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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 145 records · Page 8
All sourcesNASA NTRSDOE OSTI
DOE OSTI2021

Simulation Dataset - Input files

The input data that are required to run the model are divided into fundamental data and advanced data. The fundamental data are essential to run the model, while the advanced data allow optional model features to be activated. The names of all input data files are to be entered as ASCII characters in a tabular format. Spaces, commas, or tabs can separate numeric fields, the use of any other special visible or hidden characters must be avoided. It may be useful to note that all files are generally read in using standard free-format style FORTRAN READ statements. The input data files can be generated/modified using any standard editor, spreadsheet or word processor (in non-document mode), given that the above guidelines are complied with. However, the inclusion of special formatting characters and the insertion of blank lines must be avoided. The input data files may also be generated through the use of special purpose translation programs that convert the input data files that were initially generated for another traffic simulation or transportation planning model into an INTEGRATION format.

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATI↗
NASA NTRS1972

The management approach to the NASA space station definition studies at the Manned Spacecraft Center

The overall management approach to the NASA Phase B definition studies for space stations, which were initiated in September 1969 and completed in July 1972, is reviewed with particular emphasis placed on the management approach used by the Manned Spacecraft Center. The internal working organizations of the Manned Spacecraft Center and its prime contractor, North American Rockwell, are delineated along with the interfacing techniques used for the joint Government and industry study. Working interfaces with other NASA centers, industry, and Government agencies are briefly highlighted. The controlling documentation for the study (such as guidelines and constraints, bibliography, and key personnel) is reviewed. The historical background and content of the experiment program prepared for use in this Phase B study are outlined and management concepts that may be considered for future programs are proposed.

Heberlig, J. C.↗
NASA NTRS1981

The role of pilots

The need for detailed specifications is addressed. Candidates for standardization include hardware interfaces, communication protocols, and data exchange services. Atmosphere, Ocean, and Resource pilot programs, utilization of current techniques and technologies in the use and exchange of data and to facilitate access to data are discussed. Pilot objectives aim to: (1) demonstrate the use of advanced technologies, (2) provide a test bed environment for data handling technique evaluation, (3) evolve requirements and capabilities, and (4) document validated methodologies as standards and guidelines for data systems planning use. A user oriented catalog system, data set management, a network communication system, and a user interface are also discussed.

Gary, J. P.↗
NASA NTRS1991

Definition, technology readiness, and development cost of the orbit transfer vehicle engine integrated control and health monitoring system elements

An Integrated Control and Health Monitoring (ICHM) system was conceived for use on a 20 Klb thrust baseline Orbit Transfer Vehicle (OTV) engine. Considered for space used, the ICHM was defined for reusability requirements for an OTV engine service free life of 20 missions, with 100 starts and a total engine operational time of 4 hours. Functions were derived by flowing down requirements from NASA guidelines, previous OTV engine or ICHM documents, and related contracts. The elements of an ICHM were identified and listed, and these elements were described in sufficient detail to allow estimation of their technology readiness levels. These elements were assessed in terms of technology readiness level, and supporting rationale for these assessments presented. The remaining cost for development of a minimal ICHM system to technology readiness level 6 was estimated. The estimates are within an accuracy range of minus/plus 20 percent. The cost estimates cover what is needed to prepare an ICHM system for use on a focussed testbed for an expander cycle engine, excluding support to the actual test firings.

Cannon, I.↗
NASA NTRS1998

Issues in NASA Program and Project Management. Special Edition: A Collection of Papers on NASA Procedures and Guidance 7120.5A

A key aspect of NASA's new Strategic Management System is improving the way we plan, approve, execute and evaluate our programs and projects. To this end, NASA has developed the NASA Program and Project Management processes and Requirements-NASA Procedures and Guidelines (NPG) 7120.5A, which formally documents the "Provide Aerospace Products and Capabilities" crosscutting process, and defines the processes and requirements that are responsive to the Program/Project Management-NPD 7120.4A. The Program/Project Management-NPD 7120.4A, issued November 14, 1996, provides the policy for managing programs and projects in a new way that is aligned with the new NASA environment. An Agencywide team has spent thousands of hours developing the NASA Program and Project Management Processes and Requirements-NPG 7120.5A. We have created significant flexibility, authority and discretion for the program and project managers to exercise and carry out their duties, and have delegated the responsibility and the accountability for their programs and projects.

