silkski/ENERAD huggingface dataset:
The purpose of this project is to explore the mobility , mixing , and possible clumping of Pb isotopes during laboratory impact shock experiments . Impact events are a common planetary occurrence and their effect on istotope systematics and subsequent geochronology is not fully understood . By artificially shocking mixtures of zircon and sanidine and investigating the sample products , it may be possible to understand if and how Pb is mobilized during impact shock . Isotopes of Pb are the final daughter products of the decay chains of 238U , 235U and 232Th and therefore understanding how mobile the daughter product is during impact events could have consequences for dating impact events . These investigations will also reveal if Pb isotopes can be mixed between minerals
Acoustic emission ( AE ) data acquired during intermittent load hold tensile testing of epoxy impregnated Kevlar(Registeres TradeMark ) 49 ( K / Ep ) composite strands were analyzed to monitor progressive damage during the approach to tensile failure . Insight into the progressive damage of K / Ep strands was gained by monitoring AE event rate and energy . Source location based on energy attenuation and arrival time data was used to discern between significant AE attributable to microstructural damage and spurious AE attributable to noise . One of the significant findings was the observation of increasing violation of the Kaiser effect ( Felicity ratio < 1.0 ) with damage accumulation . The efficacy of three different intermittent load hold stress schedules that allowed the Felicity ratio to be determined analytically is discussed .
The Marshall Space Flight Center ( MSFC ) is developing x - ray mirror modules for the Astronomical Roengen Telescope- X - ray Concentrator ( ART - XC ) instrument on board the Spectrum - Roentgen - Gamma Mission . ART - XC will consist of seven co - aligned x - ray mirror modules with seven corresponding CdTe focal plane detectors . Each module provides an effective area of 65 sq cm at 8 keV , response out to 30 keV , and an angular resolution of 45 arcsec or better HPD . We will present a status of the ART x - ray module development at MSFC .
This article describes processes involved in developing subsystem hazard analyses for Source Controlled Items ( SCI ) , specific components , sub - assemblies , and/or piece parts , of the NASA ARES I Upper Stage ( US ) project . SCIs will be designed , developed and /or procured by Boeing as an end item or an off - the - shelf item . Objectives include explaining the methodology , tools , stakeholders and products involved in development of these hazard analyses . Progress made and further challenges in identifying potential subsystem hazards are also provided in an effort to assist the System Safety community in understanding one part of the ARES I Upper Stage project .
In 1995 , Lewis participated in a pilot test of Lead Specifications . The Specifications were sponsored by the Center to Protect Worker 's Rights ( CPWR ) . Entitled " Model Specifications for the Protection of Worker 's from Lead on Steel Structures " , one aspect of this endeavor was to test and compare several lead abatement technologies . The project overview , objectives , team , and requirements as well as abatement methods and materials are outlined .
In previous studies , a mixed finite element was derived and shown to be effective in facilitating accurate modal reduction of rotor blades . This study builds upon that earlier work through the development of algorithms that allow the element 's Lagrangian axial displacement degrees of freedom to be eliminated in favor of the axial force degrees of freedom . This reduction process , which had been demonstrated previously for the case of a single mixed finite element , may be viewed as a generalization of the UMARC blade analysis methodology to arbitrary topologies . A unique strength of the method . developed here is that the model may consist of two dimensional or even three dimensional elements .
We consider the use of low speed preconditioning for time dependent problems . These are solved using a dual time step approach . We consider the effect of this dual time step on the parameter of the low speed preconditioning . In addition , we compare the use of two sets of variables , conservation and primitive variables , to solve the system . We show the effect of these choices on both the convergence to a steady state and the accuracy of the numerical solutions for low Mach number steady state and time dependent flows .
