silkski/ENERAD huggingface dataset:
While rolling over the Meridiani Planum sedimentary terrane , the rover Opportunity has occasionally discovered large , > 10 cm erratics . Most of these have proven to be meteorites [ 1 ] , but one - Bounce Rock - is a martian basaltic rock similar in composition to the meteorite EETA79001 lithology B [ 2 ] . Presently , Opportunity is intensively investigating an --30 cm tall rock named Marquette Island that may be a distinct type of martian mafic lithology . We report the results of its continuing investigation using the Microscopic Imager ( MI ) ; Mossbauer Spectrometer ( MB ) and Alpha Particle X - ray Spectrometer ( APXS ) . A companion abstract discusses the results of Panoramic Camera ( Pancam ) imaging of the rock [ 3 ] .
The Stardust Interstellar Preliminary Examination ( ISPE ) reported in 2014 the discovery of 7 probable contemporary interstellar ( IS ) particles captured in Stardust IS Collector aerogel and foils . The ISPE reports represented work done over 6 years by more than 60 scientists and > 30,000 volunteers , which emphasizes the challenge identifying and analyzing Stardust IS samples was far beyond the primary Stardust cometary collection . We present a new potentially interstellar particle resulting from a continuation of analyses of the IS aerogel collection .
Due to the unique perspective of thermal infrared spectral measurements of geologic targets taken obliquely from a planetary rover or fixed lander , we have conducted several series of experiments designed to explore the various interferences which may arise from the local environment . Additional information is contained in the original extended abstract .
There is excellent evidence that a dynamical instability in the early solar system led to gravitational interactions between the giant planets and trans - Neptunian planetesimals . Giant planetary migration triggered by the instability dispersed a disk of primordial trans - Neptunian object ( TNOs ) and created a number of small body reservoirs ( e.g. the Kuiper Belt , scattered disk , irregular satellites , and the Jupiter / Neptune Trojan populations ) . It also injected numerous bodies into the main asteroid belt , where modeling shows they can successfully reproduce the observed P and D - type asteroid populations .
The National Aeronautics and Space Administration ( NASA ) has developed technologies to reduce aviation weather - related accidents . New technologies are presented for data - link and display of weather information to aircraft in flight , for detection of turbulence ahead of aircraft in flight , and for automated insitu reporting of atmospheric conditions from aircraft .
In recent years , methane in the martian atmosphere has been detected by Earth - based spectroscopy , the Planetary Fourier Spectrometer on the ESA Mars Express mission , and the NASA Mars Science Laboratory . The methane 's origin remains a mystery , with proposed sources including volcanism , exogenous sources like impacts and interplanetary dust , aqueous alteration of olivine in the presence of carbonaceous material , release from ancient deposits of methane clathrates , and/or biological activity . An additional potential source exists : meteor showers from the emission of large comet dust particles could generate martian methane via UV pyrolysis of carbon - rich infall material . We find a correlation between the dates of Mars / cometary orbit encounters and detections of methane on Mars . We hypothesize that cometary debris falls onto Mars during these interactions , generating methane via UV photolysis .
The objective of this work is to fundamentally reexamine the design space of tiltrotor aircraft beyond the very successful conventional vehicle configuration with tractor - type twin proprotors that are nacelle - mounted at the wing tips . Previously proposed alternate tiltrotor configurations include the Bell quad - tiltrotor and the Augusta Westland ERICA hybrid tiltrotor / tiltwing concepts . More recently , arguably alternate tiltrotor configurations include the NASA Langley " Puffin " and the Joby Aviation S-2 concepts . This work seeks to define a broad aircraft design space for alternate tiltrotor configurations . Being doing so , it is hoped this work will not only provide design inspiration for future aircraft developers but to also help realize new applications and missions for both passenger - carrying vehicles and vertical lift UAVs ( Unmanned Aerial Vehicles ) might one day be successfully enabled .
