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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 19 records
All sourcesNASA NTRSDOE OSTI
DOE OSTI2013

Gen IV Materials Handbook Functionalities and Operation (4A) Handbook (V.4.0)

This document is prepared for navigation and operation of the Gen IV Materials Handbook, with architecture description and new user access initiation instructions. Development rationale and history of the Handbook is summarized. The major development aspects, architecture, and design principles of the Handbook are briefly introduced to provide an overview of its past evolution and future prospects. Detailed instructions are given with examples for navigating the constructed Handbook components and using the main functionalities. Procedures are provided in a step-by-step fashion for Data Upload Managers to upload reports and data files, as well as for new users to initiate Handbook access.

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DOE OSTI2025

TMD Handbook

This handbook provides a comprehensive review of transverse-momentum-dependent parton distribution functions and fragmentation functions, commonly referred to as transverse momentum distributions (TMDs). TMDs describe the distribution of partons inside the proton and other hadrons with respect to both their longitudinal and transverse momenta. They provide unique insight into the internal momentum and spin structure of hadrons, and are a key ingredient in the description of many collider physics cross sections. Understanding TMDs requires a combination of theoretical techniques from quantum field theory, nonperturbative calculations using lattice QCD, and phenomenological analysis of experimental data. The handbook covers a wide range of topics, from theoretical foundations to experimental analyses, as well as recent developments and future directions. It is intended to provide an essential reference for researchers and graduate students interested in understanding the structure of hadrons and the dynamics of partons in high energy collisions.

72 PHYSICS OF ELEMENTARY PARTICLES AND FIELDS↗
DOE OSTI2014

Overview of the 2014 Edition of the International Handbook of Evaluated Reactor Physics Benchmark Experiments (IRPhEP Handbook)

The International Reactor Physics Experiment Evaluation Project (IRPhEP) is a widely recognized world class program. The work of the IRPhEP is documented in the International Handbook of Evaluated Reactor Physics Benchmark Experiments (IRPhEP Handbook). Integral data from the IRPhEP Handbook is used by reactor safety and design, nuclear data, criticality safety, and analytical methods development specialists, worldwide, to perform necessary validations of their calculational techniques. The IRPhEP Handbook is among the most frequently quoted reference in the nuclear industry and is expected to be a valuable resource for future decades.

11 NUCLEAR FUEL CYCLE AND FUEL MATERIALS↗
NASA NTRS1963

Space Flight Handbooks. Volume 3 - Planetary Flight Handbook: Speed Contours & Auxiliary Graphs for Manned Missions to Mars and Venus - Part 1

This Handbook contains a series of maps, graphs, and tables which will be of use to the preliminary design analyst in scheduling round-trip interplanetary missions to Mars and Venus in the time period 1965-1999. It constitutes the third in a series of space flight manuals prepared for the George C. Marshall Space Flight Center, NASA. The present Handbook, denoted as Volume 3 of this series, is divided into three Parts. Part 3-1 presents maps for obtaining departure and arrival speeds for trips to these planets, a listing of useful constants, planetary ephemerides, tables of important occurrences, and a number of auxiliary graphs. Although most of the basic calculations were performed for the period 1965 -1980, much of the information is also applicable to the years 1980- 1999, as is explained in the text.

VENUS↗
NASA NTRS1968

Space Flight Handbooks. Volume 3, Planetary Flight Handbook: Mars Stopover Missions Using Venus Swingbys - Part 6

This volume of the NASA Planetary Flight Handbook contains trajectory data to aid the mission analyst in the planning of stopover missions to Mars that employ the Venus swingby mode. Compared to other mission modes, the Venus swingbys yield substantial reductions in propulsive velocity and Earth entry speed requirements when employed as part of a round trip stopover mission. Conversely, the swingbys are at best, of marginal utility for one-way missions. Consequently, this Handbook has been tailored expressly for use in the planning of round trip missions. The relevant charts, graphs, and tabular data are presented for the totality of such missions, i.e., in terms of total round trip mission duration and stopover time at Mars. Recognizing, however, that within the context of round trip missions the single-leg data can be of importance in certain phases of the mission analyses, all such data has been preserved on a master magnetic tape. Copies of this tape will be made available to interested organizations.