The electric resistance of woven SiC fiber reinforced SiC matrix composites were measured under tensile loading conditions . The results show that the electrical resistance is closely related to damage and that real - time information about the damage state can be obtained through monitoring of the resistance . Such self - sensing capability provides the possibility of on - board / in - situ damage detection or inspection of a component during " down time " . The correlation of damage with appropriate failure mechanism can then be applied to accurate life prediction for high - temperature ceramic matrix composites .
This viewgraph presentation reviews the use of particle analysis to assist in preparing for the 4th Hubble Space Telescope ( HST ) Servicing mission . During this mission the Space Telescope Imaging Spectrograph ( STIS ) will be repaired . The particle analysis consisted of Finite element mesh creation , Black - body viewfactors generated using I - DEAS TMG Thermal Analysis , Grey - body viewfactors calculated using Markov method , Particle distribution modeled using an iterative Monte Carlo process , ( time - consuming ) ; in house software called MASTRAM , Differential analysis performed in Excel , and Visualization provided by Tecplot and I - DEAS . Several tests were performed and are reviewed : Conformal Coat Particle Study , Card Extraction Study , Cover Fastener Removal Particle Generation Study , and E - Graf Vibration Particulate Study . The lessons learned during this analysis are also reviewed .
Aeolian tone generation from tandem cylinders is predicted using a hybrid approach . A standard computational fluid dynamics ( CFD ) code is used to compute the unsteady flow around the cylinders , and the acoustics are calculated using the acoustic analogy . The CFD code is nominally second order in space and time and includes several turbulence models , but the SST k - omega model is used for most of the calculations . Significant variation is observed between laminar and turbulent cases , and with changes in the turbulence model . A two - dimensional implementation of the Ffowcs Williams - Hawkings ( FW - H ) equation is used to predict the far - field noise .
Phased microphone array measurements obtained during flight tests conducted in 2016 and 2017 are used to assess the importance of local meteorological measurements on the data . In particular , the effectiveness of atmospheric absorption corrections is evaluated under vastly different temperature and humidity conditions . The results indicate that , even under conditions with high absorption , sources can be visualized up to a frequency that is dependent on background noise levels , wind , and atmospheric turbulence . However , absolute levels were found to be problematic on days with high absorption rates , with the discrepancies most prevalent for aircraft positions further from the center of the array . Restricting the data to those days with favorable meteorological conditions generally resulted in a good collapse of the spectra , with differences less than a couple of decibels .
The Quartz Crystal Microbalance Surface Acoustic Wave ( QCM / SAW ) cascade impactor is an instrument designed to collect size - fractionated distributions of aerosols on a series of quartz crystals and employ SAW devices coated with chemical sensors for gas detection . We are calibrating the cascade impactor in our laboratory for future deployment for in - situ experiments to measure ozone . Experiments have been performed to characterize the QCM and SAW mass loading , saturation limits , mass frequency relationships , and sensitivity . The characteristics of mass loading , saturation limits , mass - frequency relationships , sensitivity , and the loss of ozone on different materials have been quantified .
An overview of the international " MIcrostructure Formation in CASTing of Technical Alloys " ( MICAST ) program is given . Directional solidification processing of metals and alloys is described , and why experiments conducted in the microgravity environment aboard the International Space Station ( ISS ) are expected to promote our understanding of this commercially relevant practice . Microstructural differences observed when comparing the aluminum - 7 wt% silicon alloys directionally solidified on Earth to those aboard the ISS are presented and discussed .
This slide presentation reviews the progress made in the design and development of the Ares V launch vehicle . Included in the presentation are views of the elements of the Ares V , the commonality of the Ares I and V , a chart that shows the progress made in the design of the launcher , description of the current activities around the design and preparation for the Ares V , and a slide describing the prospect of large payload volume and the flexibility that this gives to new space sciences .
