silkski/ENERAD huggingface dataset:
A number of specific benefits that fit within the hallmarks of effective development are realized with implementation of model - based approaches to systems and assurance . Model Based Systems Engineering ( MBSE ) enabled by standardized modeling languages ( e.g. , SysML ® ) is at the core . These benefits in the context of spaceflight system challenges can include : Improved management of complex development , Reduced risk in the development process , Improved cost management , Improved design decisions . With appropriate modeling techniques the assurance community can improve early oversight and insight into project development . NASA has shown the basic constructs of SysML in an MBSE environment offer several key advantages , within a Model Based Mission Assurance ( MBMA ) initiative .
The Meridiani Planum hematite deposit has been designated as the prime landing site for Opportunity , one of the two Mars Exploration Rover ( MER ) spacecraft . Iron oxide and hydroxide minerals , including hematite , can mineralize and preserve microfossils and physical biomarkers . Previous research by ourselves and others , summarized below , has demonstrated such mineralization in a variety of terrestrial hematite deposits . Our most recent study has focused on the mineralization of microorganisms in rock varnish , the iron- and manganese - rich layers that coat rocks in many arid environments .
Woven Thermal Protection Systems ( WTPS ) is a relatively new program funded by the Office of the Chief Technologist ( OCT ) . The WTPS approach to producing TPS architectures uses precisely engineered 3 - D weaving techniques that allow tailoring material characteristics needed to meet specific mission requirements . A series of mechanical tests were performed to evaluate performance of different weave types , and get a better understanding of failure modes expected in these three - dimensional architectures . These properties will aid in material down selection and guide selection of the appropriate WTPS for a potential mission .
The spectral reflectance of oceanic whitecaps in the visible and near infrared was investigated using high - altitude , 20 m resolution Airborne Visible / Infrared Imaging Spectrometer ( AVIRIS ) measurements off the Southern California coast . The whitecap effect on surface reflectance was expressed as a function of the difference between the reflectance of pixels contaminated by whitecaps and of adjacent pixels free of whitecaps . Whitecap reflectance was found to decrease substantially in the near infrared , by about 40 % at 850 nm and 80 % at 1,600 nm , in agreement with previous measurements in the coastal zone and the open ocean . The spectral dependence of whitecap reflectance appears to be fairly independent of environmental conditions , making it easy to take into account the resulting and significant effects in ocean color and aerosol remote sensing algorithms .
An algorithm has been developed that solves the semiconductor Maxwell - Bloch equations , without making the standard slowly - varying envelope ( SVEA ) and rotating - wave ( RWA ) approximations . It is applied to study the propagation of ultrashort pulses in semiconductor materials . The results include many - body effects due to the Coulomb interaction among the charge carriers as well as the nonlinear effects resulting from spectral hole - burning .
Anomalously fractionated isotopic material is found in many primitive Solar System objects , such as meteorites and comets . It is thought , in some cases , to trace interstellar matter that was incorporated into the Solar Nebula without undergoing significant processing . We will review observations and models of the nitrogen , oxygen , and carbon fractionation chemistry in dense molecular clouds . The range of fractionation ratios expected in different interstellar molecules will be discussed and compared to the ratios measured in molecular clouds , comets and meteoritic material . These studies make several predictions that can be tested by high - resolution molecular line observations with ALMA ( Atacama Large Millimeter Array ) .
The current Geostationary Operational Environmental Satellites ( GOES ) are equipped to make cloud top measurements only .   In contrast , a millimeter - wave radar allows 3 - D measurements of   precipitation associated with hurricanes and other convective systems .   It also provides important inputs to numerical weather prediction models for improving the accuracy in weather   nowcasting and forecasting .
We have reviewed the literature on composition of young stars , both hot and cool , as well as older solar - type stars . We find that all these classes of stars have lower abundances of the heavy elements ( specifically C , N , O , Mg , Si , and Fe ) than the sun . Therefore studies of interstellar depletions in which the solar composition is used as the reference standard are probably in error , tending to overestimate the total quantities of these elements , hence the depletions . We have revised the depletion estimates , using stellar abundances as the reference standard and making use of recent IS gas - phase abundance measurements . As a result of our revised depletions , we can place new and stringent constraints on several published models for the interstellar dust .
A large test article was recently designed , analyzed , fabricated , and successfully tested up to the representative design ultimate loads to demonstrate that stiffened composite panels with through - the - thickness reinforcement are a viable option for the next generation large transport category aircraft , including non - conventional configurations such as the hybrid wing body . This paper focuses on finite element analysis and test data correlation of the hybrid wing body center section test article under mechanical , pressure and combined load conditions . Good agreement between predictive nonlinear finite element analysis and test data is found . Results indicate that a geometrically nonlinear analysis is needed to accurately capture the behavior of the non - circular pressurized and highly - stressed structure when the design approach permits local buckling .
