silkski/ENERAD huggingface dataset:
The surface of the Moon is covered in regolith , which is NOT soil ! The regolith is shattered igneous rock plus glass . The particles are unsorted , unweathered and not abraided . Modeling of the regolith at the level of individual particles will be very problematic . Modeling of the regolith , if successful for one area , will be successful for most other areas if variation in particle size is addressed .
InSight is a proposed Discovery mission which will deliver a lander containing geophysical instrumentation , including a heat flow probe and a seismometer package , to Mars . The aim of this mission is to perform , for the first time , an in - situ investigation of the interior of a truly Earth- like planet other than our own , with the goal of understanding the formation and evolution of terrestrial planets through investigation of the interior structure and processes of Mars .
Ares V is the heavy lift vehicle NASA is designing for lunar and other space missions . It has significantly more lift capability than the Saturn V vehicle used for the Apollo missions to the moon . Ares V is powered by two recoverable 5.5 segment solid rocket boosters and six RS-68B engines on the core stage . The upper stage , designated as the Earth Departure Stage , is powered by a single J-2X engine . This paper provides an overview of the Ares V vehicle and the RS-68B engine , an upgrade to the Pratt & Whitney Rocketdyne RS-68 engine developed for the Delta IV vehicle .
Three Geostationary Operational Environmental Satellite ( GOES ) R transponders ( services ) required analysis and measurements to develop an accurate link budget . These are a ) Search and Rescue transponder which suffers from power robbing due to thermal uplink noise , b ) the Data Collection Platform Report which suffers from degradation due to NPR ( Noise Power Ratio ) , and c ) GOES Rebroadcast transponder which uses a dual circular downlink L band for which there was no depolarization data . The first two services required development of extended link budget to analytically calculate the impact of these degradations which are shown to have a significant impact on the link budget . The third service required measurements of atmospheric L band CP depolarization as there were no known previous measurements and results are reported her
We have used laser - induced fluorescence ( LIF ) to carry out a detailed , systematic survey of the properties of the free stream of the 20 Megawatt Aerodynamic Heating Facility at NASA / Ames Research Center . In both air and nitrogen flows we have measured the atomic nitrogen absolute number density and flow velocity at each operating condition . In air flows we have also measured the atomic oxygen absolute number density and rotational / translational temperature at each operating condition . These results have been used to provide , for the first time , a direct , nonintrusive measurement of the enthalpy on the centerline of the flow . In addition , the observed arc jet properties can be used to test and improve computer simulations of the arc jet flow which include detailed chemical rate processes ( especially nitrogen atom recombination ) taking place during the supersonic expansion .
This paper reports on the navigation activities during Rosetta s Mars swing - by . It covers the Mars approach phase starting after a deterministic deep - space maneuver in September 2006 , the swing - by proper on 25 February 2007 , and ends with another deterministic deep - space maneuver in April 2007 which was also foreseen to compensate any navigation error . Emphasis is put on the orbit determination and prediction set - up and the evolution of the targeting estimates in the B - plane and their adjustments by trajectory correction maneuvers .
A series of total ionizing dose ( TID ) measurements were performed on commercial hard drives to explore the possible uses of the devices for the high radiation mission , and to help the understanding of the reliability of current hard drive technology . Three different models from three major manufacturers were tested with the aid of a commercial hard drive test system .
Even though a great deal of theoretical and experimental information has been obtained in recent years on the flow over simple shapes in hypersonic flow a great deal of confusion still exists on how to interpret and extrapolate the results obtained . This paper offers information recently obtained at Langley at Mach numbers ranging from 7 to 21 encompassing both work in air and helium on shapes ranging from rods to delta wings . The results indicate that in most cases methods for making useful estimates of pressure are in hand for simple shapes . However , three - dimensional effects and the interaction between the components considerably complicates the flow fields over delta wings at low angles of attack .
To continue to develop a innovative and successful workforce for planetary scientists , it is critical to foster an interdisciplinary , diverse , equitable , inclusive , and accessible environment across the field , especially for members of the LGBTQ+ community . Note :    Members    of    the    community    utilize    various acronyms to describe a person ’s sexual orientation or gender identity , but for the purposes of this paper , we will use the acronym LGBTQ+ to include any and all members of this marginalized group . LGBTQ+ stands for Lesbian , Gay , Bisexual , Transgender , Queer , and the “ + ” signifies the importance that one acronym can not possibly capture everyone 's experience of their gender identity , expression , and/or sexual orientation .