Space launch vehicles incorporate upper - level wind profiles to determine wind effects on the vehicle and for a commit to launch decision . These assessments incorporate wind profiles measured hours prior to launch and may not represent the actual wind the vehicle will fly through . Uncertainty in the upper - level winds over the time period between the assessment and launch can be mitigated by a statistical analysis of wind change over time periods of interest using historical data from the launch range . Five sets of temporal wind pairs at various times ( .75 , 1.5 , 2 , 3 and 4 - hrs ) at the Eastern Range , Western Range and Wallops Flight Facility were developed for use in upper - level wind assessments . Database development procedures as well as statistical analysis of temporal wind variability at each launch range will be presented .
Mars sample return is a major scientific goal of the 2011 US National Research Council Decadal Survey for Planetary Science . Toward achievement of this goal , recent architecture studies have focused on several mission concept options for the 2018/2020 Mars launch opportunities . Mars orbiters play multiple roles in these architectures such as : relay , landing site identification / selection / certification , collection of on - going or new measurements to fill knowledge gaps , and in - orbit collection and transportation of samples from Mars to Earth . This paper reviews orbiter concepts that combine these roles and describes a novel family of relay orbits optimized for surface operations support . Additionally , these roles provide an intersection of objectives for long term NASA science , human exploration , technology development and international collaboration .
NASA 's Stennis Space Center ( SSC ) and Glenn Research Center ( GRC ) participate in the development of technologies for propulsion testing and propulsion applications in air and space transportation . Future transportation systems and the test facilities needed to develop and sustain them are becoming increasingly complex . Sensor technology is a fundamental pillar that makes possible development of complex systems that must operate in automatic mode ( closed loop systems ) , or even in assisted - autonomous mode ( highly self - sufficient systems such as planetary exploration spacecraft ) . Hence , a great deal of effort is dedicated to develop new sensors and related technologies to be used in research facilities , test facilities , and in vehicles and equipment . This paper describes sensor technologies being developed and in use at SSC and GRC , including new technologies in integrated health management involving sensors , components , processes , and vehicles .
A grid block transformation scheme which allows the input of grids in arbitrary reference frames , the use of mirror planes , and grids with relative velocities has been developed . A simple ice crystal and sand particle bouncing scheme has been included .. Added an SLD splashing model based on that developed by William Wright for the LEWICE 3.2.2 software . A new area based collection efficiency algorithm will be incorporated which calculates trajectories from inflow block boundaries to outflow block boundaries . This method will be used for calculating and passing collection efficiency data between blade rows for turbo - machinery calculations .
The proposed Small Solar Probe mission features a close approach to the sun with a perihelion of 4 radii .   Carbon molecules emitted from the spacecraft 's heat shield will become ionized   by electron impact and photoionization .   The newly created ions and electrons may generate electromagnetic and electrostatic plasma waves which are possible sources of interference with   in - situ plasma measurements .
This slide presentation reviews strategies for managing risk mitigation that occur with anomalies in on - orbit spacecraft . It reviews the risks associated with mission operations , a diagram of the method used to manage undesirable events that occur which is a closed loop fault analysis and until corrective action is successful . It also reviews the fish bone diagram which is used if greater detail is required and aids in eliminating possible failure factors .
Thermal Acoustic Oscillations ( TAO ) can occur in cryogenic systems and produce significant sources of heat . This source of heat can increase the boil off rate of cryogenic propellants in spacecraft storage tanks and reduce mission life . This paper discusses the causes of TAO , how it can be detected , what analyses can be done to predict it , and how to prevent it from occurring . The paper provides practical insight into what can aggravate instability , practical methods for mitigation , and when TAO does not occur . A real life example of a cryogenic system with an unexpected heat source is discussed , along with how TAO was confirmed and eliminated .
Viewgraphs on Advanced Life Support ( ALS ) Systems are presented . The topics include : 1 ) Fundamental Need for Advanced Life Support ; 2 ) ALS organization ; 3 ) Requirements and Rationale ; 4 ) Past Integrated tests ; 5 ) The need for improvements in life support systems ; 6 ) ALS approach to meet exploration goals ; 7 ) ALS Projects showing promise to meet exploration goals ; and 9 ) GRC involvement in ALS .
