silkski/ENERAD huggingface dataset:
An accelerated total ionizing dose ( TID ) hardness assurance test for enhanced low dose rate sensitive ( ELDRS ) bipolar linear circuits , using high dose rate tests on parts that have been exposed to molecular hydrogen , has been proposed and demonstrated on several ELDRS part types . In this study several radiation - hardened " ELDRS - free " part types have been tested using this same approach to see if the test is overly conservative .
VLBI observations of intraday variable ( IDV ) quasars found in the MASIV ( Micro - Arcsecond Scintillation - Induced Variability ) 5 GHz VLA Survey of 500 flat - spectrum sources in the northern sky have shown that these sources are extremely compact , often unresolved , on milliarcsecond scales , and more core - dominated than their non - IDV counterparts . VAST : an ASKAP Survey for Variables and Slow Transients , proposes to observe 10,000 square degrees of southern sky daily for 2 years in the VAST - Wide survey component . This is expected to reveal of order 30,000 compact sources brighter than 10 mJy showing refractive interstellar scintillation ( the cause of centimeter - wavelength IDV ) at the survey frequency of about 1.4 GHz . Many of these sources may be suitable astrometric calibrators for VLBI at higher frequencies .
A generalized exact optical bright solitary wave solution in a three dimensional dispersive linear medium is presented . The most interesting property of the solution is that it can exist in the normal group - velocity - dispersion ( GVD ) region . In addition , another peculiar feature is that it may achieve a condition of ' zero - dispersion ' to the media so that a solitary wave of arbitrarily small amplitude may be propagated with no dependence on is pulse width .
Large scale distributions of ozone , water vapor , aerosols , and clouds were measured throughout the troposphere by two NASA Langley lidar systems on board the NASA DC-8 aircraft as part of the Tropical Composition , Cloud , and Climate Coupling Experiment ( TC4 ) over Central and South America and adjacent oceans in the summer of 2007 . Special emphasis was placed on the sampling of convective outflow and transport , sub - visible cirrus clouds , boundary layer aerosols , Saharan dust , volcanic emissions , and urban and biomass burning plumes . This paper presents preliminary results from this campaign , and demonstrates the value of coordinated measurements by the two lidar systems .
The Don Quijote Phase - A study is a definition study funded by ESA and devoted to the analysis of the possibilities to deflect a Near Earth Object ( NEO ) in the range of 300 - 800 m diameter . DEIMOS Space S.L. and EADS Astrium have teamed up within this study to form one of the three consortia that have analyzed these aspects for ESA . Target asteroids for the mission are 1989 ML , 2002 AT4 and Apophis . This paper presents the mission analysis activities within the consortium providing : low - thrust interplanetary rendezvous Orbiter trajectories to the target asteroids , ballistic interplanetary trajectories for the Impactor , Orbiter arrival description at the asteroids , Orbiter stable orbits characterization at the asteroid , deflection determination by means of a Radio Science Experiment ( RSE ) as well as the mission timelines and overall mission scenarios .
With the intent of improving the safety characteristics of lithium ion cells , electrolytes containing flame retardant additives have been investigated . A number of triphenyl phosphate - containing electrolytes were evaluated in both coin cells and experimental three electrode lithium - ion cells ( containing reference electrodes ) . A number of chemistries were investigated , including MCMB carbon / LiNi(0.8)Co(0.2)O2 ( NCO ) , graphite / LiNi(0.8)Co(0.15)Al(0.05)O2 ( NCA ) , Li / Li(Li(0.17)Ni(0.25)Mn(0.58))O2 , Li / LiNiMnCoO2 ( NMC ) and graphite / LiNiMnCoO2 ( NMC ) , to study the effect that different electrolyte compositions have upon performance . A wide range of TPP - containing electrolytes were demonstrated to have good compatibility with the C / NCO , C / NCA , and Li / NMC systems , however , poor performance was initially observed with the high voltage C / NMC system . This necessitated the development of improved electrolytes with stabilizing additives , leading to formulations containing lithium bis(oxalato)borate ( LiBOB ) that displayed substantially improved performance .