Relativistic electrons in the magnetosphere are both energized and lost via their interaction with plasma waves such as whister chorus , plasmaspheric hiss and EMIC waves . These waves are usually localized in different regions of the magnetosphere as well as being located either inside or outside the plasmapause . We study relativistic electron losses in the outer radiation belts by characterizing decay times scales at low and high altitudes and their relationship to microbursts . We use data collected by SAMPEX , a low Earth orbiting spacecraft in a highly inclined polar orbit and the HEO spacecraft in a high altitude Molniya orbit . The sensors onboard these spacecraft measure electrons of energies > 0.6 MeV , > 1 MeV , > 3 MeV , 2 - 6 MeV , 3 - 16 MeV. High time resolution data enable identifying and characterizing electron microbursts observed at low altitudes .
This paper describes new software simulation code for predicting single event upset data from measured heavy ion data , using methods , code , and algorithms already reported in the open literature . The measured data that is used to compare against the results of this new simulation code has also been reported in the open literature ( R. Koga , et al ) . The new code is not provided as part of this paper , only the methodology used in generating the code . This paper presents results of basic research , not design - to information , and is representative of other papers reported in the open literature ( see paper references ) . Therefore , the content of this paper is suitable for being made publicly available at the IEEE conference and the resulting IEEE journal .
This paper groups and summarizes the salient points and findings from two AIAA conference panels targeted at defining the direction , with associated key issues and recommendations , for the integration of experimental ground testing and computational methods . Each panel session utilized rapporteurs to capture comments from both the panel members and the audience . Additionally , a virtual panel of several experts were consulted between the two sessions and their comments were also captured . The information is organized into three time - based groupings , as well as by subject area . These panel sessions were designed to provide guidance to both researchers / developers and experimental / computational service providers in defining the future of ground testing , which will be inextricably integrated with the advancement of computational tools .
The Laser Engineered Net Shaping ( LENS(Trademark ) ) process is a new technology to fabricate three - dimensional metallic components directly from CAD solid models . It directly fabricates metal hardware by injecting the metal powder of choice into the focal point of a 700W Nd : Yag laser as it traces the perimeter and fills of a part . The Rapid Prototype Laboratory at Marshall Space Flight Center is currently operating a OPTOMEC 750 LENS machine in evaluation experiments involving integration of this technology into various manufacturing processes associated with aerospace applications . This paper will cover our research finding about properties of samples created from Inconel 718 & SS316 using this process versus the same materials in cast & wrought conditions .
Studies on Soviet and American astronauts have demonstrated that red blood cell production is altered in response to low gravity ( g ) environment . This is associated with changes in individual red cells including increased mean cell volume and altered membrane deformability . During long orbital missions , there is a tendency for the red cell mass deficit to be at least partly corrected although the cell shape anomalies are not . Data currently available suggest that the observed decrease in red cell mass is the result of sudden suppression of erythropoieses and that the recovery trend observed during long missions reflects re - establishment of erythropoietic homeostasis at a " set point " for the red cell mass that is slightly below the normal level at 1 g.
The operation of a coherent Doppler lidar , developed by NASA for missions to planetary bodies , is analyzed and its projected performance is described . The lidar transmits three laser beams at different but fixed directions and measures line - of - sight range and velocity along each beam . The three line - of - sight measurements are then combined in order to determine the three components of the vehicle velocity vector and its altitude relative to the ground . Operating from over five kilometers altitude , the NDL provides velocity and range data with a few cm / sec and a few meters precision , respectively , depending on the vehicle dynamics . This paper explains the sources of measurement error and analyzes the impact of vehicle dynamics on the lidar performance .
A new system of two photometers was built to observe the Sun at 3 and 7 THz from space , named SOLART . It has been flown coupled to U.C. Berkeley GRIPS experiment on a NASA stratospheric balloon flight over Antarctica , 19 - 30 January 2016 . The mission was successfully accomplished . We describe the system performance , solar brightness determination and the first THz impulsive burst detected .
Dynamic spacing human factors deals with the following human factors issues : define controller limits to incorporating dynamic changes in separation standards ; identify timing , planning , and coordination strategies ; and consider consistency with current practices , policies , and regulations . The AVOSS technologies will make it possible to reduce separation standards in the terminal area under certain meteorological conditions . This paper contains the following sections : Dynamic space human factors overview , Preliminary tests , and current research status & plans .
Objectives : Demonstrate control of a dynamically similar , integrated Ares I / Orion , using Ares I relevant ascent control algorithms . Perform an in - flight separation / staging event between a Ares I - similar First Stage and a representative Upper Stage . Demonstrate assembly and recovery of a new Ares I - like First Stage element at KSC . Demonstrate First Stage separation sequencing , and quantify First Stage atmospheric entry dynamics , and parachute performance . Characterize magnitude of integrated vehicle roll torque throughout First Stage flight .
The DC electrical behavior of n - type 4H - SiC resistors used for realizing 500C durable integrated circuits ( ICs ) is studied as a function of substrate bias and temperature . Improved fidelity electrical simulation is described using SPICE NMOS model to simulate resistor substrate body bias effect that is absent from the SPICE semiconductor resistor model .
