended to improve the overall quality and efficiency of communication among NASA Quality Assurance Engineers and Contractors. The use of QAS software will be limited to NASA Kennedy Space Center and Contractors. It is accessible through the KSC network.

Confluence↗
NASA NTRS2020

Gateway Lunar Habitat Modules as the Basis for a Modular Mars Transit Habitat

This paper provides a summary of the results from a recent concept study of various configurations for a Mars Transit Habitat. The designs considered are composed of modules based on published contractor concepts proposed for the lunar Gateway through NASA’s NextSTEP program. Using these Gateway concepts as a starting point for the design of a Mars Transit Habitat has potential advantages. Both Gateway and Mars Transit Habitats will have similar requirements for long-term operations in deep space, autonomous and remote operations when the crew is not onboard, and similar requirements for transferring crew to and from a planetary surface—the Moon and Mars respectively. The contractor designs for Gateway were traded against a monolithic transit habitat previously proposed by NASA’s Mars Integration Group. In addition, these concepts were considered for a “shakedown” mission for the transit habitat hardware in cislunar space to build confidence in new systems, including the advanced environmental control and life support systems needed for Mars missions. The results presented include overall vehicle configurations, mass, and volume estimates for the selected design concepts. Two concepts using large expandable modules are identified as leading candidates for a Mars Transit Habitat and the remaining elements are identified as representative of the habitable pressure vessels needed for safe haven configurations, logistics modules, surface habitats, rovers, and descent and ascent crew cabins in the overall Mars Architecture.

Smitherman, David↗
NASA NTRSDate not supplied

NASA's Space Launch System Begins Moving To The Launch Site

NASA is accelerating plans for a human return to the Moon. NASA was directed by the White House in 2019 to land the first woman and next man on the Moon by 2024. NASA’s backbone for future deep space exploration is the Space Launch System (SLS), as well as the Orion crew spacecraft, Gateway outpost, and Human Landing System as part of the Artemis program. While the SLS upper stage, the Interim Cryogenic Propulsion Stage (ICPS), based on an existing commercial stage was shipped to Kennedy Space Center (KSC) in 2017, major completed components of SLS will soon begin their eastward journey that will see them at KSC in 2020 to be integrated for their history-making launch back to the Moon. Core Stage prime contractor Boeing completed the Artemis I core stage in 2019 at NASA’s Michoud Assembly Facility (MAF) and shipped it to NASA Stennis Space Center (SSC) for stage green run testing in 2020 and then to KSC. Northrop Grumman, prime contractor for the 5-segment solid rocket boosters, is scheduled to begin overland shipment of the Artemis I motor segments from Utah to KSC in 2020 to await integration. This paper will discuss SLS progress to date and planned 2020 milestones.

Bruce R Askins↗
NASA NTRS2021

Orion Meteoroid and Debris Analysis with a Single Kevlar® Layer Enhancement to the Propulsion Tank Multi-Layer Insulation: Comparison of the Observed Data and the Adjusted Ballistic Models

In a continual mass optimization effort for the Orion vehicle by NASA and its prime contractor Lockheed Martin Space, along with the European Space Agency (ESA) and its contractors Airbus and Thales Alenia Space-Italy (TAS-I), a series of shield characterization shots have been performed to quantify the ballistic enhancement of a single-layer of Kevlar® in multi-layer insulation (MLI). This enhanced MLI is part of Orion’s propulsion subsystem, and it is planned to replace a double-layer Kevlar® configuration starting at the Artemis IV mission. This effort has included fifty-two shield characterization shots for five different shield configurations over the four Orion propellant storage vessels. These storage vessels are located in the European Service Module (ESM). This shield characterization has been managed by the Hypervelocity Impact Technology (HVIT) group in NASA Astromaterials Research and Exploration Sciences at Johnson Space Center (JSC) for the NASA Engineering and Safety Center (NESC) and the Multi-Purpose Crew Vehicle (MPCV) program office in coordination with Lockheed Martin Space and Thales Alenia Space-Italy (TAS-I). The shield characterization has used the two-stage, light-gas-gun at the Remote Hypervelocity Test Laboratory (RHTL) of NASA JSC White Sands Test Facility (WSTF) for acceleration of projectiles to representative orbital impact speeds. From this shield characterization effort, a revised ballistic limiting equation (BLE) has been developed for each of the five representative shielding configurations of the ESM pressure vessels. This document provides a brief description of the shield configurations considered for the Orion program and the shield characterization findings. These results are compared to the assumed BLE for each configuration going into the Artemis missions that utilize this version of ballistic enhanced MLI. The models are integrated into a fourteen day High Lunar Orbit (HLO) mission as a representative reliability prediction impact for Orion, and it has been found that the predicted risk of a loss-of-crew (LOC) event is actually a little less than half of the assumed value that launched this design modification opportunity.