I will describe the history of the universe , from the Big Bang to 2013 , when the JWST is to be launched to look back towards our beginnings . I will discuss how the COBE results led to the Nobel Prize , how the COBE results have been confirmed and extended , and their implications for future observations . The James Webb Space Telescope will be used to examine every part of our history from the first stars and galaxies to the formation of individual stars and planets and the delivery of life - supporting materials to the Earth . I will describe the plans for the JWST and how observers may use it . With luck , the JWST may produce a Nobel Prize for some discovery we can only guess today .
This viewgraph presentation reviews the Adaptive Cross - Correlation ( ACC ) Algorithm for extended scene - Shack Hartmann wavefront ( WF ) sensing . A Shack - Hartmann sensor places a lenslet array at a plane conjugate to the WF error source . Each sub - aperture lenslet samples the WF in the corresponding patch of the WF . A description of the ACC algorithm is included . The ACC has several benefits ; amongst them are : ACC requires only about 4 image - shifting iterations to achieve 0.01 pixel accuracy and ACC is insensitive to both background light and noise much more robust than centroiding ,
To model radiative transfer through the atmosphere with high accuracy , one must resort to the calculation of spectral absorption coefficients on a line - by - line basis . The calculation of these coefficients is computationally expensive for three reasons : ( 1 ) thousands of spectral lines can contribute to absorption at a single frequency ; ( 2 ) the tails of spectral line profiles are long ( i.e. , a given line can contribute to absorption over a wide range of frequencies ) ; and ( 3 ) the sampling frequencies at which monochromatic radiances are to be calculated must be spaced sufficiently close together to resolve the thinnest lines of interest ( e.g. , those that arise in the stratosphere ) . We have developed a new algorithm to accelerate the calculation of spectral absorption coefficients while retaining high numerical accuracy .
Traditionally used for high precision geodesy , the GPS system has recently emerged as an equally powerful tool in atmospheric studies , in particular , climatology and meteorology . There are several products of GPS - based systems that are of interest to climatologists and meteorologists . One of the most useful is the GPS - based estimate of the amount of Precipitable Water Vapor ( PWV ) in the troposphere . Water vapor is an important variable in the study of climate changes and atmospheric convection ( Yuan et al . , 1993 ) , and is of crucial importance for severe weather forecasting and operational numerical weather prediction ( Kuo et al . , 1993 ) .
The central nervous system must resolve the ambiguity of inertial motion sensory cues in order to derive accurate spatial orientation awareness . Adaptive changes in how inertial cues from the otolith system are integrated with other sensory information lead to perceptual and postural disturbances upon return to Earth s gravity . The primary goals of this ground - based research investigation are to explore physiological mechanisms and operational implications of tilt - translation disturbances during and following re - entry , and to evaluate a tactile prosthesis as a countermeasure for improving control of whole - body orientation during tilt and translation motion .
Heat - shield for Extreme Entry Environment Technology ( HEEET ) has been in development since 2014 with the goal of enabling missions to Venus , Saturn and other high - speed sample return missions . It is offered as a new technology and incentivized for mission use in the New Frontiers 4 AO by NASA . The current plans are to mature the technology to TRL 6 by FY’18 . The HEEET Team has been working closely with multiple NF-4 proposals to Venus , Saturn and has been supporting recent Ice - Giants mission studies . This presentation will provide progress made to date and the plans for development in FY’18 .
We use multi - point timing analysis to determine the orientation and motion of flux transfer events ( FTEs ) detected by the four Cluster spacecraft on the high - latitude dayside and flank magnetopause during 2002 and 2003 . During these years , the distances between the Cluster spacecraft were greater than 1000 km , providing the tetrahedral configuration needed to select events and determine velocities . Each velocity and location will be examined in detail and compared to the velocities and locations determined by the predictions of the component and antiparallel reconnection models for event formation , orientation , motion , and acceleration for a wide range of spacecraft locations and solar wind conditions .