We investigated whether Repetition Blindness ( RB ) in processing RSVP strings depends critically on memory demands . When all items in the sequence had to be reported , strong RB was found . When only the 2 critical items ( cued by color ) had to be reported , no RB was found . Preliminary results show that imposing a separate memory load , while reporting only the critical items , also produces little RB . Implications for the processing locus of RB will be discussed .
Market forces are driving industry to reproduce product cycle time ( the time required to conceive , design , build , test , validate and deliver a product ) . Application of existing tools in new areas can reduce the time required to design a new product and increase the confidence of acceptable test results later in the expensive testing and validation phase . Finite element methods , computational fluid dynamics codes and sharing of CAD datasets when applied to the design of engine externals can provide methods for product improvement and expedited delivery to the customer .
Silicate inclusions in nine known IIE irons show diversity in mineralogy , and Colomera , Kodaikanal , Elga and Miles contain alkali - rich silicate inclusions . Bogard et al . showed evidence of a complex parent body evolution for IIE irons based on Ar-39 - Ar-40 ages . Colomera contained a sanidine - rich surface inclusion and the K - enrichment trends in the Na - rich inclusions are different from those of other IIEs . To elucidate the origin of K - rich materials , we studied the mineralogy and Ar - Ar age of silicate inclusions from the Tarahumara IIE iron meteorite .
This paper describes a videogrammetric technique for determining aerodynamic loads based on optical elastic deformation measurements . The data reduction methods are developed to extract the normal force and pitching moment from beam deformation data . The axial force is obtained by measuring the axial translational motion of a movable shaft in a spring / bearing device . Proof - of - concept calibration experiments are conducted to assess the accuracy of this optical technique .
The Mars Premier mission that was to be flown in 2007 by CNES in cooperation with NASA / JPL included a rendezvous experiment to be performed in Mars orbit to validate key technologies   applicable to a Sample Return mission .   The experiment goal was to demonstrate the capability to detect and track a sample canister at long range and validate terminal rendezvous   strategies including a capture .
The Mars Science Laboratory developed the WorkStation TestSet ( WSTS ) to support flight software development . The WSTS is the non - real - time flight avionics simulator that is designed to be completely software - based and run on a workstation class Linux PC . This provides flight software developers with their own virtual avionics testbed and allows device - level and functional software testing when hardware testbeds are either not yet available or have limited availability . The WSTS has successfully off - loaded many flight software development activities from the project testbeds . At the writing of this paper , the WSTS has averaged an order of magnitude more usage than the project 's hardware testbeds .
Aristarchus plateau ( ~25 N , 40 W ) is a volcanologically diverse region containing sinuous rilles , volcanic depressions , mare material of various ages - including a candidate for the youngest mare unit on the lunar surface - pyroclastic deposits , and material of possible highland origin [ 1 - 5 ] . Here , we present preliminary mapping of a 13deg x 10deg area around Aristarchus plateau [ 6 ] . Interpretations of the region s volcanic evolution have implications for the global history of lunar volcanism , the crustal and mantle development of the Moon , and may ultimately help support successful lunar exploration [ 7 ] .
The HPC Challenge ( HPCC ) benchmark suite and the Intel MPI Benchmark ( IMB ) are used to compare and evaluate the combined performance of processor , memory subsystem and interconnect fabric of five leading supercomputers - SGI Altix BX2 , Cray XI , Cray Opteron Cluster , Dell Xeon cluster , and NEC SX-8 . These five systems use five different networks ( SGI NUMALINK4 , Cray network , Myrinet , InfiniBand , and NEC IXS ) . The complete set of HPCC benchmarks are run on each of these systems . Additionally , we present Intel MPI Benchmarks ( IMB ) results to study the performance of 11 MPI communication functions on these systems .
The concept of ' phase heritage ' ( e.g. , Timms et al . , 2017a ) involves microstructural recognition of the former presence of a phase that has since transformed to another via evidence encoded in crystallographic orientations . Phase heritage relies on the phenomenon that newly grown ( daughter ) phases nucleate with particular crystallographic orientation relationships with the preceding ( parent ) phase . This phenomenon is common for displacive ( i.e. , shear or martensitic ) transformations , well documented in the metals and ceramics literature , but is relatively uncommon in geosciences . This presentation outlines the concepts behind this approach , showcases results from software for automated analysis of EBSD data , and illustrates examples of polymorphic and dissociation phase transformations in the ZrSiO4 - ZrO2 - SiO2 system , which has particularly useful applications for ' extreme thermobarometry ' in impact environments ( Timms et al . , 2017a ) .