In this work , we study the performance of structured Low - Density Parity - Check ( LDPC ) Codes together with bandwidth efficient modulations . We consider protograph - based LDPC codes that facilitate high - speed hardware implementations and have minimum distances that grow linearly with block sizes . We cover various higher- order modulations such as 8 - PSK , 16 - APSK , and 16 - QAM . During demodulation , a demapper transforms the received in - phase and quadrature samples into reliability information that feeds the binary LDPC decoder . We will compare various low - complexity demappers and provide simulation results for assorted coded - modulation combinations on the additive white Gaussian noise and independent Rayleigh fading channels .
Object - Relational database management system is an integrated hybrid cooperative approach to combine the best practices of both the relational model utilizing SQL queries and the object - oriented , semantic paradigm for supporting complex data creation . In this paper , a highly scalable , information on demand database framework , called NETMARK , is introduced . NETMARK takes advantages of the Oracle 8i object - relational database using physical addresses data types for very efficient keyword search of records spanning across both context and content . NETMARK was originally developed in early 2000 as a research and development prototype to solve the vast amounts of unstructured and semistructured documents existing within NASA enterprises . Today , NETMARK is a flexible , high - throughput open database framework for managing , storing , and searching unstructured or semi - structured arbitrary hierarchal models , such as XML and HTML .
This viewgraph presentation describes the 2005 Pathfinder along with an investigation of its aeroelastic responses . The contents include : 1 ) HALE Class of Vehicles ; 2 ) Aero - elastic Research Flights Overall Objective ; 3 ) General Arrangement ; 4 ) Sensor Locations ; 5 ) NASA Ramp Operations ; 6 ) Lakebed Operations ; 7 ) 1st Flight Data Set ; 8) Tool development / data usage ; 9 ) HALE Tool Development & Validation ; 10 ) Building a HALE Foundation ; 11 ) Compelling Needs Drive HALE Efforts ; and 12 ) Team Photo
In support of Operations Community Coordinated Modeling Center ( CCMC ) performing validation and verification of space weather models . To identify suitable metrics the CCMC focus on parameters most useful to operations that CCMC resident models can provide . The real time simulations carried out at CCMC are an essential tool to test model performance and stability by using input conditions that may occur in nature at any time . Since 2001 , the magnetospheric MHD model BATSRUS has been run in real time using ACE real time data . CCMC staff developed an experimental real - time system that controls uploading of the real - time ACE data , monitors continuous model execution , initiates automatic recovery procedure in case of data gaps or hardware failures , synchronizes BATSRUS and FRC runs , and periodically runs IDL based visualization software .
A key component of future models of coronal evolution will be the high resolution vector magnetograms that drive the models . Much of this data will have limited field of view , and so will need to be supplemented from other sources , particularly when a global context is needed . I will discuss our plans to develop a tool capable of synthesizing magnetograms from multiple sources . This will rely heavily on the CCMC 's KAMELEON data formatter and interpolator .
We have measured iridium and platinum in ancient metasediments to obtain the first direct constraints on the extraterrestrial mass flux at the Earth 's surface before 3.8 Gyr ( the Hadean era ) . The craters of the Moon record an intense " late heavy bombardment " ( LHB ) beginning as early as 4.15 Gyr , and terminating ca.3.85 + /- 0.05 Gyr . Recent geochemical studies of metasediments and other supracrustal rocks from Akilia Island , in southern West Greenland , appear to extend both the record of marine sedimentation and the record of metabolically - sophisticated life to > 3.8 Gyr . Additional information is contained in the original extended abstract .
The New Millennium Program 's ( NMP ) Space Technology 5 ( ST-5 ) Project , currently in Phase B of the design process , is slated to launch three 20 - kg class spin stabilized microsatellites in late 2003 . The proposed orbit is highly elliptical and could result in an earth shadow eclipse of almost 2 hours . Although ST-5 's maximum eclipse is only 2 hours , future missions could involve eclipses as long as 8 hours . As spacecraft size , mass , and available resources decrease and eclipse duration increases , thermal engineers will be challenged to design simple but robust thermal control systems that meet temperature requirements for all phases of the mission . This paper presents the results of a study of three design concepts and preliminary analysis of the design selected for ST-5 .
