SEARCH · Engineering Papers

Results for “Electrical components”

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.

SourceResearch connectionFrom yearThrough year

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 235 records · Page 13

All sources NASA NTRS DOE OSTI

NASA NTRS1997

Charged aerosols and electrical structure of the polar summer mesopause region

The results of observations carried out in the framework of two programs, the middle atmosphere electrodynamics campaign and the noctilucent cloud (NLC) campaign, are reported. The measurements performed during overhead NLC and polar mesosphere summer echo (PMSE) conditions revealed a number of aerosol-related layering effects on the region's electrical structure. It was found that both polar components of electrical conductivity can be affected in NLC regions.

Mitchell, John D.↗

NASA NTRS2007

Strong, Lightweight, Porous Materials

A new class of strong, lightweight, porous materials has been invented as an outgrowth of an effort to develop reinforced silica aerogels. The new material, called X-Aerogel is less hygroscopic, but no less porous and of similar density to the corresponding unmodified aerogels. However, the property that sets X-Aerogels apart is their mechanical strength, which can be as much as two and a half orders of magnitude stronger that the unmodified aerogels. X-Aerogels are envisioned to be useful for making extremely lightweight, thermally insulating, structural components, but they may also have applications as electrical insulators, components of laminates, catalyst supports, templates for electrode materials, fuel-cell components, and filter membranes.

Leventis, Nicholas↗

NASA NTRS1988

Average low-latitude meridional electric fields from DE 2 during solar maximum

The average meridional electric field (zonal ion flow) patterns in the region between +/- 30 deg magnetic latitude were obtained by analyzing the electric field data taken by the Vector Electric Field Instrument aboard the DE 2 spacecraft during solar maximum conditions. The average data set displayed a rapid increase of the downward meridional electric field with local time near 1800 MLT; there was a secondary nighttime maximum of this electric field component, observed post midnight, with the crossover to upward electric fields (westward ion flow) occurring between 0400 and 0500 MLT. A sharp return to near zero was observed between 1200 and 1300. The zonal ion drift was found to be approximately symmetric with respect to the geomagnetic equator. These results are compared with results of the DE-2 neutral wind measurements and with results obtained from radar measurements.

Maynard, N. C.↗

NASA NTRS1975

Solar electric propulsion

The major components of a solar electric propulsion system are discussed and some problems in low thrust mission analysis are detailed. Emphasis is placed on the development of a nominal low thrust trajectory and guidance and navigation aspects.

Barbieri, R. W.↗

NASA NTRS1988

Contactless Coupling For Power And Data

Experimental flat-plate coupling transmits digital data signals and electrical power across small gap between two modules. Split transformer and optoelectronic components transmit electrical power and digital signals across small gap. Coupling concept useful substitute for electrical connectors in equipment assembled by robots, remote manipulators, or humans working in protective clothing or otherwise restricted in dexterity. Offers higher reliability due to one overall alignment mechanism as opposed to multiple pin/socket alignment requirements.

Moody, John C.↗

NASA NTRS1993

Precision linear shaped charge severance of graphite-epoxy materials

This paper presents Precision Linear Shaped Charge (PLSC) components designed to sever a variety of target materials. Recent data for the severance of graphite-epoxy panels or targets with PLSC's are presented. A brief history of the requirement to originate the development of PLSC's for weapon components at Sandia National Laboratories is presented. The Department of Energy's (DOE) nuclear weapon systems have continually decreased in size. Today's relatively small weapons require the design of much more efficient, lighter, and smaller explosive components because fragments, air shocks, and pyro-shocks associated with the function of these components can damage electrical and other sensitive components located nearby. The DOE requirements for PLSC's are listed. Therefore, linear shaped charge (LSC) components for weapon systems can no longer be empirically or experimentally designed for a given application. Many of today's designs require severing concentric cylinders, for example, where the LSC jet is designed to sever only one of the two cylinders as was the case for the B90/Nuclear Depth Strike Bomb. Therefore, code modeling and simulation technology must be utilized to obtain a better understanding of the LSC jet hydrodynamic penetration, fracture, shear, and spall mechanisms associated with the severance of metallic as well as composite targets.