This paper describes the architecture and implementation of a distributed launch and ascent simulation of NASA 's Orion spacecraft and Ares I launch vehicle . This simulation is one segment of the Distributed Space Exploration Simulation ( DSES ) Project . The DSES project is a research and development collaboration between NASA centers which investigates technologies and processes for distributed simulation of complex space systems in support of NASA 's Exploration Initiative . DSES is developing an integrated end - to - end simulation capability to support NASA development and deployment of new exploration spacecraft and missions . This paper describes the first in a collection of simulation capabilities that DSES will support .
Highly sensitive , high‐mass resolution mass spectrometry is an important in situ tool for the study of solar system bodies . In this talk we detail the science objectives , develop the rationale for the measurement requirements , and describe potential instrument / mission methodologies for studying the formation , evolution , and habitability of the Galilean satellites . We emphasize our studies of Ganymede and Europa as described in our instrument proposals for the recently selected JUICE mission and the proposed Europa Clipper mission .
An exploratory effort between NASA - Marshall Space Flight Center ( MSFC ) and SpinCraft , Inc. , to experimentally spin form cylinders and concentric parts from small and thin sheets of aluminum Metal Matrix Composites ( MMC ) , successfully yielded good microstructure data and forming parameters . MSFC and SpinCraft will collaborate on the recent technical findings and develop strategy to implement this technology for NASA 's advanced propulsion and airframe applications such as pressure bulkheads , combustion liner assemblies , propellant tank domes , and nose cone assemblies .
A 4BMS - X ( Four Bed Molecular Sieve - Exploration ) design and heater optimization study for CO2 sorbent beds in proposed exploration system architectures is presented . The primary objectives of the study are to reduce heater power and thermal gradients within the CO2 sorbent beds while minimizing channeling effects . Some of the notable changes from the ISS ( International Space Station ) CDRA ( Carbon Dioxide Removal Assembly ) to the proposed exploration system architecture include cylindrical beds , alternate sorbents and an improved heater core . Results from both 2D and 3D sorbent bed thermal models with integrated heaters are presented . The 2D sorbent bed models are used to optimize heater power and fin geometry while the 3D models address end effects in the beds for more realistic thermal gradient and heater power predictions .
We present demonstration of a novel broadband lidar technique capable of dealing with the atmospherically induced variations in CO2 absorption using a Fabry - Perot based detector and a broadband laser . The Fabry - Perot solid etalon in the receiver part is tuned to match the wavelength of several CO2 absorption lines simultaneously . The broadband technique tremendously reduces the requirement for source wavelength stability , instead putting this responsibility on the Fabry- Perot based receiver . The instrument technology we are developing has a clear pathway to space and realistic potential to become a robust , low risk space measurement system .
The National Aeronautics and Space Administration ( NASA ) has developed independent airframe and engine models that have been integrated into a single real - time aircraft simulation for piloted evaluation of propulsion control algorithms . In order to have confidence in the results of these evaluations , the integrated simulation must be validated to demonstrate that its behavior is realistic and that it meets the appropriate Federal Aviation Administration ( FAA ) certification requirements for aircraft . The paper describes the test procedures and results , demonstrating that the integrated simulation generally meets the FAA requirements and is thus a valid testbed for evaluation of propulsion control modes .
Rich and multifaceted domain specific specification languages like the Autonomic System Specification Language ( ASSL ) help to design reliable systems with self - healing capabilities . The GEAR game - based Model Checker has been used successfully to investigate properties of the ESA Exo- Mars Rover in depth . We show here how to enable GEAR s game - based verification techniques for ASSL via systematic model extraction from a behavioral subset of the language , and illustrate it on a description of the Voyager II space mission .
The Chandra X - R - ay Observatory has been launched on July 23 1999 . The first public release of the Chandra data analysis system , CIAO ( Chandra Interactive Analysis of Observations ) will be available in the near future . The XMM Science Survey Consortium is considering the possibility of using the whole or parts of CIAO to analyse observations from the XMM satellite and during the meeting we will give presentations and demonstrations of parts of CIAO , including the new GUIs developed for " FirstLook " analysis , data filtering and browsing ; SHERPA , the multi - dimensional , multi - missions modelling and fitting application ; CHIPS , the Chandra Imaging and Plotting System ; generic data manipulation tools and other applications .
Using the empirical constraints provided by observations in the inner corona and in interplanetary space . we derive the flow properties of the solar wind using a two fluid model . Density and scale height temperatures are derived from White Light coronagraph observations on SPARTAN 201 - 1 and at Mauna Loa , from 1.16 to 5.5 R , in the two polar coronal holes on 11 - 12 Apr. 1993 . Interplanetary measurements of the flow speed and proton mass flux are taken from the Ulysses south polar passage . By comparing the results of the model computations that fit the empirical constraints in the two coronal hole regions , we show how the effects of the line of sight influence the empirical inferences and subsequently the corresponding numerical results .