A viewgraph presentation describing thermal - mechanical tests on the structures of hypersonic vehicles is shown . The topics include : 1 ) U.S. Laboratories for Hot Structures Testing ; 2 ) NASA Dryden Flight Loads Laboratory ; 3 ) Hot Structures Test Programs ; 4 ) Typical Sequence for Hot Structures Testing ; 5 ) Current Hot Structures Testing ; and 6 ) Concluding Remarks .
Xenoliths are foreign clasts that oc - cur in various classes of meteorites , e.g. [ 1,2,3 ] . A re - cent study reveals the presence of several distinct classes of xenoliths in regolith - bearing meteorites , in - cluding in over 20 different carbonaceous chondrites [ 4 ] . The most common types of xenoliths are fine - grained hydrous clasts , often referred to as C1 or CI clasts in the literature , although their mineralogy is actually more similar to hydrous micrometeorites [ 5,6 ] . Xenoliths in meteorites present an opportunity to study material not yet classified or available as separate meteorites , and can provide additional information on processes in the dynamic early history of the Solar Sys - tem . Here we have performed chemical and mineralogi - cal analyses of xenoliths in the CM2 carbonaceous chondrite LON 94101 , using scanning electron micro - scopy ( SEM ) and transmission electron microscopy ( TEM ) .
We study the shock formation and energy dissipation of slow magnetosonic waves in coronal plumes . The wave parameters and the spreading function of the plumes as well as the base magnetic field strength are given by empirical constraints mostly from SOHO / UVCS . Our models show that shock formation occurs at low coronal heights , i.e. , within 1.3 bun , depending on the model parameters . In addition , following analytical estimates , we show that scale height of energy dissipation by the shocks ranges between 0.15 and 0.45 Rsun . This implies that shock heating by slow magnetosonic waves is relevant at most heights , even though this type of waves is apparently not a solely operating energy supply mechanism .
We report here on the predicted impact of species such as ice - water , CO2 , CH4 , and NH3 , on oxidized titanium , as well as HC species on diamond surfaces . These simulations provide the dynamics of product distributions during and after a hypervelocity impact event , ionization fractions , and dissociation probabilities for the various species of interest as a function of impact velocity ( energy ) . We are using these results to determine the relevance of the fragmentation process to Cassini INMS results , and to quantify its effects on the observed spectra .
The Antarctic Dry Valleys ( ADV ) provide a unique terrestrial analog for Martian surface processes as they are extremely cold and dry sedimentary environments . The surface geology and the chemical composition of the Dry Valleys that are similar to Mars suggest the possible presence of these soil - formation processes on Mars . The soils and sediments from Wright Valley , Antarctica were investigated in this study to examine mineralogical and chemical changes along the surface layer in this region and as a function of depth . Surface samples collected near Prospect Mesa and Don Juan Pond of the ADV were analyzed using visible / near - infrared ( VNIR ) and mid - IR reflectance spectroscopy and major and trace element abundances .
Insights and lessons learned from the aerodynamic analysis of the High Wing Transport ( HWT ) high - lift configuration are presented . Three - dimensional Navier - Stokes CFD simulations using the OVERFLOW flow solver are compared with high Reynolds test data obtained in the NASA Ames 12 Foot Pressure Wind Tunnel ( PWT ) facility . Computational analysis of the baseline HWT high - lift configuration with and without Externally Blown Flap ( EBF ) jet effects is highlighted . Several additional aerodynamic investigations , such as nacelle strake effectiveness and wake vortex studies , are presented . Technical capabilities and shortcomings of the computational method are discussed and summarized .
