silkski/ENERAD huggingface dataset:
This report summarizes the Access to Space ( A2S ) Workshop held on February 25 - 27 , 2020 at the Johns Hopkins University Applied Physics Laboratory ( APL ) and hosted by NASA ’s Science Mission Directorate ( SMD ) . This workshop solicited community input on the creation and management of an ESPA - class1payload pipeline for NASA SMD launches . The workshop brought together roughly 180 participants including scientists , engineers , instrument developers , launch providers , and policy makers across NASA centers , government agencies , commercial industry , research institutes , and academia .
The preliminary results obtained with the solar extreme ultraviolet spectrometer , onboard the Solar and Heliospheric Observatory ( SOHO ) , are reported on . The solar ultraviolet measurement of emitted radiation ( SUMER ) instrument established a long time series of the network evolution in following the solar rotation . The maps of the network evolution were obtained in lines spanning from 10(sup 4 ) K to 6 x 10(sup 6 ) K. Line profiles were also recorded with a sampling of 1 x 0.76 sq arcsec over the entire field . The progress analysis of this set of data is underlined and the velocity distribution in the cell network is considered .
Current best - practices for mesh generation in a structured overset framework are evaluated to determine their effects on the accuracy and convergence of the flow solution on a two - dimensional sectional cut of the High - Lift Common Research Model ( HLCRM ) wing . Mesh parameters are varied independently and correlated with force and moment coefficients from the flow solutions to identify the trends and sensitivities of the parameter variations , and the characteristics of a best practice mesh .   Grid convergence and mesh adaption studies are also performed to determine the minimum mesh quality needed in order for solution - based adaption to reach an accurate flow solution .
With the growth of aviation operations and the emergence of new entrants into the National Airspace System , there has been an increasing demand for aeronautical communications .   However , the existing VHF / UHF frequency allocations for NAS operations have become increasingly scarce and unable to support the projected growth in demand .   While traditional approaches to address the spectrum scarcity issue ( such as reduction of channel bandwidth ) have provided some relief , there is a need for a more scalable and sustainable solution .   Consequently , NASA is investigating a new approach to spectrum management within the NAS using Artificial Intelligence and other advanced technologies .   The concept considers both air - ground and air - air communication networks with the anticipated outcome that the proposed concept will meet the spectrum needs of future NAS communications .
In the early morning on Saturday , February 1 , 2003 , the Space Shuttle Columbia broke up during entry . After extensive investigation of the accident and recommendations made by the Columbia Accident Investigation Board , President Bush gave the vision for space exploration for NASA , which include return the Space Shuttle to flight as soon as practical , complete assembly of the ISS by the end of the decade , initiate robotic missions to the moon no later than 2008 , develop a new Crew Exploration Vehicle , conduct first robotic , then human missions to Mars and extend human exploration across the solar system .
Geoscientists have been training and preparing astronauts to observe the Earth from space and explore other planetary surfaces with a legacy that reaches back to the early days of the space program . Continuing this legacy and critical function , a core NASA team has been closely coordinating with the Johnson Space Center ( JSC ) Flight Operations Directorate ( FOD ) as well as academic , institute , and other governmental partners to conduct a comprehensive geoscience training program that ranges from initial astronaut candidate training to preparing crew for Artemis missions . Described below are the three program training phases , along with recent program highlights and forward planning .
Capability for precise lunar landing is the goal for future NASA missions . A LIDAR - based terrain relative navigation ( TRN ) approach lets us achieve this goal and also land under any illumination conditions . Results from field test data showed that the LIDAR TRN algorithm obtained position estimates with mean error of about 20 meters and standard deviations of about 10 meters . Moreover , the algorithm was capable of providing 99 percent correct estimates by assessing the local terrain relief in the data . Also , the algorithm was able to handle initial position uncertainty of up to 1.6 kilometers   without performance degradation .