The light curves and spectra of two ultra soft X - ray sources are presented . The sources , WGAJ 1047.1 + 6335 and WGAJ 1802.1 + 1804 were discovered during a search using the Rosat position sensitive proportional counter ( PSPC ) . The X - ray spectra of both objects show an unusually strong black body component with respect to the harder bremsstrahlung component . Based on the optical observations and on the analysis of the X - ray data , the two objects are identified with new AM Her type cataclysmic variables .
This presentation will explain Windchill soft - types - what they are , how they work , and how to construct custom ones , configured specifically for your system . The process and particulars of creating and implementing a WTDocument soft - type will be discussed , and the interaction between soft - types and Windchill objects will be shown .
The Microgravity Science Division identifies four priority ratings for microgravity research and technology issues : 1 ) Critical ; 2 ) Severely Limiting ; 3 ) Enhancements ; 4 ) Communication . Reduced gravity instabilities are critical , while severely limiting issues include phase separation , phase change , and flow through components . Enhancements are listed for passive phase separation and phase change . This viewgraph presentation also classifies microgravity issues as spaceflight , ground - based , or other for the time periods 2003 - 2008 , 2009 - 2015 , and beyond .
Supernova 1987 A in the Large Magellanic Cloud is one of the most intensively studied objects in the universe and a Rosetta Stone for understanding the explosions of massive stars . Now almost 25 years old , SN 1987 A is a very young supernova remnant , a phase previously unobserved in any other supernova . In this talk I will discuss recent observations from the far ultraviolet to the far - infrared with HST , the VLT , and the Herschel Space Observatory . These data reveal new insights into the composition , geometry , and heating of the explosion debris , the shock interaction with circumstellar material , and dust in the SN 1987 A system .
An integrally stiffened graphite / epoxy composite rotorcraft structure is evaluated via computational simulation . A computer code that scales up constituent micromechanics level material properties to the structure level and accounts for all possible failure modes is used for the simulation of composite degradation under loading . Damage initiation , growth , accumulation , and propagation to fracture are included in the simulation . Design implications with regard to defect and damage tolerance of integrally stiffened composite structures are examined . A procedure is outlined regarding the use of this type of information for setting quality acceptance criteria , design allowables , damage tolerance , and retirement - for - cause criteria .
By using power spectrum and standard FFT time series analysis , the Hard X - ray burst during solar cycle -22 were studied . This data of Hard X - ray burst spectrometer ( HXRBS ) on the solar maximum mission from Launch and February 14 , 1980 , through re - entry on December 2 , 1989 , by NASA artificial satellite . The results indicate that there are short and intermediate solar periodicities . Also it is found that there is a relation between the short periodicities ( few minutes ) with similar periodicities in solar radio emissions and in good agreement with the theoretical mode of solar oscillations .
A set of Penrose diagrams is constructed in order to examine the large - scale causal structure of black holes with dynamic horizons . Coordinate dependencies of significant features , such as the event horizon and radial mass scale , are demonstrated on the diagrams . Unlike in static Schwarzschild geometries , the radial mass scale is clearly seen to differ from the horizon . Trajectories for photons near the horizon are briefly discussed .
Compressive Sensing is an emerging technology for data compression and simultaneous data acquisition . This is an enabling technique for significant reduction in data bandwidth , and transmission power and hence , can greatly benefit spaceflight instruments . We apply this process to detect exoplanets via gravitational microlensing . We experiment with various impact parameters that describe microlensing curves to determine the effectiveness and uncertainty caused by Compressive Sensing . Finally , we describe implications for spaceflight missions .
Joe Kosmo shared some final words and advice for his teammates in the Spacesuit and Crew Survival Systems Branch ( EC5 ) and the Crew and Thermal Systems Division ( CTSD ( EC ) ) upon his retirement . He knew nothing about spacesuits when he started working for NASA in 1961 , but neither did anyone else . He summed up the best lessons learned during his 50 years of developing U.S. spacesuits and encouraged the next generation s space industry workers to challenge what they hear and decide what is right . Topics include and oral history of early NASA manned flights by Richard S. Johnston , U.S. human spaceflight chronology , a history of advanced EVA project funding , and a discussion of NASA 's innovative spirit .
This document outlines potential joint scientific studies involving the THEMIS and RBSP missions as a function of mission phase from the commissioning of RBSP in August 2012 through the end of its prime mission in the summer of 2014 . It describes consensus recommendations for interspace craft separation , fast survey and burst mode strategies for THEMIS that will enable the two missions to achieve and exceed their common objectives . An appendix describes the need for careful intercalibration of THEMIS and RBSP particle observations .