Edward J. Hoffman↗
NASA NTRS2008

Effects of Low Temperature on Charging of Spacecraft Dielectrics

Spacecraft dielectric charging, sometimes called deep-dielectric-charging or bulk-charging, occurs when high energy electrons imbed themselves in dielectric materials, and the charge density builds up, sometimes to breakdown levels. Charges usually bleed off slowly due to material conductivity. At very low (cryogenic) temperatures, the dielectric conductivity decreases until charges may remain and build up over weeks, months, or years. In those cases, the guidelines given in NASA and industry documents for when dielectric charging may become important are misleading. Arcing tests of spacecraft cables at liquid nitrogen temperatures and very low flux levels have been done at NASA MSFC for the JWST Project. In this paper, we describe the results of those tests and analyze their important implications for cryogenic spacecraft cable design and construction.

Ferguson, Dale C.↗
NASA NTRS2008

Effects of Low Temperature on Charging of Spacecraft Dielectrics

Spacecraft dielectric charging, sometimes called deep-dielectric-charging or bulk-charging, occurs when high energy electrons imbed themselves in dielectric materials, and the charge density builds up, sometimes to breakdown levels. Charges usually bleed off slowly due to material conductivity. At very low (cryogenic) temperatures, the dielectric conductivity decreases until charges may remain and build up over weeks, months, or years. In those cases, the guidelines given in NASA and industry documents for when dielectric charging may become important are misleading. Arcing tests of spacecraft cables at liquid nitrogen temperatures and very low flux levels have been done at NASA MSFC for the JWST Project. In this paper, we describe the results of those tests and analyze their important implications for cryogenic spacecraft cable design and construction.

Ferguson, Dale C.↗
NASA NTRS1983

Assessment of the NASA Flight Assurance Review Program

The NASA flight assurance review program to develop minimum standard guidelines for flight assurance reviews was assessed. Documents from NASA centers and NASA headquarters to determine current design review practices and procedures were evaluated. Six reviews were identified for the recommended minimum. The practices and procedures used at the different centers to incorporate the most effective ones into the minimum standard review guidelines were analyzed and guidelines for procedures, personnel and responsibilies, review items/data checklist, and feedback and closeout were defined. The six recommended reviews and the minimum standards guidelines developed for flight assurance reviews are presented. Observations and conclusions for further improving the NASA review and quality assurance process are outlined.

Holmes, J.↗
DOE OSTI2020

LDM-151: Data Management Science Pipelines Design

The LSST Science Requirements Document (the LSST SRD) specifies a set of data product guidelines, designed to support science goals envisioned to be enabled by the LSST observing program. Following these guidelines, the details of these data products have been described in the LSST Data Products Definition Document (DPDD), and captured in a formal flow-down from the SRD via the LSST System Requirements (LSR), Observatory System Specifications (OSS), to the Data Management System Requirements (DMSR). The LSST Data Management subsystem's responsibilities include the design, implementation, deployment and execution of software pipelines necessary to generate these data products. This document describes the design of the scientific aspects of those pipelines.

79 ASTRONOMY AND ASTROPHYSICS↗
DOE OSTI2021

Design Guidelines for Deployable Wind Turbines for Military Operational Energy Applications

This document aims to provide guidance on the design and operation of deployable wind systems that provide maximum value to missions in defense and disaster relief. Common characteristics of these missions are shorter planning and execution time horizons and a global scope of potential locations. Compared to conventional wind turbine applications, defense and disaster response applications place a premium on rapid shipping and installation, short-duration operation (days to months), and quick teardown upon mission completion. Furthermore, defense and disaster response applications are less concerned with cost of energy than conventional wind turbine applications. These factors impart design drivers that depart from the features found in conventional distributed wind turbines, thus necessitating unique design guidance. The supporting information for this guidance comes from available relevant references, technical analyses, and input from industry and military stakeholders. This document is not intended to be a comprehensive, prescriptive design specification. This document is intended to serve as a written record of an ongoing discussion of stakeholders about the best currently available design guidance for deployable wind turbines to help facilitate the effective development and acquisition of technology solutions to support mission success. The document is generally organized to provide high-level, focused guidance in the main body, with more extensive supporting details available in the referenced appendices. Section 2 begins with a brief qualitative description of the design guidelines being considered for the deployable wind turbines. Section 3 provides an overview of the characteristics of the mobile power systems commonly used in U.S. military missions. Section 4 covers current military and industry standards and specifications that are relevant to a deployable wind turbine design. Section 5 presents the deployable turbine design guidelines for the application cases.