A review is provided of recent aerothermodynamic ground - test contributions by NASA Langley Research Center ( LaRC ) to the BOLT flight test program . Several test entries into the Langley Aerothermodynamic Laboratory 20 - Inch Mach 6 Air Tunnel are discussed . These entries were intended to support the development and design of flight hardware and instrumentation . Some trends and observations from these entries are provided . Also , a comparison of two different global heat transfer test techniques is included and discussed .
This slide presentation reports on the analysis of several years of Delft Object - oriented Radar Interferometric Software ( Doris ) data undertaken to estimate daily determination of satellite antenna phase center corrections . This was done on a satellite by satellite basis . For each DORIS satellite , we considered long - term time series of such individual estimations , looking for possible biases , discontinuities , trends or annual signals . The analysis compared DORIS to GPS estimates for common satellites ( Jason and TOPEX / Poseidon ) .
Probability of collision ( P(sub c ) ) estimates for Earth - orbiting satellites typically assume a temporally - isolated conjunction event . However , under certain conditions two objects may experience multiple high - risk close approach events over the course of hours or days . In these repeating conjunction cases , the P(sub c ) accumulates as each successive encounter occurs . The NASA Conjunction Assessment Risk Analysis team has updated its “ brute force Monte Carlo ” ( BFMC ) software to estimate such accumulating P(sub c ) values for repeating conjunctions . This study describes the updated BFMC algorithm and discusses the implications for conjunction risk assessment .
This paper describes the modeling and simulation of trapped granular media , within the context of the Granular Imager project . We describe the physics of trapped granular media in space , and the methodologies used to stably confine and shape such a medium using electromagnetic fields . The numerical models have also been validated with results in the literature , obtaining excellent agreement . The results of the numerical tests indicate that it is possible , with structural arrangements of rings and plates at different levels of electrostatic potential , to stably confine one or more charged particles , when driven by voltages that can be modulated in time and space .
The in - space manufacturing project at NASA Marshall Space Flight Center seeks to mature the manufacturing capabilities which will be needed on long duration , long endurance human spaceflight missions . The ability to manufacture materials and parts in space rather than launching them from earth has the potential to reduce logistics requirements and enhance crew safety . The International Space Station serves as a unique orbiting test bed for in - space manufacturing technology development for NASA and its commercial partners . This paper provides an overview of the projects currently in the in - space manufacturing technology portfolio and key technology development efforts in the past year .
The IGS analysis centers and user community in general need to be assured that the data centers archive a consistent set of files . Changes to the archives can occur because of the re - publishing of data , the transmission of historic data , and the resulting re - distribution ( or lack thereof ) of these data from data center to data center . To ensure the quality of the archives , a defined data flow and method of archive population needs to be established . This poster will diagram and review the current IGS data flow , discuss problems that have occurred , and provide recommendations for improvement .
The Near - Infrared Spectrometer ( NIRSpec ) places the most stringent demands upon its detectors of all James Webb Space Telescope ( JWST ) instruments . We present the scientific rationale for challenging requirements including noise < or=6 e- rms per exposure . In concert , we discuss laboratory test results that are informing the design of NIRSpec 's detector system and operational concept .
NASA 's current mission planning system is based on point design , two - dimensional display , spread sheets , and report technology . This technology does not enable engineers to analyze the results of parametric studies of missions plans . This technology will not support the increased observational complexity and data volume of missions like Cassini , Mars Reconnaissance Orbiter ( MRO ) , Mars Science Laboratory ( MSL ) , and Mars Sample Return ( MSR ) . The goal of the 3D - ROMPS task has been to establish a set of operational mission planning and analysis tools in the Image Processing Laboratory ( IPL ) Mission Support Area ( MSA ) that will respond to engineering requirements for planning future Solar System Exploration ( SSE ) missions using a three - dimensional display .