Joshua E Miller↗
NASA NTRSDate not supplied

Investigation into High Power Converter Topologies

The NESC commissioned NASA Glenn Research Center (GRC) to perform a study of high-power DC-DC converter topologies Why perform the study? • Several past contractor-led converter development programs have been plagued with development delays and cost overruns due to: • Poor initial design decisions • Complex requirements driving designs • Better inform government engineers about strengths and weaknesses of various topologies, learn about new topologies/design strategies. • Allow NASA to be better prepared for upcoming high power/high voltage power conversion systems work, such as Lunar and Martian surface missions, high power electric propulsion, as well as terrestrial systems, such as electrified aircraft. • Contractors often do not have the option to restart poor decisions – allows NASA to be better informed at the start of programs.

Power Converter↗
NASA NTRS2023

The Trash Compaction Processing System (TCPS) Technology Demonstrations Science Objectives and Requirement Definitions

Throughout the Next STEP Phase A and Phase B, the Trash Compaction Processing System (TCPS) is being developed for a technology demonstration (TD) on the International Space Station (ISS) in 2025. For Phase A, two contractors built proof-of-concept hardware. One contractor was chosen to build the TD hardware for Phase B. Both Phase A lessons learned and risk reduction activities at Ames Research Center (ARC) were used to write the TD science objectives, scope, and requirements. The work at ARC aims to retire technical risks and provide design data to TCPS developers and the ISS system integrators. This paper will summarize the lessons learned from the proof-of-concept hardware, the risk reduction activities, and how these lessons learned form the basis of the TD requirement matrix.

TCPS↗
NASA NTRS2022

Atmospheric Research 2020 Technical Highlights

Welcome to the 2020 Atmospheres Highlights report. Here we summarize research and scientific communication/outreach accomplishments from the portion of atmospheric science activities at NASA’s Goddard Space Flight Center (GSFC) that comprises the Earth Science Division’s Atmospheres organization. As in previous years, this report is intended for a broad audience, including colleagues within NASA, scientists outside the Agency, science graduate students, and members of the public. Organizationally, the report covers research activities under the Office of Deputy Organizationally, the report covers research activities under the Office of Deputy Director for Atmospheres (610AT), which is within Earth Sciences Division (Code Director for Atmospheres (610AT), which is within Earth Sciences Division (Code 610) in the Sciences and Exploration Directorate (600). Laboratories and office within 610) in the Sciences and Exploration Directorate (600). Laboratories and office within 610AT include: Mesoscale Atmospheric Processes Laboratory (612), Climate and 610AT include: Mesoscale Atmospheric Processes Laboratory (612), Climate and Radiation Laboratory (613), Atmospheric Chemistry and Dynamics Laboratory (614), Radiation Laboratory (613), Atmospheric Chemistry and Dynamics Laboratory (614), and the Wallops Field Support Office (610.W). As of this writing, the 277 personnel and the Wallops Field Support Office (610.W). As of this writing, the 277 personnel in Code 610AT consist of 53 civil servants and 224 cooperative agreement associates, in Code 610AT consist of 53 civil servants and 224 cooperative agreement associates, postdoctoral fellows and contractors, postdoctoral fellows and contractors.

Annual Report↗
NASA NTRS1967

Ultek trip report

Experiences in checking production of ultrahigh vacuum systems at contractor establishment

CONTRACTOR↗
NASA NTRS1954

NACA Conference on Helicopters a Compilation of the Papers Presented at Langley Aeronautical Laboratory, Langley Field, Va., May 12 and 13, 1954

This document contains reproductions of technical papers presented at the NACA Conference on Helicopters held at the Langley Aeronautical Laboratory May 12 and 13, 1954. The primary purpose of this conference was to convey to the military services, their contractors, and others concerned with the design of helicopters the results of NACA research on helicopters and to provide those attending an opportunity to discuss the results. The papers in this document are in the same form in which they were presented at the conference in order to facilitate their prompt distribution. The original presentation and this record are considered as complementary to, rather than as substitutes for, the Committee's more complete and formal reports . A list of the conferees is included.

Drag↗
NASA NTRS1962

Studies in the Fields of Space Flight and Guidance Theory: Progress Report - No. 2

Compiled in this paper are 11 progress papers from 7 of the agencies working under contract to MSFC in the areas of guidance theory and space flight theory. This is the second paper of the "Progress Reports" and covers the period from December 1, 1961 to June 15, 1962. Extensive references are made to "Progress Report No. 1." This second progress report is referred to as "report" and "Progress Report No. 1" will be referred to as the "first report" in this introduction. Information given in the first report is not repeated herein. The reports of the various contractors will be referred to by index number as papers. There are two parallel series of publications covering the over-all activities at MSFC in the areas of guidance theory and space flight theory. One is the series of progress reports of which this paper is the second in the series. The other is the series of "Status Reports on Theory of Space Flight and Adaptive Guidance." These series along with a few other special reports, give a complete picture of the immediate objectives, accomplishments, and final goals of Aeroballistics Division and associated contr

FLIGHT OPTIMIZATION↗