17 WIND ENERGY↗
NASA NTRS1993

California Student Get Away Special Payload GAS-450

The California Student Get Away Special Payload GAS-450, recently went into orbit on the STS-57 Mission, Space Shuttle, Endeavour, 21 June 1993, 6:14 AM and landed on the 29 June 1993 at Kennedy Space Center (KSC). Fifty students from 13 California Central Coast Schools and one in San Francisco designed and built 13 active experiments (6 modules) for this mission. Preliminary analysis of our completely reusable payload bus system indicated that the structure, power system, microprocessor, and sensor systems in each experiment module worked flawlessly. The experiments themselves performed exceptionally well with a 60 percent success ratio. The students are thoroughly documenting their own experiments and results via a standard research paper guideline generated by the GAS-450 technical staff. Lessons learned (program management and technical) are documented at the end of the paper. If any other organization needs payload/experiment development or NASA documentation assistance, then please contact us. We can help make your idea a space tested reality. Three years of intense effort culminated on 3 February 1993, the GSFC field operations team at Kennedy Space Center performed the final pressure decay and electrical tests upon the fully integrated GAS-450 flight canister. Subsequently, the payload was integrated with its parent GAS Bridge Assembly in mid-February and the bridge was transferred to the KSC orbiter team in late February 1993. The STS-57 mission originally scheduled to launch on the 29 April 1993 slipped until 21 June 1993. Our Payload shared the cargo bay with ten other GAS Canisters, the EUREKA experiment, the SHOOT experiment, and the SPACEHAB-1 module. The SIL technical staff retrieved the GAS-450 payload after flight from the NASA Spin Test Facility at KSC and shipped it back to California on the 22 July 1993 for student analysis at Allan Hancock College this summer.

Ray, Glen↗
NASA NTRS2013

Space Mission Concept Development Using Concept Maturity Levels

Over the past five years, pre-project formulation experts at the Jet Propulsion Laboratory (JPL) has developed and implemented a method for measuring and communicating the maturity of space mission concepts. Mission concept development teams use this method, and associated tools, prior to concepts entering their Formulation Phases (Phase A/B). The organizing structure is Concept Maturity Level (CML), which is a classification system for characterizing the various levels of a concept's maturity. The key strength of CMLs is the ability to evolve mission concepts guided by an incremental set of assessment needs. The CML definitions have been expanded into a matrix form to identify the breadth and depth of analysis needed for a concept to reach a specific level of maturity. This matrix enables improved assessment and communication by addressing the fundamental dimensions (e.g., science objectives, mission design, technical risk, project organization, cost, export compliance, etc.) associated with mission concept evolution. JPL's collaborative engineering, dedicated concept development, and proposal teams all use these and other CML-appropriate design tools to advance their mission concept designs. This paper focuses on mission concept's early Pre-Phase A represented by CMLs 1- 4. The scope was limited due to the fact that CMLs 5 and 6 are already well defined based on the requirements documented in specific Announcement of Opportunities (AO) and Concept Study Report (CSR) guidelines, respectively, for competitive missions; and by NASA's Procedural Requirements NPR 7120.5E document for Projects in their Formulation Phase.