The Genesis mission was the only mission returning pristine solar material to Earth since the Apollo program . Unfortunately , the return of the spacecraft on September 8 , 2004 resulted in a crash landing shattering the solar wind collectors into smaller fragments and exposing them to desert soil and other debris . Thorough surface cleaning is required for almost all fragments to allow for subsequent analysis of solar wind material embedded within . However , each collector fragment calls for an individual cleaning approach , as contamination not only varies by collector material but also by sample itself .
The TDI project ( TDI ) investigates trending technical data standards for applicability to NASA vehicles , space stations , payloads , facilities , and equipment . TDI tested COTS software compatible with a certain suite of related industry standards for capabilities of individual benefits and interoperability . These standards not only esnable Information Technology ( IT ) efficiencies , but also address efficient structures and standard content for business processes . We used source data from generic industry samples as well as NASA and European Space Agency ( ESA ) data from space systems .
The NASA Lewis Research Center has a thermal management program supporting SP-100 goals , which includes heat pipe radiator development . As a part of the program Lewis has elected to prepare an in - house heat pipe code tailored to the needs of its SP-100 staff to supplement codes from other sources . The latter , designed to meet the needs of the originating organizations , were deemed not entirely appropriate for use at Lewis . However , a review of their features proved most beneficial in the design of the Lewis code .
Selection of a landing site for the ' 03 and later Mars surface missions represents a balance between potential science results and landing site safety . Although safety has to be the prime consideration , it is the melding together of spacecraft hazard analysis with science analysis that provides the key to understanding the nature of the surface for determining both its safety for landing and its scientific potential . Our goal here is to discuss the geological factors that go into a determination of site safety , at scales from centimeters up to kilometers , and to understand the implications for the resulting scientific return that can be expected .
Destructive examinations were performed to document the progression of multi - site damage ( MSD ) in three lap joint panels that were removed from a full scale fuselage test article that was tested to 60,000 full pressurization cycles . Similar fatigue crack growth characteristics were observed for small cracks ( 50 microns to 10 mm ) emanating from counter bore rivets , straight shank rivets , and 100 deg counter sink rivets . Good correlation of the fatigue crack growth data base obtained in this study and FASTRAN Code predictions show that the growth of MSD in the fuselage lap joint structure can be predicted by fracture mechanics based methods .
The Advanced Concepts Office at Marshall Space Flight Center completed a brief spacecraft design study for the 8 - meter monolithic Advanced Technology Large Aperture Space Telescope ( ATLAST-8 m ) . This spacecraft concept provides all power , communication , telemetry , avionics , guidance and control , and thermal control for the observatory , and inserts the observatory into a halo orbit about the second Sun - Earth Lagrange point . The multidisciplinary design team created a simple spacecraft design that enables component and science instrument servicing , employs articulating solar panels for help with momentum management , and provides precise pointing control while at the same time fast slewing for the observatory .
This paper addresses the advantages of utilizing a centrifuge test over the conventional static load test methods to structurally qualify aerospace structures . Three recent test cases are reviewed and used as examples to highlight these benefits . In addition , the overall capability of Goddard 's High Capacity Centrifuge ( HCC ) is outlined along with some unique features that were designed specifically to reduce costs , test turn around time , and increase test item safety .
In this paper , we study the potential benefits of using relatively broadband wireless power transmission WPT strategies in both weak - signal and multipath environments where traditional narrowband strategies can be very inefficient . The paper is primarily a theoretical and analytical treatment of the problem that attempts to derive results that are widely applicable to many different WPT applications , including space solar power SSP .
An empty test section flow calibration of the refurbished NASA Ames 12 - Foot Pressure Tunnel was recently completed . Distributions of total pressure , dynamic pressure , Mach number , flow angularity temperature , and turbulence are presented along with results obtained prior to facility demolition . Axial static pressure distributions along tunnel centerline are also compared . Test section model support geometric configurations will be presented along with a discussion of the issues involved with different model mounting schemes .