The first findings from a year of WMAP satellite operations provide a detailed full sky map of the cosmic microwave background radiation . The observed temperature anisotropy , combined with the associated polarization information , encodes a wealth of cosmological information . The results have implications for the history , content , and evolution of the universe , and its large scale properties . These and other aspects of the mission will be discussed .
The paper presents three benchmark cases for verification of Reynolds - averaged   Navier - Stokes   solvers .   The verification   studies focus   on a   one - equation    Spalart - Allmaras model , SA-[neg]-QCR2000 ,    that uses a    version    of quadratic constitutive relations . The   benchmark cases are   a   two - dimensional subsonic   flow   around   a Joukowski airfoil , a three - dimensional supersonic   flow through a square duct , and a three - dimensional flow over a wing - fuselage configuration . The turbulence - model formulation , geometry , flow conditions , grids , and the expected output   are   described in detail .   Reference   solutions   computed   by several established codes are shown
A series of lectures will be given to acquaint the amateur astronomer with historical , present and future methods of observation in high - energy astrophysics . These will begin with the basic principles of how photons of high energy are detected and their energy measured . The detectors and data distribution methods will be described . Finally , a comprehensive description of the experiments and missions in high - energy astrophysics will be reviewed .
NASA 's planned SMAP mission will utilize a radar operating in a band centered on 1.26 GHz and a co - observing radiometer operating at 1.41 GHz to measure surface soil moisture . Both the radar and radiometer sub - systems are susceptible to radio frequency interference ( RFI ) . Any significant impact of such interference requires mitigation in order to avoid degradation in the SMAP science products . Studies of RFT detection and mitigation methods for both the radar and radiometer are continuing in order to assess the risk to mission products and to refine the performance achieved .
The Lasers and Electro - Optics Branch at Goddard Space Flight Center has been tasked with building the Lasers for the Global Ecosystems Dynamics Investigation ( GEDI ) Lidar Mission , to be installed on the Japanese Experiment Module ( JEM ) on the International Space Station ( ISS ) . GEDI will use three NASA - developed lasers , each coupled with a Beam Dithering Unit ( BDU ) to produce three sets of staggered footprints on the Earth 's surface to accurately measure global biomass . We will report on the design , assembly progress , test results , and delivery process of this laser system .
NASA , DOD ( Department of Defense ) , and DOE ( Department of Energy ) are currently looking to the NASA UEET ( Ultra - Efficient Engine Technology ) Program to develop ceramic matrix composites ( CMC ) for hot - section components in advanced power and propulsion systems . Success will greatly depend on developing ceramic fibers with a variety of key thermostructural properties , in particular , high as - produced tensile strength and retention of a large fraction of this strength for long times under the anticipated CMC service conditions . Current UEET approaches center on selecting the optimum fiber type from commercially available fibers since the costs for development of advanced fibers are high and the markets for high - temperature CMC have yet to be established .
Various methods of providing runway information in the cockpit during the take - off and landing roll have been proposed . The most reliable method has been to use runway distance markers when visible . Flight tests were used to evaluate the feasibility of using weak radio - active sources to trigger a runway distance counter in the cockpit . The results of these tests indicate that a weak radioactive source would provide a reliable signal by which this indicator could be operated .
Computational simulations using the Launch Ascent and Vehicle Aerodynamics ( LAVA ) framework are presented for the First AIAA Sonic Boom Prediction Workshop test cases . The framework is utilized with both structured overset and unstructured meshing approaches . The three workshop test cases include an axisymmetric body , a Delta Wing - Body model , and a complete low - boom supersonic transport concept . Solution sensitivity to mesh type and sizing , and several numerical convective flux discretization choices are presented and discussed . Favorable comparison between the computational simulations and experimental data of nearand mid - field pressure signatures were obtained .
A sample mission sequence is defined for a low earth orbit demonstration of Precision Formation Flying ( PFF ) . Various guidance navigation and control strategies are discussed for use in the PFF experiment phases . A sample PFF experiment is implemented and tested in a realistic Hardware - in - the - Loop ( HWIL ) simulation using the Formation Flying Test Bed ( FFTB ) at NASA 's Goddard Space Flight Center .
Arc - jet testing is a fundamental tool in the screening of thermal protection systems under atmospheric entry conditions . In this work , high - fidelity computational fluid dynamics simulations coupled with machine learning methods for the Hypersonic Materials Environmental Test System arc - jet facility have been carried out . This effort improves the MEDLI-2 data reconstruction fidelity by understanding the impact of the NuSil coating over the PICA thermocouple plugs . Thermochemical non - equilibrium models are employed to simulate the flows inside the arc - jet nozzle and chamber and machine learning techniques are used to calibrate the arc - jet inflow conditions . The material response is simulated with the recession and in - depth numerical results compared to experimental measurements .
