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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 343 records · Page 19
All sourcesNASA NTRSDOE OSTI
DOE OSTI2023

AmeriFlux FLUXNET-1F CA-Ca1 British Columbia - 1949 Douglas-fir stand

This is the AmeriFlux Management Project (AMP) created FLUXNET-1F version of the carbon flux data for the site CA-Ca1 British Columbia - 1949 Douglas-fir stand. This is the FLUXNET version of the carbon flux data for the site CA-Ca1 British Columbia - 1949 Douglas-fir stand produced by applying the standard ONEFlux (1F) software. Site Description - 1949 Douglas-fir stand; Tower Type 20" triangular tower; Latitude/Longitude 49.86725N 125.33360W (GPS survey, 2003. Coordinates updated/corrected May, 2006); Elevation 320 m; North-east facing terrain, 5-10 deg slope; Mean Air Temp. 8.3 °C* ; Mean Annual Precipitation 1461 mm * ; Date Operations Began June 1997 ; Frequency of EC Measurements 20.83 Hz; Frequency of Other Met. Sensors 1 - 4 sec, year round ; Soil Respiration Measurements 30 min., automated soil respiration system in 2000, periodically during growing season using portable system in 2002 ; * 1998-2001 averages from the 1948 Douglas-fir stand meteorological tower

Black, T. Andrew↗
DOE OSTI2023

Code Demonstration: Approximation of nearly-periodic symplectic maps via structure-preserving neural networks

In this notebook, we use the symplectic gyroceptron architecture from [Duruisseaux et al., 2022] to learn a surrogate map for the nearly-periodic symplectic flow map associated to a nearly-periodic Hamiltonian system composed of two nonlinearly coupled oscillators, where one of them oscillates significantly faster than the other: $\Big\lbrace$ $ {\dot{q}_1 = p_1 \hspace{5mm} \dot{p}_1 = -q_1 - \epsilon \partial_{q1}U(q_1 , q_2 )} \atop {\dot{q}_2 = \epsilon p_2 \hspace{4mm} \dot{p}_2 = -\epsilon q_2 - \epsilon \partial_{q2}U(q_1 , q_2 )}$. These equations of motion are the Hamilton's equations associated to the Hamiltonian $H_{\epsilon}(q_1,q_2,p_1,p_2)=\frac{1}{2}(q^2_1+p^2_1)+\frac{1}{2}\epsilon(q^2_2+p^2_2)+\epsilon$$U(q_1,q_2)$.

97 MATHEMATICS AND COMPUTING↗
DOE OSTI2025

Trapping Two Dissimilar Rigidity Ions with Identical Average Dynamics

It may seem obvious that ions with different charge-to-mass ratios (q/m) would have different dynamics in a trap or periodic focussing system, leading to different equilibrium bunch shapes and sizes. However, the ponderomotive acceleration in an oscillating field is proportional to (q/m) 2 rather than q/m for the direct field, leading to the possibility of combining the two effects to cancel any differences in the average dynamics between two chosen species.

43 PARTICLE ACCELERATORS↗
NASA NTRS1967

Rotating emission ring in binary systems.

Representation of rotating gaseous emission rings in eclipsing binary systems by periodic orbits around more massive component in restricted three-body problem

PERIODIC ORBIT↗
NASA NTRS1971

Definition study for an extended manned test of a regenerative life support system

A program was defined which consists of extended ground-based manned tests of regenerative life support systems. The tests are to evaluate prototypes of advanced life support systems under operational, integrated conditions, thus providing data for the design of efficient environmental control and life support systems for use in long-duration space missions. The requirements are defined for test operations to provide a simulation of an orbiting space laboratory. The features of Phase A and B programs are described. These tests use proven backup equipment to ensure successful evaluation of the advanced subsystems. A pre-tests all-systems checkout period is provided to minimize equipment problems during extended testing and to familiarize all crew and operating staff members with test equipment and procedures.

Source record↗
NASA NTRS1976

Formulation of detailed consumables management models for the development (preoperational) period of advanced space transportation system. Volume 1: Detailed requirements for the mission planning processor

Detailed requirements for the mission planning processor are documented. The mission planning processor is a user oriented tool for consumables management and is part of the total consumables subsystem management concept. A quasi top-down approach was applied to the design of the mission planning processor. Interface requirements, input/output, and data base concepts were considered before computational processing. Existing analytical models were investigated for applicability before new models were developed. The mission planning processor was designed for an interactive system using demand terminals for input/outputdisplay and interfacing with an updateable mission data bank. The control and support routines provide the user interface, peripheral data handling, program control, and support functions required by the mission planning processor for execution on an interactive system. A description, interface requirements, definition of internal variables, listing of input data, processing flow diagram, and listing of output data are presented for each routine.

Connelly, L. C.↗
NASA NTRS1976

Formulation of detailed consumables management models for the development (preoperational) period of advanced space transportation system. Volume 3: Study of constraints/limitations for STS consumables management

The constraints and limitations for STS Consumables Management are studied. Variables imposing constraints on the consumables related subsystems are identified, and a method determining constraint violations with the simplified consumables model in the Mission Planning Processor is presented.