Mass spectroscopic measurements on the gas and dust in the coma of Comet Halley revealed the presence of considerable amounts of organic species . Greenberg ( 1973 ) proposed that prior to the formation of the comet UV processing of the ice mantles on grains in dense clouds could lead to the formation of complex organic molecules . Theoretical predictions of the internal UV field in dense clouds as well as the discovery in interstellar ices of species like OCS and OCN- which have been formed in simulation experiments by photoprocessing of interstellar ice analogues point to the importance of such processing . We undertook a laboratory simulation study of the formation of organic molecules in interstellar ices and their possible relevance to the Comet Halley results .
The goal of the Information Presentation Directed Research Project ( DRP ) is to address design questions related to the presentation of information to the crew on flight vehicles , surface landers and habitats , and during extra - vehicular activities ( EVA ) . Designers of displays and controls for exploration missions must be prepared to select the text formats , label styles , alarms , electronic procedure designs , and cursor control devices that provide for optimal crew performance on exploration tasks . The major areas of work , or subtasks , within the Information Presentation DRP are : 1 ) Controls , 2 ) Displays , 3 ) Procedures , and 4 ) EVA Operations .
This paper advocates for a specific design approach , based on simple principals , yet addresses challenges faced by the system engineers when designing complex data and information infrastructure . The document provides guidance for breaking out various work elements in the overall network architecture design , so that communication systems are conceived and effectively realized regardless of their location , size and local specifics . Although targeted at the Global Airspace System ( GAS ) and National Airspace System ( NAS ) , this framework can be applied to any network - centric architecture .
In the summer of 20 11 NASA approved the proposal for the Space Geodesy Project ( SGP ) . A major element is developing at the Goddard Geophysical and Astronomical Observatory a prototype of the next generation of integrated stations with co - located VLBI , SLR , GNSS and DORIS instruments as well as a system for monitoring the vector ties . VLBI2010 is a key component of the integrated station . The objectives ofSGP , the role of VLBI20 lOin the context of SGP , near term plans and possible future scenarios will be discussed .
A new , interferometer based system for measuring thermal expansion to an absolute accuracy of 20 ppb or better at cryogenic temperatures has been developed . Data from NIST Copper SRM 736 measured from room temperature to 15 K will be presented along with data from many other materials including beryllium , ULE , Zerodur , and composite materials . Particular attention will be given to a study by the Space Optics Manufacturing Technology Center ( SOMTC ) investigating the variability of ULE and beryllium materials used in the AMSD program . Approximately 20 samples of each material , tested from room temperature to below 30 K are compared as a function of billet location .
The Atmospheric Tomography ( ATom ) mission deployed an extensive gas and aerosol payload on the NASA DC-8 aircraft on four campaigns spanning each season . ATom systematically sampled the atmosphere from 0.2 to 12 kilometer altitude , from 85 degrees North Latitude to 65 degrees South Latitude , in both the Pacific and the Atlantic to provide detailed profiles of chemical composition over the remote oceans . We will present profiles of reactive trace species , such as O3 , NOx , NOy , HOx , HCHO , and several other short - lived source gases . We will combine these measurements with results from a 0 - D box model to show their utility in ( 1 ) evaluating gradients in latitude / season , ( 2 ) identifying contributions of pollution from long - range and convective transport , and ( 3 ) evaluating column measurements from remote sensing satellite instruments .
GRIDVIEW is being developed by the GEODYNAMICS Branch at NASA 's Goddard Space Flight Center and can be downloaded on the web at http://geodynamics.gsfc.nasa.gov/gridview/. The program is very mature and has been successfully used for more than four years , but is still under development as we add new features for data analysis and visualization . The software can run on any computer supported by the IDL virtual machine application supplied by RSI . The virtual machine application is currently available for recent versions of MS Windows , MacOS X , Red Hat Linux and UNIX . Minimum system memory requirement is 32 MB , however loading large data sets may require larger amounts of RAM to function adequately .