Vigil, Manuel G.↗

NASA NTRSDate not supplied

Turbine Electrified Energy Management with Model Predictive Control

Affordability, sustainability, and efficiency are primary motivators driving the future of NASA aeronautics research. These factors are realized, in part, through the development and implementation of new technologies and strategies enabling efficient, affordable, and safe hybrid-electric aircraft. Research supporting electrified aircraft propulsion control systems exemplifies such new methodologies, offering varied opportunities to integrate electric machines with gas-based turbine engines. For hybrid-electric propulsion systems, current conceptual architectures seek to introduce energy storage and exploit electrical power system components to assist gas-based system components. Capitalizing on the electric machines in hybridized engines, Turbine Electrified Energy Management (TEEM) is a control approach that enhances transient operability to improve overall propulsion and vehicle efficiency by injecting or extracting power from engine shafts. Traditionally implemented with proportional-integral (PI) control, this study expands the application of TEEM by presenting model predictive control (MPC) schemes to execute the TEEM concept. Via cost function design and constraint selection, the transient operability goals for TEEM are considered in the controller designs. The proposed MPCs are simulated on a nonlinear turbofan engine model at two environmental conditions, with comparisons drawn to a baseline PI. Performance is evaluated using compressor maps and two TEEM-specific metrics: transient stack usage and transient excursion integral. Simulation results reveal the developed schemes perform comparably to the benchmark controller and can be implemented in two distinct configurations. Potential modifications for future investigations include cost function measures that optimize energy use, additional performance effectiveness measures, and battery storage capabilities.

Elyse D. Hill↗

NASA NTRS1972

A simple tachometer circuit

Electric circuit to measure frequency of repetitive sinusoidal or rectangular wave is presented. Components of electric circuit and method of operation are explained. Application of circuit as tachometer for automobile is discussed.

Dimeff, J.↗

NASA NTRS1992

An intracloud lightning parameterization scheme for a storm electrification model

The parameterization of an intracloud lightning discharge has been implemented in the present storm electrification model. The initiation, propagation direction, and termination of the discharge are computed using the magnitude and direction of the electric field vector as the determining criteria. The charge redistribution due to the lightning is approximated assuming the channel to be an isolated conductor with zero net charge over its entire length. Various simulations involving differing amounts of charge transferred and distribution of charges have been done. Values of charge transfer, dipole moment change, and electrical energy dissipation computed in the model are consistent with observations. The effects of the lightning-produced ions on the hydrometeor charges and electric field components depend strongly on the amount of charge transferred. A comparison between the measured electric field change of an actual intracloud flash and the field change due to the simulated discharge shows favorable agreement. Limitations of the parameterization scheme are discussed.

Helsdon, John H., Jr.↗

NASA NTRS1982

The structure of the plasma sheet-lobe boundary in the Earth's magnetotail

The structure of the magnetotail plasma sheet-plasma lobe boundary was studied by observing the properties of tailward flowing O+ ion beams, detected by the ISEE 2 plasma experiment inside the boundary during three time periods. The computed value of the north-south electric field component as well as the O+ parameters are shown to change at the boundary. The results are related to other observations made in this region. The O+ parameters and the Ez component behavior are shown to be consistent with that expected from the topology of the electric field lines in the tail as mapped from the ionosphere.

Orsini, S.↗

NASA NTRS1984

The structure of the plasma sheet-lobe boundary in the earth's magnetotail

Orsini, S.↗

NASA NTRS1999

Generation of Electron Suprathermal Tails in the Upper Solar Atmosphere: Implications for Coronal Heating

We present a mechanism for the generation of non-Maxwellian electron distribution function in the upper regions of the solar atmosphere in the presence of collisional damping. It is suggested that finite amplitude, low frequency, obliquely propagating electromagnetic waves can carry a substantial electric field component parallel to the mean magnetic field that can be significantly larger than the Dreicer electric field. This long wavelength electric fluctuation is capable of generating high frequency electron plasma oscillations and low frequency ion acoustic-like waves. The analysis has been performed using 1-1/2D Vlasov and PIC numerical simulations in which both electrons and ions are treated kinetically and self consistently. The simulation results indicate that high frequency electron plasma oscillations and low frequency ion acoustic-like waves are generated. The high frequency electron plasma oscillation drives electron plasma turbulence, which subsequently is damped out by the background electrons. The turbulence damping results in electron acceleration and the generation of non-Maxwellian suprathermal tails on time scales short compared to collisional damping. Bulk heating also occurs if the fluctuating parallel electric field is strong enough. This study suggests that finite amplitude, low frequency, obliquely propagating, electromagnetic waves can play a significant role in the acceleration and heating of the solar corona electrons and in the coupling of medium and small-scale phenomena.