Source record↗
NASA NTRS1968

Space Flight Handbooks: Planetary Flight Handbook; Mars Stopover Missions Using Venus Swingbys - Volume 3, Part 6

This is the second of three supplements to the Handbook of Mars Stopover Missions Using Venus Swingbys, Part 6 of NASA SP-35, Planetary Flight Handbook. NASA SP-35, Part 6, contains a general discussion, contour charts and related graphical information. Supplement A contains the tabular trajectory data for zero-day stopover time missions, and Supplement C contains the tabular trajectory data for 60-day stopover time missions.

Source record↗
NASA NTRS1963

Space Flight Handbooks. Volume 3- Planetary Flight Handbook: Supplementary Trajectory Data: Venus to Earth and Mars to Earth - Part 2

Parts 2 and 3 present tabulations of trajectory data for scheduling flights to and from Venus and Mars during the period 1960-2000. Part 2 contains information for outbound flights to these planets; Part 3 contains information for trajectories returning from the planets to Earth. Each Part contains data for single-plane transfers, as well as for broken-plane transfers which employ a midcourse plane-change to eliminate the high speed "ridges." The mathematical analyses employed for all calculations are described in Part 1 of this handbook. To facilitate the construction of round-trip trajectories, the date at the target planet is held fixed while the trip duration is varied in 10-day increments from zero days to the length of that planet's synodic period with Earth. Dates of arrival at the target planet are presented in the extreme right-hand column of Part 2, and dates of departure from the target planet are presented in the extreme left-hand column of Part 3. Thus, by holding Part 2 directly to the left of Part 3, the analyst may easily and rapidly scan all trip possibilities which involve any desired stopover time at the target planet. Within approximately 200 days of each conjunction or opposition, data are presented in 10-day increments at the target planet. Only those trips are listed for which the hyperbolic excess speeds at either or both ends of the trajectory do not exceed 0.6 EMOS (Earth Mean Orbital Speed). For the remaining mission regions, the requirements are so smoothly varying that a 50-day interval in dates at the target planet may be employed; the 10-day interval in trip times is, however, preserved here. In these regions, only those trips are listed for which either or both speeds do not exceed 0.3 EMOS.

INTERPLANETARY FLIGHT↗
NASA NTRS1963

Space Flight Handbooks. Volume 3- Planetary Flight Handbook: Supplementary Trajectory Data: Venus to Earth and Mars to Earth - Part 3

Parts 2 and 3 present tabulations of trajectory data for scheduling flights to and from Venus and Mars during the period 1960-2000. Part 2 contains information for outbound flights to these planets; Part 3 contains information for trajectories returning from the planets to Earth. Each Part contains data for single-plane transfers, as well as for broken-plane transfers which employ a midcourse plane-change to eliminate the high speed "ridges." The mathematical analyses employed for all calculations are described in Part 1 of this handbook. To facilitate the construction of round-trip trajectories, the date at the target planet is held fixed while the trip duration is varied in 10-day increments from zero days to the length of that planet's synodic period with Earth. Dates of arrival at the target planet are presented in the extreme right-hand column of Part 2, and dates of departure from the target planet are presented in the extreme left-hand column of Part 3. Thus, by holding Part 2 directly to the left of Part 3, the analyst may easily and rapidly scan all trip possibilities which involve any desired stopover time at the target planet. Within approximately 200 days of each conjunction or opposition, data are presented in 10-day increments at the target planet. Only those trips are listed for which the hyperbolic excess speeds at either or both ends of the trajectory do not exceed 0.6 EMOS (Earth Mean Orbital Speed). For the remaining mission regions, the requirements are so smoothly varying that a 50-day interval in dates at the target planet may be employed; the 10-day interval in trip times is, however, preserved here. In these regions, only those trips are listed for which either or both speeds do not exceed 0.3 EMOS.

Source record↗
DOE OSTI2019

Precipitation Meteorological Instruments (PRECIPMET) Handbook

The PRECIPMET surface meteorology instrument system provides temperature, relative humidity, pressure, wind speed and direction, and precipitation data relevant to the precipitation network instruments: laser disdrometer (PARS2) and radar wind profiler (RWP). The PRECIPMET is installed at the intermediate facilities (IF) of the U.S. Department of Energy (DOE)’s Atmospheric Radiation Measurement (ARM) Southern Great Plains (SGP) atmospheric observatory. The instrument system consists of a Vaisala WXT520 weather transmitter and a 12”-diameter Novalynx tipping bucket rain gauge (TBRG). The WXT520 is mounted on top of the control building at a height of approximately 4 meters. The tipping bucket is mounted on a pole level with the surrounding fencing (approximately 2 meters) to prevent physical interference with the gauge.

54 ENVIRONMENTAL SCIENCES↗