In this paper , we present some ideas regarding the modeling , dynamics and control aspects of granular spacecraft . Granular spacecraft are complex multibody systems composed of a spatially disordered distribution of a large number of elements , for instance a cloud of grains in orbit . An example of application is a spaceborne observatory for exoplanet imaging , where the primary aperture is a cloud instead of a monolithic aperture . A model is proposed of the multi - scale dynamics of the grains and cloud in orbit , as well as a control approach for cloud shape maintenance and alignment , and preliminary simulation studies are carried out for the representative imaging system .
The design estimate for the materials for the International Space Station ( ISS ) specified in SSP 30512 was a conservative estimate . The environment dose was over estimated . The materials originally qualified for approximately 10 - 15 years are anticipated to be acceptable for periods of up to 20 - 30 years based on SSP-30512 or 40 - 60 years based on 2x SSP-30512 . This viewgraph presentation shows charts and graphs that review the altitude , the solar minimum and maximum , and the radiation exposure of other satellite , among other graphics .
The purpose of this NCRP commentary is to provide the current state of knowledge on the effects of ionizing radiation on the immune system and on latent herpes virus reactivation to the scientific community and government agencies . Its purpose is to better understand radiation - induced latent virus reactivation , which is possibly an underestimated consequence of ionizing radiation exposure . This activity should involve the radiation research community ( academia , industry and regulatory agencies ) and government agencies ( NASA , DOD , CDC ) .
Polymers containing covalently bonded nonlinear optical ( NLO ) chromophores are expected to possess special properties such as greater stability , better mechanical processing , and easier film formation than their non - polymeric equivalent . For the present work , polymethylmethacrylate ( PMMA ) was selected as the basic polymer unit on which to incorporate different NLO chromophores . The NLO components were variations of DIVA { [ 2 - methoxyphenyl methylidene]-propanedinitrile } which we prepared from vanillin derivatives and malononitrile . These were esterified with methacrylic acid and polymerized either directly or with methyl methacrylate to form homopolymers or copolymers respectively . Characterization of the polymers and NLO property studies are underway .
The authors are developing a smart coating system based on pH - triggered release microcapsules . These microcapsules can be incorporated into various coating systems for corrosion detection , protection and self - repair of mechanical coating damage . This paper will present the results from progress made to date in the controlled release properties of these microcapsules as well as in their corrosion indication and corrosion inhibition function .
NASA Ames Research Center is known internationally as a center of excellence for its capabilities and achievements in the field of developmental aerodynamics . The Center has a variety of aerodynamic test facilities including the largest wind tunnel in the world ( with 40 x 80 deg and 80 x 120 deg atmospheric test sections ) and the 12 - Foot Pressure Wind Tunnel which is the subject of this paper . Additional information is contained in the original extended abstract .
This paper provides an overview of the non - grey radiation modeling capabilities of Cullimore and Ring 's Thermal Desktop(Registered TradeMark ) Version 4.8 SindaWorks software . The non - grey radiation analysis theory implemented by Sindaworks and the methodology used by the software are outlined . Representative results from a parametric trade study of a radiation shield comprised of a series of v - grooved shaped deployable panels is used to illustrate the capabilities of the SindaWorks non - grey radiation thermal analysis software using emissivities with temperature and wavelength dependency modeled via a Hagen - Rubens relationship .
Exploration missions are expected to use variable pressure extravehicular activity ( EVA ) spacesuits as well as a spacecraft " exploration atmosphere " of 56.5 kPa ( 8.2 psia ) , 34 % O2 , both of which provide the possibility of reducing the oxygen prebreathe times necessary to reduce decompression sickness ( DCS ) risk . Previous modeling work predicted 8.4 % DCS risk for an EVA beginning at the exploration atmosphere , followed by 15 minutes of in - suit O2 prebreathe , and 6 hours of EVA at 29.6 kPa ( 4.3 psia ) . In this study we model notional prebreathe protocols for a variable pressure suit where the exploration atmosphere is unavailable .