This viewgraph presentation discusses : radiation fundamentals , radiation damage , how radiation dosage is determined , fluence testing approaches , ionization damage exposure , displacement damage exposure , Europa energy " bins " , rationale for group flux ( energy bins ) , electron / proton group fluences , electron beam exposure testing , proton sources , reactor exposures , gamma exposures , preliminary exposure findings , testing caveats , preliminary conclusions , internal discharge , and electron dose depth curves .
The goal of our efforts is to extrapolate nearfield jet noise measurements to the geometric far field where the jet noise sources appear to radiate from a single point . To accomplish this , information about the location of noise sources in the jet plume , the radiation patterns of the noise sources and the sound pressure level distribution of the radiated field must be obtained . Since source locations and radiation patterns can not be found with simple single microphone measurements , a more complicated method must be used .
The paper presents reliability assessment results for the robust designs under uncertainty of a 3 - D flexible wing previously reported by the authors . Reliability assessments ( additional optimization problems ) of the active constraints at the various probabilistic robust design points are obtained and compared with the constraint values or target constraint probabilities specified in the robust design . In addition , reliability - based sensitivity derivatives with respect to design variable mean values are also obtained and shown to agree with finite difference values . These derivatives allow one to perform reliability based design without having to obtain second - order sensitivity derivatives . However , an inner - loop optimization problem must be solved for each active constraint to find the most probable point on that constraint failure surface .
This paper investigates the inertial force effect on nonlinear aeroelasticity of flexible wing aircraft . The geometric are nonlinearity due to rotational and tension stiffening . The effect of large bending deflection will also be investigated . Flutter analysis will be conducted for a truss - braced wing aircraft concept with tension stiffening and inertial force coupling .
The goals of the Integrated Medical Model ( IMM ) are to develop an integrated , quantified , evidence - based decision support tool useful to crew health and mission planners and to help align science , technology , and operational activities intended to optimize crew health , safety , and mission success . Presentation slides address scope and approach , beneficiaries of IMM capabilities , history , risk components , conceptual models , development steps , and the evidence base . Space adaptation syndrome is used to demonstrate the model 's capabilities .
On January 29 , 2016 , the Space Station Integrated Kinetic Launcher for Orbital Payload Systems ( SSIKLOPS ) , known as " Cyclops " to the International Space Station ( ISS ) community , deployed Lonestar from the ISS . The deployment of Lonestar , a collaboration between Texas A&M University and the University of Texas at Austin , continued to showcase the simplicity and reliability of the Cyclops deployment system . Cyclops , a NASA - developed , dedicated 10 - 100 kg class ISS SmallSat deployment system , utilizes the Japanese airlock and robotic systems to seamlessly insert SmallSats into orbit . This paper will illustrate Cyclops ' successful deployment of Lonestar from the ISS as well as outline its concept of operations , interfaces , requirements , and processes .
The International Space Station ( ISS ) Environmental Control and Life Support ( ECLS ) system includes regenerative and non - regenerative technologies that provide the basic life support functions to support the crew , while maintaining a safe and habitable shirtsleeve environment . This paper provides a summary of the U.S. ECLS system activities over the past year , covering the period of time between March 2010 and February 2011 and the continued permanent presence of six crew members on ISS . Work continues on the last of the Phase 3 pressurized elements , commercial cargo resupply vehicles , and extension of the ISS service life from 2015 to 2020 or beyond .
The SNC ( martian ) meteorites exhibit complex isotopic characteristics that yield information both about the ages of individual meteorites as well as information about the petrogenetic processes that produced both individual samples and about the origins of suites and sub - suites within the SNC clan . Here I review these data , reiterate earlier interpretations , and offer some new conclusions .
Three - dimensional effects related to the analysis of stitched textile composites are discussed . The method of calculation is based on the virtual crack closure technique ( VCCT ) , and models that model the upper and lower surface of the delamination or debond with two - dimensional ( 2D ) plate elements rather than three - dimensional ( 3D ) solid elements . The major advantages of the plate element modeling technique are a smaller model size and simpler geometric modeling . Details of the modeling of the laminated plate and the stitching are discussed .