Designed and funded in the pre-'better , faster , cheaper ' era , Cassini was built to be the one mission to Saturn for many years to come . Its complement of twelve Orbiter science instruments and the Huygens Probe make Cassini one of the most complex missions ever flown . With a seven - year cruise and Saturn Orbit Insertion now over , Cassini is settling in to perform a very ambitious prime mission over the next four years . This paper provides an overview of the spacecraft design and the mission operations to date .
Most robotic missions to the outer solar system must grapple with the hazards posed by the dusty rings of the gas giants . Early assessments of these hazards led simply to ring avoidance due to insufficient data and high uncertainties on the dust population present in such rings . Recent approaches , principal among them the Cassini dust hazard management strategy , provide useful results from detailed modeling of spacecraft vulnerabilities and dust hazard regions , which along with the range of mission trajectories are used to to assess the risks posed by each passage through a zone of potential hazard . This paper shows the general approach used to implement the analysis for Cassini , with recommendations for future outer planet missions .
A model review is a validation technique aimed at determining if a model is of sufficient quality and allows defects to be identified early in the system development , reducing the cost of fixing them . In this paper we propose a technique to perform automatic review of Abstract State Machine ( ASM ) formal specifications . We first detect a family of typical vulnerabilities and defects a developer can introduce during the modeling activity using the ASMs and we express such faults as the violation of meta - properties that guarantee certain quality attributes of the specification . These meta - properties are then mapped to temporal logic formulas and model checked for their violation . As a proof of concept , we also report the result of applying this ASM review process to several specifications .
Vegetation water content ( VWC ) is an important component of microwave soil moisture retrieval algorithms . This paper aims to estimate VWC using L band active and passive radar / radiometer datasets obtained from a NASA ground - based Soil Moisture Active Passive ( SMAP ) simulator known as ComRAD ( Combined Radar / Radiometer ) . Several approaches to derive vegetation information from radar and radiometer data such as HH , HV , VV , Microwave Polarization Difference Index ( MPDI ) , HH / VV ratio , HV/(HH+VV ) , HV/(HH+HV+VV ) and Radar Vegetation Index ( RVI ) are tested for VWC estimation through a generalized linear model ( GLM ) . The overall analysis indicates that HV radar backscattering could be used for VWC content estimation with highest performance followed by HH , VV , MPDI , RVI , and other ratios .
2014 marks the crystal ( 15th ) anniversary of the launch of the Chandra X‐ray Observatory . This paper offers some of the major lessons learned by some of the key members of the Chandra Telescope team . We offer some of the lessons gleaned from our experiences developing , designing , building and testing the telescope and its subsystems , with 15 years of hindsight . Among the topics to be discussed are the early developmental tests , known as VETA‐I and VETA‐II , requirements derivation , the impact of late requirements and reflection on the conservatism in the design process .
Modular robotic systems offer potential advantages as versatile , fault - tolerant , cost - effective platforms for space exploration , but a sufficiently mature system is not yet available . We describe the possible applications of such a system , and present prototype hardware intended as a step in the right direction . We also present elements of an automated design and optimization framework aimed at making modular robots easier to design and use , and discuss the results of applying the system to a gait optimization problem . Finally , we discuss the potential near - term applications of modular robotics to terrestrial robotics research .
A three - step process bridges the gap between lower - fidelity solutions that ignore optimal dynamics and fully optimized solutions that are computationally expensive to generate . First , analytic solutions for transfers with free time and angle characterize the evolution of the shape and orientation of the orbit . Next , optimal control theory supplies the thrust vector with variable specific impulse while satisfying flight time and transfer angle constraints . Transfers with the additional constraint of constant specific impulse then provide a more realistic thruster model for preliminary trade studies . These approximations deliver a hundredfold improvement in run time at the expense of a few percent error in mass .