Newman, C. M.↗
NASA NTRS1978

Photometric study of the X-ray pulsar 4U 1626-67

Results are reported for UBVR photometric observations of the optical candidate for the pulsating X-ray source 4U 1626-67. The data are found to be consistent with a constant V magnitude of approximately 19.00 and marginally consistent with constant B-V and U-B colors, but two averaged measures obtained about 2 hr apart suggest that the B-V and U-B colors are variable and that this variability may be entirely in U and B. Additional evidence for variability of the optical candidate is examined, and it is shown that the optical object is probably variable with a B amplitude of no more than about 0.5 mag and time scales as short as less than the order of 1 min. A power spectrum analysis reveals no significant peaks at or near the X-ray pulse period of 7.68 sec or its harmonics. It is concluded that although the optical data do not provide any additional evidence that 4U 1626-67 is a binary, a short-period binary system with the optical emission strongly dominated by an accretion disk is probably favored.

Grindlay, J. E.↗
NASA NTRS1979

Highly compact binary X-ray sources

It is proposed that many of the X-ray sources associated with the galactic bulge are accreting neutron stars or black holes with masses of at least about 1 solar mass in ultrashort-period binary systems with very low-mass (no more than about 0.5 solar mass) stellar companions. It is demonstrated that this hypothesis may provide a coherent picture of the evolutionary history and observational properties of these sources, including the apparent lack of conspicuous optical counterparts and the apparent absence of X-ray eclipses.

Joss, P. C.↗
NASA NTRS1980

Voyager mission support

Special events participated in by the Deep Space Stations (DSS) for the period of February through April 1980 are presented. The status of the DSS is reviewed for the same period, including system performance tests and operational verification tests. A list of software accepted for operation at the DSS is given.

Fanelli, N.↗
NASA NTRS1982

Civil helicopter propulsion system reliability and engine monitoring technology assessments

A study to reduce operating costs of helicopters, particularly directed at the maintenance of the propulsion subsystem, is presented. The tasks of the study consisted of problem definition refinement, technology solutions, diagnostic system concepts, and emergency power augmentation. Quantifiable benefits (reduced fuel consumption, on-condition engine maintenance, extended drive system overhaul periods, and longer oil change intervals) would increase the initial cost by $43,000, but the benefit of $24.46 per hour would result in breakeven at 1758 hours. Other benefits not capable of being quantified but perhaps more important include improved aircraft avilability due to reduced maintenance time, potential for increased operating limits due to continuous automatic monitoring of gages, and less time and fuel required to make engine power checks. The most important improvement is the on-condition maintenance program, which will require the development of algorithms, equipment, and procedures compatible with all operating environments.

Murphy, J. A.↗
NASA NTRS1982

Simplified aeroelastic modeling of horizontal axis wind turbines

Certain aspects of the aeroelastic modeling and behavior of the horizontal axis wind turbine (HAWT) are examined. Two simple three degree of freedom models are described in this report, and tools are developed which allow other simple models to be derived. The first simple model developed is an equivalent hinge model to study the flap-lag-torsion aeroelastic stability of an isolated rotor blade. The model includes nonlinear effects, preconing, and noncoincident elastic axis, center of gravity, and aerodynamic center. A stability study is presented which examines the influence of key parameters on aeroelastic stability. Next, two general tools are developed to study the aeroelastic stability and response of a teetering rotor coupled to a flexible tower. The first of these tools is an aeroelastic model of a two-bladed rotor on a general flexible support. The second general tool is a harmonic balance solution method for the resulting second order system with periodic coefficients. The second simple model developed is a rotor-tower model which serves to demonstrate the general tools. This model includes nacelle yawing, nacelle pitching, and rotor teetering. Transient response time histories are calculated and compared to a similar model in the literature. Agreement between the two is very good, especially considering how few harmonics are used. Finally, a stability study is presented which examines the effects of support stiffness and damping, inflow angle, and preconing.

Wendell, J. H.↗
NASA NTRS1982

Development of methodology for horizontal axis wind turbine dynamic analysis

Horizontal axis wind turbine dynamics were studied. The following findings are summarized: (1) review of the MOSTAS computer programs for dynamic analysis of horizontal axis wind turbines; (2) review of various analysis methods for rotating systems with periodic coefficients; (3) review of structural dynamics analysis tools for large wind turbine; (4) experiments for yaw characteristics of a rotating rotor; (5) development of a finite element model for rotors; (6) development of simple models for aeroelastics; and (7) development of simple models for stability and response of wind turbines on flexible towers.

Dugundji, J.↗
NASA NTRS1984

Optical identification of 2S 1417-62

The 17 s X-ray pulsar 2S 1417-62 has been identified with a V of approximately 16.9 mag OB star on the basis of an X-ray position obtained with the Einstein X-Ray Observatory and spectrophotometry with the 4-m telescope at Cerro Tololo Inter-American Observatory. Strong H-alpha emission is observed as well as significant changes in X-ray luminosity. The optical counterpart may be either a Be or a B I star, but the H-alpha emission strength and galactic position suggest that a Be star is more likely. A Be star identification also further supports the limit of approximately 15 days or more on the system binary period obtained by Kelley et al. (1981) from pulse timing studies.

Grindlay, J. E.↗