The test results of measurements performed on two different sizes of ferroelectric random access memory ( FeRAM ) suggest the degradation is due to the low radiation tolerance of sense amplifiers and reference voltage generators which are based on commercial complementary metal oxide semiconductor ( CMOS ) technology . This paper presents total ionizing dose ( TID ) testing of 64Kb Ramtron FM1608 and 256Kb Ramtron FM1808 .
The OSIRIS - REx mission to the asteroid(101955 ) Bennu heavily relies on optical navigation to provide relative state information between the asteroid and the spacecraft . These measurements enable determination of the spacecraft 's orbit to the tight requirements needed to meet the science goals of the mission . In this document we describe the algorithms and techniques used by the Goddard independent verification and validation navigation effort to extract these measurements from the images taken by the spacecraft during the mission . We also demonstrate the capabilities of the techniques by showing the high accuracy of the results when used in an orbit determination solution .
This paper examines the behavior of flux and slope limiters on non - uniform grids in multiple dimensions . We note that on non - uniform grids the scalar formulation in standard use today sacrifices k - exactness , even for linear solutions , impacting both accuracy and convergence . We rewrite some well - known limiters in a n way to highlight their underlying symmetry , and use this to examine both traditional and novel limiter formulations . A consistent method of handling stretched meshes is developed , as is a new directional formulation in multiple dimensions for irregular grids . Results are presented demonstrating improved accuracy and convergence using a combination of model problems and complex three - dimensional examples .
The prediction of separation bubbles on NACA 65 - 213 and NACA 0012 using a modified Chen - Thyson transition model is presented . The contents include : 1 ) Background ; 2 ) Analysis of NACA 65 - 213 separation bubble using cebeci 's viscous - inviscid interaction method ; 3 ) Analysis of NACA 0012 separation bubble using navier - stokes method ; and 4 ) Comparison with experiment .
The Laser Interferometer Space Antenna ( LISA ) mission is a planned gravitational wave detector consisting of three spacecraft in heliocentric orbit . Laser interferometry is used to measure distance fluctuations between test masses aboard each spacecraft to the picometer level over a 5 million kilometer separation . Laser frequency fluctuations must be suppressed in order to meet the measurement requirements . Arm - locking , a technique that uses the constellation of spacecraft as a frequency reference , is a proposed method for stabilizing the laser frequency . We consider the problem of arm - locking using classical optimal control theory and find that our designs satisfy the LISA requirements .
Algorithms for rapid generation of moderate - fidelity structural finite element models of air vehicle structures to allow more accurate weight estimation earlier in the vehicle design process have been developed . Application of these algorithms should help to rapidly assess many structural layouts before the start of the preliminary design phase and eliminate weight penalties imposed when actual structure weights exceed those estimated during conceptual design . By defining the structural topology in a fully parametric manner , the structure can be mapped to arbitrary vehicle configurations being considered during conceptual design optimization . Recent enhancements to this approach include the porting of the algorithms to a platform - independent software language Python , and modifications to specifically consider morphing aircraft - type configurations . Two sample cases which illustrate these recent developments are presented .
The Shuttle Environmental Assurance Initiative ( SEA ) has identified a potential for the Space Shuttle Program ( SSP ) to incur materials obsolescence issues due to agreements between the fluoro - chemical industry and the United States Environmental Protection Agency ( USEPA ) to participate in a Global Stewardship Program for perfluorooctanoic acid ( PFOA ) . This presentation will include discussions of the chemistry , regulatory drivers , affected types of fluoropolymer and fluoroelastomer products , timeline for reformulations , and methodology for addressing the issue . It will cover the coordination of assessment efforts with the International Space Station and Head Quarters Air Force Space Command , along with some examples of impacted materials . The presentation is directed at all members of the international aerospace community concerned with identifying potential environmentally driven materials obsolescence issues .