In the Propellant Development and Characterization Subcommittee ( PDCS ) meeting , topics included : the analysis , characterization , and processing of propellants and propellant ingredients ; chemical reactivity ; liquid propellants ; test methods ; rheology ; surveillance and aging ; and process engineering . In the Safety and Environmental Protection Subcommittee ( S&EPS ) meeting , topics covered included : hydrazine propellant vapor detection methods ; toxicity of propellants and propellants ; explosives safety ; atmospheric modeling and risk assessment of toxic releases ; reclamation , disposal , and demilitarization methods ; and remediation of explosives or propellant contaminated sites .
As assembly of the International Space Station ( ISS ) proceeds , predictive techniques are used to determine the best approach for handling a variety of cabin air quality challenges . These techniques use equipment offgassing data collected from each ISS module before flight to characterize the trace chemical contaminant load . Combined with crew metabolic loads , these data serve as input to a predictive model for assessing the capability of the onboard atmosphere revitalization systems to handle the overall trace contaminant load as station assembly progresses . The techniques for predicting in - flight air quality are summarized along with results from early ISS mission analyses . Results from groundbased analyses of in - flight air quality samples are compared to the predictions to demonstrate the technique 's relative conservatism .
This PowerPoint presentation defines technology transfer and discusses spin - out / off pros / cons involving whether to include a project within NASA or to contract outside NASA . The author discusses what would making the technology transfer happen by suggesting to evaluate NASA technologies / needs and find partners with ability to do business with NASA . The presentation concludes with recent Goddard successes .
Following successful application of Coulomb - Mohr and interaction equations for evaluation of safety margins in Albemet 162 brazed joints , two additional base metal / filler metal systems were investigated . Specimens consisting of stainless steel brazed with silver - base filler metal and titanium brazed with 1100 Al alloy were tested to failure under combined action of tensile , shear , bending and torsion loads . Finite Element Analysis ( FEA ) , hand calculations and digital image comparison ( DIC ) techniques were used to estimate failure stresses and construct Failure Assessment Diagrams ( FAD ) . This study confirms that interaction equation R(sub sigma ) + R(sub tau ) = 1 , where R(sub sigma ) and R(sub t u ) are normal and shear stress ratios , can be used as conservative lower bound estimate of the failure criterion in stainless steel and titanium brazed joints .
Several unintentional hypergolic fluid related spills , fires , and explosions from the Apollo Program , the Space Shuttle Program , the Titan Program , and a few others have occurred over the past several decades . Spill sites include the following government facilities : Kennedy Space Center ( KSC ) , Johnson Space Center ( JSC ) , White Sands Test Facility ( WSTF ) , Vandenberg Air Force Base ( VAFB ) , Cape Canaveral Air Force Station ( CCAFS ) , Edwards Air Force Base ( EAFB ) , Little Rock AFB , and McConnell AFB . Until now , the only method of capturing the lessons learned from these incidents has been " word of mouth " or by studying each individual incident report . Through studying several dozen of these incidents , certain root cause themes are apparent . Scrutinizing these themes could prove to be highly beneficial to future hypergolic system test , checkout , and operational use .
This viewgraph presentation includes : 1 ) an introduction to RBC Technologies ; 2 ) Rechargeable Zinc Alkaline ( RZA(tm ) ) Systems which include MnO2 / Zn , Ni / Zn , Ag / Zn , and Zn / Air ; and 3 ) RZA Silver / Zinc Battery Developments . Conclusions include the following : 1)Issues with long term wet life and cycle life of the silver / zinc battery system are being overcome through the use of new anode formulations and separator designs ; 2 ) Performance may exceed 200 cycles to 80 % of initial capacity and ultimate wet - life of > 36 months ; and 3 ) Rechargeable silver / zinc batteries available in prismatic and cylindrical formats may provide a high energy , high power alternative to lithium - ion in military / aerospace applications .