Concept Maturity Levels (CMLs)↗
DOE OSTI2025

IROS 2023 Workshop Report: Draft Guidelines on Manufacturing Procedures, Test Methods and Reporting for Soft Robotics

Soft roboticists are facing challenges with reproducibility, which prevents researchers from making holistic comparisons to prior work, impedes full understanding of results, and forces the need to “reinvent the wheel,” delaying fundamental advances. Reproducibility of results is key to advancing science as well as achieving technology transfer from research laboratories to industrial applications. Recently, a discussion-based workshop dedicated to the topic, “Developing Standard Testing and Reporting Guidelines for Soft Robotics,” was held at IROS 2023 in Detroit, MI. The purpose of this document is to record a set of recommendations and voluntary draft guidelines for soft roboticists concerning fabrication/manufacturing, test procedures, and reporting, which were collectively developed at the workshop. Together as a community, we hope to improve the reporting standards of soft robotics and drive the field as a whole toward more rigorous research practices.

43 PARTICLE ACCELERATORS↗
NASA NTRS2006

Recent Developments in Space Debris Mitigation Policy and Practices

In recent years, emphasis has shifted from national efforts to control the space debris population to international ones. Here, too, great progress has been made, most notably by the Inter-Agency Space Debris Coordination Committee (IADC) and the Committee on the Peaceful Uses of Outer Space (COPUOS) of the United Nations. Today, a firm international consensus is rapidly building on the principal space debris mitigation measures. The IADC is an association of the space agencies of ten countries (China, France, Germany, India, Italy, Japan, Russia, Ukraine, the United Kingdom, and the United States) and the European Space Agency, representing 17 countries of which four (France, Germany, Italy, and the United Kingdom) are also full IADC members. At the 17th meeting of the IADC in October 1999, a new Action Item (AI 17.2) was adopted to develop a set of consensus space debris mitigation guidelines. The purpose of the activity was to identify the most valuable space debris mitigation measures and to reach an international agreement on common directives. The IADC Space Debris Mitigation Guidelines (www.iadc-online.org/index.cgi?item=docs_pub) were formally adopted in October 2002 during the Second World Space Congress in Houston, Texas. Two years later a companion document, entitled Support to the IADC Space Debris Mitigation Guidelines, was completed to provide background and clarification for the guidelines.

Johnson, Nicholas L.↗
NASA NTRS1973

Phase 111A Crew Interface Specifications Development for Inflight Maintenance and Stowage Functions

This report presents the findings and data products developed during the Phase IIIA Crew Interface Specification Study for Inflight Maintenance and Stowage Functions, performed by General Electric for the NASA, Johnson Space Center with a set of documentation that can be used as definitive guidelines to improve the present process of defining, controlling and managing flight crew interface requirements that are related to inflight maintenance (including assembly and servicing) and stowage functions. During the Phase IIIA contract period, the following data products were developed: 1) Projected NASA Crew Procedures/Flight Data File Development Process. 2) Inflight Maintenance Management Process Description. 3) Preliminary Draft, General Specification, Inflight Maintenance Management Requirements. 4) Inflight Maintenance Operational Process Description. 5) Preliminary Draft, General Specification, Inflight Maintenance Task and Support Requirements Analysis. 6) Suggested IFM Data Processing Reports for Logistics Management The above Inflight Maintenance data products have been developed during the Phase IIIA study after review of Space Shuttle Program Documentation, including the Level II Integrated Logistics Requirements and other DOD and NASA data relative to Payloads Accommodations and Satellite On-Orbit Servicing. These Inflight Maintenance data products were developed to be in consonance with Space Shuttle Program technical and management requirements.

Carl, John G.↗
DOE OSTI2022

Guidelines and Specifications for Enhanced Durability Evaluation of Insulating Glass and Vacuum Insulating Glass Units

The National Renewable Energy Laboratory (NREL) has conducted research into durability of advanced fenestration technologies for almost thirty years. NREL has recently begun to research potential methods to enhance durability evaluation of present market insulating glass units (IGU). This document outlines a proposed process flow for adoption of these methods by interested parties. The proposed evaluation process flow described below is still a topic of active research at NREL as well as with industry partners. NREL will periodically update this document based on research results, both internal and external to NREL that may inform development of improved durability evaluation. This document is also meant to serve as a guideline for interested parties who may wish to engage in enhanced durability evaluation of IGU's both internally or with external testing laboratories. NREL will work to support adoption of the suggestions in this guideline by interested partners in the hope that these practices are more broadly adopted by the industry. Further research into this area will continue to inform both adaptations of this guideline as well as development of improved durability evaluation standards.

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATI↗