NASA 's Johnson Space Center ( JSC ) has utilized COTS products in its programs since the early 1990 's . Recently it has become evident that , of all failure modes possible , radiation will probably dominate ; sometimes to the point of driving system architecture . It is now imperative that radiation susceptibility be addressed when writing the system requirements . Susceptibility assessment , e.g. testing , must begin early in the design phase to establish performance and continue through the hardware qualification program to prove satisfaction of the original requirements(s ) . Examples of requirements , testing , and architecture versus failure rate will be given .
PIAA optics for high contrast imaging present challenges in manufacturing and testing due to their large surface departures from aspheric profiles at the aperture edges . With smaller form factors and consequent smaller surface deformations ( < 50 microns ) , fabrication of these mirrors with diamond turning followed by electron beam lithographic techniques becomes feasible . Though such a design reduces the system throughput to approx.50 % , it still provides good performance down to 2 lambda / D inner working angle . With new achromatic focal plane mask designs , the system performance can be further improved . We report on the design , expected performance , fabrication challenges , and initial assessment of such novel PIAA optics .
When two supermassive black holes ( SMBHS ) approach within 1 - 10 mpc , gravitational wave ( GW ) losses begin to dominate the evolution of the binary , pushing the system to merge in a relatively small time . During this final inspiral regime , the system will emit copious energy in GWs , which should be directly detectable by pulsar timing arrays and space - based interferometers . At the same time , any gas or stars in the immediate vicinity of the merging 5MBHs can get heated and produce bright electromagnetic ( EM ) counterparts to the GW signals . We present here a number of possible mechanisms by which simultaneous EM and GW signals will yield valuable new information about galaxy evolution , accretion disk dynamics , and fundamental physics in the most extreme gravitational fields .
This paper presents the results of a preliminary structural sizing and alternate material trade study for NASA s Crew Exploration Vehicle ( CEV ) Crew Module ( CM ) . This critical CEV component will house the astronauts during ascent , docking with the International Space Station , reentry , and landing . The alternate material design study considers three materials beyond the standard metallic ( aluminum alloy ) design that resulted from an earlier NASA Smart Buyer Team analysis . These materials are graphite / epoxy composite laminates , discontinuously reinforced SiC / Al ( DRA ) composites , and a novel integrated panel material / concept known as WebCore . Using the HyperSizer ( Collier Research and Development Corporation ) structural sizing software and NASTRAN finite element analysis code , a comparison is made among these materials for the three composite CM concepts considered by the 2006 NASA Engineering and Safety Center Composite Crew Module project .
The fundamental capability of Nuclear Thermal Propulsion ( NTP ) is game changing for space exploration . A first generation Nuclear Cryogenic Propulsion Stage ( NCPS ) based on NTP could provide high thrust at a specific impulse above 900 s , roughly double that of state of the art chemical engines . Characteristics of fission and NTP indicate that useful first generation systems will provide a foundation for future systems with extremely high performance . The role of the NCPS in the development of advanced nuclear propulsion systems could be analogous to the role of the DC-3 in the development of advanced aviation . Progress made under the NCPS project could help enable both advanced NTP and advanced Nuclear Electric Propulsion ( NEP ) .
In support of the ongoing effort by the National Aeronautics and Space Administration ( NASA ) to bring supersonic commercial travel to the public , NASA , in partnership with other industry organizations , conducted a flight research experiment to analyze acoustic propagation at the lateral edge of the sonic boom carpet . The name of the effort was the Farfield Investigation of No - boom Thresholds ( FaINT ) . The research from FaINT determined an appropriate metric for sonic boom waveforms in the transition and shadow zones called Perceived Sound Exposure Level , established a value of 65 dB as a limit for the acoustic lateral extent of a sonic boom 's noise region , analyzed change in sonic boom levels near lateral cutoff , and compared between real sonic boom measurements and numerical predictions .