We report recent advancements of the agglomerated multigrid methodology for complex flow simulations on fully unstructured grids . An agglomerated multigrid solver is applied to a wide range of test problems from simple two - dimensional geometries to realistic three- dimensional configurations . The solver is evaluated against a single - grid solver and , in some cases , against a structured - grid multigrid solver . Grid and solver issues are identified and overcome , leading to significant improvements over single - grid solvers .
Upon completion of the first Space Launch System flight , NASA personnel will begin post - flight analyses . Telemetry from across the vehicle will be combined with external radar tracking and environmental observation data in order to close validation criteria and generate a best estimated trajectory ( BET ) .   This paper will describe the approach taken by the SLS team to integrate flight data from multiple flights sources into BET , pre - flight simulation and testing results , primary sources of uncertainty , and path towards processing flight results . This paper also includes a brief description of algorithms and approaches to estimate as - flown vehicle parameters such as booster specific impulse , booster ( and core ) thrust multipliers and dry mass .
Niobium antimony telluride , Nb3Sbx , Te7 - x , was synthesized and tested for thermoelectric properties in the Thermoelectrics group at the Jet Propulsion Laboratory . The forty atoms per   unit cell of Nb3Sb2Te5 and its varied mixture of atoms yield acomplicated structure , suggesting that Nb3Sb2Te5 and related compounds may exhibit low thermal conductivity and hence a   higher ZT value . Nb3SbxTe7 - x , compounds were synthesized and subsequently analyzed for their Seebeck voltage , heat conduction , and electrical resistivity . Results indicate that   Nb3Sb2Te5 is a heavily doped semiconductor whose thermoelectric properties are compromised by compensating n - type and p - type carriers . Attempts to dope in favor of either carrier by   varying the Sb : Te ratio yielded samples containing secondary metallic phases that dominated the transport properties of the resulting compounds .
The 50,000 year old , 1.8 km diameter Lonar crater is located in Maharashtra , India . This relatively small crater is of particular interest because of its unique morphological and mineralogical properties , which make it a valid analogue for similar craters on the surface of Mars . We show that even in this relatively small crater , substantial hydrothermal alteration of shocked breccias in the floor of the crater has occurred , probably due to the thermal effects of the impact event . The 38 my old , 28 km diameter , Mistastin crater contains an 80 m thick impact melt sheet . We have also documented the presence of alteration phases in the material from this larger crater .
The Space Shuttle Main Engine ( SSME ) electrical harness and cable system consists of the various interconnecting devices necessary for operation of complex rocket engine functions . Thirty seven harnesses incorporate unique connectors , backshell adapters , conductors , insulation , shielding , and physical barriers for a long maintenance - free life while providing the means to satisfy performance requirements and to mitigate adverse environmental influences . The objective of this paper is to provide a description of the SSME electrical harness and cable designs as well as the development history and lessons learned .
High - power plasma thrusters that utilize molten metallic propellants ( e.g. , the Lithium Lorentz Force Accelerator ) are currently being investigated as a primary propulsion option for in - space nuclear - electric systems . A critical component of the thruster is the propellant feed system , which must reliably and accurately pump liquid metal into the thruster discharge chamber . We present design details and calibration results for a compact liquid metal propellant feed system that contains no moving parts , for use in laboratory testing of plasma thrusters . Feed line pressure is maintained using an MHD flow coupler , and the flow rate is monitored using a simple voltage divider , which is submerged in the propellant reservoir . Results for lithium and gallium propellants show capability to meter propellant at flow rates up to 10 + /- 0.1 mg / s.
The destruction rates of a perfluoropolyether ( PFPE ) lubricant , Krytox 143AC(TradeMark ) , subjected to rolling contact with 440C steel in a spiral orbit tribometer at room temperature have been evaluated as a function of test environment . The rates in ultrahigh vacuum , 0.21 3 kPa ( 1.6 Torr ) oxygen and one atmosphere of dry nitrogen were about the same . Water vapor in the test environment - a few ppm in one atmosphere of nitrogen - reduced the destruction rate by up to an order of magnitude . A similar effect of water vapor was found for the destruction rate of Pennzane(Registered TradeMark ) 2001A , an unformulated multiply alkylated cyclopentane ( MAC ) hydrocarbon oil .
To date the LEO battery has completed 5000 nominal cycles . The EODV is trending down by 50mV per 1000 cycles . To date the GEO battery has completed 2 nominal shadow periods and currently in sunlight period . Batteries testing after one year looks encouraging for aerospace application . There are no discrepancies between the current data and extensive testing conducted at Saft over the past 5 years .
This paper presents a status report on the progress of the Meteorological Satellite Program . In this review , I shall try to emphasize primarily the accomplishments since May 1961 when a report on the program was given to the First National Conference on Peaceful Uses of Space in Tulsa , Oklahoma . It is now one year later , and it is fitting that we stop and take stock of what we have been doing and where we are heading .