Vinas, Adolfo F.↗

NASA NTRS2015

Additive Manufacturing of Aerospace Propulsion Components

The presentation will provide an overview of ongoing activities on additive manufacturing of aerospace propulsion components, which included rocket propulsion and gas turbine engines. Future opportunities on additive manufacturing of hybrid electric propulsion components will be discussed.

Additive Manufacturing↗

NASA NTRS1987

Research in extreme ultraviolet and far ultraviolet astronomy

Analysis and interpretation continued on data generated by the flight of 27.086 in April of 1986 and by the successful UVX mission. Optical and mechanical design of the 1 meter EUV telescope, planned for launch with the large SPARTAN type carrier, ASTRO-SPAS, was also continued. The major effort centered on the preparation of flight 27.106, scheduled to launch in September, 1986. Work which was performed included: design of the skins and bulkheads; completion of the optical, mechanical, and electrical design; purchase of the major components of the instruments; assemblage of the electrical components; and performance of theoretical work, to support the data interpretation.

Bowyer, C. S.↗

NASA NTRS1987

Micro-focus X-ray imaging

The acceptance of surface mounting in the electronics industry has been slowed by problems with component availability, electrical testing, and inspection. Industry suppliers and users have been working to solve these problems, and they are easing. Component manufacturers are offering substantially more devices in surface mountable packages. Automated test equipment vendors are offering test fixtures for surface mount circuit boards. And just recently, solder connection inspection has been automated through a partership effort with a major electronics manufacturer. The results achieved in this effort are presented.

Juha, Michael↗

NASA NTRS2018

Turboelectric and Hybrid Electric Aircraft Drive Key Performance Parameters

NASA has been investigating electrified aircraft propulsion as a means of furthering its goals of reducing fuel burn, emissions, and noise. However, the electric drive components required introduce weight and efficiency penalties at odds with these goals. The purpose of this paper is to propose electric drive specific power, electric drive efficiency, and electrical propulsion fraction as the key performance parameters for fully turboelectric, partially turboelectric, and parallel hybrid electric aircraft power systems. The impacts of these parameters on overall aircraft performance are investigated. Range equations for each aircraft type are described. The benefits and costs that may result from the electrified propulsion systems are enumerated. A breakeven analysis is conducted to find the minimum allowable electric drive specific power and efficiency, for a given electrical propulsion fraction and battery specific energy, that can preserve the range, payload weight, input energy, and ratio of operating empty weight to initial weight of the conventional aircraft.

turboelectric aircraft propulsion↗

NASA NTRS2018

Turboelectric and Hybrid Electric Aircraft Drive Key Performance Parameters

NASA has been investigating electrified aircraft propulsion as a means of furthering its goals of reducing fuel burn, emissions, and noise. However, the electric drive components required introduce weight and efficiency penalties at odds with these goals. The purpose of this paper is to propose electric drive specific power, electric drive efficiency, and electric propulsion fraction as the key performance parameters for fully turboelectric, partially turboelectric, and parallel hybrid electric aircraft power systems. The impact of these parameters on overall aircraft performance are investigated. Range equations for each aircraft type are described. The benefits and costs that may result from the electrified propulsion systems are enumerated. A breakeven analysis is conducted to find the minimum allowable electric drive specific power and efficiency, for a given electrical propulsion fraction and battery specific energy, that can preserve the range, payload weight, input energy, and ratio of operating empty weight to initial weight of the conventional aircraft.

Duffy, Kirsten P.↗

NASA NTRS2015

Electric Motors for Non-Cryogenic Hybrid Electric and Turboelectric Propulsion

NASA Glenn Research Center is investigating hybrid electric and turboelectric propulsion concepts for future aircraft to reduce fuel burn, emissions, and noise. Systems studies show that the weight and efficiency of the electric system components need to be improved for this concept to be feasible. However, advances in motor component materials such as soft magnetic materials, hard magnetic materials, conductors, thermal insulation, and structural materials are expected in the coming years, and should improve motor performance. This study investigates several motor types for a one megawatt application, and projects the motor performance benefits of new component materials that might be available in the coming decades.

Hybrid propulsion↗