Some of the radio sources used by VLBI to materialize the celestial reference frame are known to have apparent motions at the sub - milliarcsecond level , particularly those observed in the early years . On the other hand , state of the art precession - nutation models match the observations at this same level . We investigate to what extent the source instability may contaminate the VLBI determination of precession and nutation corrections in several frequency domains .
The long - baseline space interferometer concept involving formation flying of multiple spacecraft holds great promise as future space missions for high - resolution imagery . A major challenge of obtaining high - quality interferometric synthesized images from long - baseline space interferometers is to accurately control these spacecraft and their optics payloads in the specified configuration . Our research focuses on the determination of the optical errors to achieve fine control of long - baseline space interferometers without resorting to additional sensing equipment . We present a suite of estimation tools that can effectively extract from the raw interferometric image relative x / y , piston translational and tip / tilt deviations at the exit pupil aperture . The use of these error estimates in achieving control of the interferometer elements is demonstrated using simulated as well as laboratory - collected interferometric stellar images .
The objectives of the GTX ( Vertical Take - off/ Horizontal Landing reusable single - stage - to - orbit system ) project this viewgraph presentation summarizes include the following : ( 1 ) Determine whether or not air - breathing propulsion can enable reusable single stage to orbit vehicles ; ( 2 ) Provide validated system performance data , and a baseline system design ; and ( 3 ) Develop technologies applicable to high - speed airbreathing propulsion
The human element is the most complex element of the mission design Mars missions will pose significant physiological and psychological challenges to crew members Some challenges ( human engineering , life support ) must be overcome ( potential " non - starters " ) Some challenges ( bone , radiation ) may be show - stoppers ISS will only Indirectly address Mars questions before any " Go / No Go " decision Significant amount of ground - based and specialized flight research will be required -- Critical Path Roadmap project will direct HSLSPO 's research toward Mars exploration objectives
Under NASA 's New Millennium Program Space Technology 8 Project , four experiments are being developed for future small system applications requiring low mass , low power , and compactness . GSFC is responsible for developing the Thermal Loop experiment , which is an advanced thermal control system consisting of a miniature loop heat pipe ( MLHP ) with multiple evaporators and condensers . The objective is to validate the operation of an MLHP , including reliable start - ups , steady operation , heat load sharing , and tight temperature control over the range of 273 K to 308K. An MLHP Breadboard has been built and tested for 1200 hours under the laboratory environment and 500 hours in a thermal vacuum chamber . Results of the TV tests are presented here .
Experimental aerodynamic investigations of the NASA Common Research Model have been conducted in the NASA Langley National Transonic Facility , the NASA Ames 11 - ft wind tunnel , and the European Transonic Wind Tunnel . In the NASA Ames 11 - ft wind tunnel , data have been obtained at only a chord Reynolds number of 5 million for a wing / body / tail = 0 degree incidence configuration . Data have been obtained at chord Reynolds numbers of 5 , 19.8 and 30 million for the same configuration in the National Transonic Facility and in the European Transonic Facility . Force and moment , surface pressure , wing bending and twist , and surface flow visualization data were obtained in all three facilities but only the force and moment , surface pressure and wing bending and twist data are presented herein .
The acoustic radiation from the turbulent boundary layer on the nozzle wall of a Mach 6 Ludwieg Tube is simulated using Direct Numerical Simulations ( DNS ) , with the flow conditions falling within the operational range of the Mach 6 Hypersonic Ludwieg Tube , Braunschweig ( HLB ) . The mean and turbulence statistics of the nozzle - wall boundary layer show good agreement with those predicted by Pate 's correlation and Reynolds Averaged Navier - Stokes ( RANS ) computations . The rms pressure fluctuation P'(rms)/T(w ) plateaus in the freestream core of the nozzle . The intensity of the freestream noise within the nozzle is approximately 20 % higher than that radiated from a single at pate with a similar freestream Mach number , potentially because of the contributions to the acoustic radiation from multiple azimuthal segments of the nozzle wall .