This paper documents a process for analyzing whether a particular supersonic aircraft configuration layout and a given cruise condition are feasible to achieve a trimmed low - boom design . This process was motivated by the need to know whether a particular configuration at a given cruise condition could be reshaped to satisfy both low - boom and flight trim constraints . Without such a process , much effort could be wasted on shaping a configuration layout at a cruise condition that could never satisfy both low - boom and flight trim constraints simultaneously . The process helps to exclude infeasible configuration layouts with minimum effort and allows a designer to develop trimmed low - boom concepts more effectively . A notional low - boom supersonic demonstrator concept is used to illustrate the analysis / design process .
The goal of this research is to develop an advanced engineering analysis system that enables high - fidelity , multi - disciplinary , full propulsion system simulations to be performed early in the design process ( a virtual test cell that integrates propulsion and information technologies ) . This will enable rapid , high - confidence , cost - effective design of revolutionary systems .
NGST will be an IR based optical system that will operate at cryogenic temperatures . As part of the AMSD program , Kodak must demonstrate the ability of our system to perform at these very cold temperatures . Kodak will discuss the test approach that will be used for cryogenic testing at MSFC 's XRCF .
Design of robust aircraft structure requires consideration of the load - carrying capability with large damage . Large notches , typically introduced as machined cracks ( aka “ notches ” ) severing a single skin bay and a central stiffening member , are often used to conservatively address the wide range of possible large damage scenarios . The objective of current effort was to explore the viability of developing preliminary laminate - based methods for predicting crack turning at the adjacent stiffener using traditional fracture mechanics concepts .
Cyanobacterial mats provide insights into ancient benthic microbial communities and their biosignatures . Thick mats occupy hypersaline saltern ponds at Guerrero Negro , Baja California , Mexico . Mat biota maintains rapid rates of biogeochemical processes under steep and rapidly changing environmental gradients . Cycling of C , O , and S all increased identically with temperature , indicating the tight coupling of these cycles . An enormous microbial diversity exhibits a highly structured spatial distribution of populations .
At supersonic cruise conditions , high fuel temperatures , coupled with low pressures in the combustor , create potential for superheated fuel injection leading to shorter fuel jet break - up time and reduced spray penetration . Another issue particularly important to the supersonic cruise is the aircraft emissions contributing to the climate change in the atmosphere . Needless to say , aircraft emissions in general also contribute to the air pollution in the neighborhood of airports . The objectives of the present efforts are to establish baseline for prediction methods and experimental data for ( a ) liquid fuel atomization and vaporization at superheated conditions and ( b ) particle sampling systems and laboratory or engine testing environments , as well as to document current capabilities and identify gaps for future research .
Eddy current methods have been successfully used in a variety of non - destructive evaluation applications including detection of cracks , measurements of material thickness , determining metal thinning due to corrosion , measurements of coating thickness , determining electrical conductivity , identification of materials , and detection of corrosion in heat exchanger tubes . This paper describes the development of an eddy current prototype that combines positional and eddy - current data to produce a C - scan of tested material . The preliminary system consists of an eddy current probe , a position tracking mechanism , and basic data visualization capability . Initial test results of the prototype are presented in this paper .
Feature based registration is one of the most reliable methods to register multi - sensor images ( both active and passive imagery ) since features are often more reliable than intensity or radiometric values . The only situation where a feature based approach will fail is when the scene is completely homogenous or densely textural in which case a combination of feature and intensity based methods may yield better results . In this paper , we present some preliminary results of testing our scale space feature based registration technique , a modified version of feature based method developed earlier for classification of multi - sensor imagery . The proposed approach removes the sensitivity in parameter selection experienced in the earlier version as explained later .
An inlet redesign of the T-38 was completed and flight tested by NASA Johnson Space Center ( JSC ) , Houston Texas . The redesign will allow full gross weight takeoffs from high altitude airports such as El Paso , Texas ( ELP ) with runway temperatures up to 99 degrees F , an increase of 9 degrees F over the current performance . This project was completed in - house using innovative test techniques . The static thrust of the T-38 was increased 20 % with this new inlet .