silkski/ENERAD huggingface dataset:
Linear negative gravity anomalies in Acidalia Planitia along the eastern edge of Tempe Terra and along the northern edge of Arabia Terra have been noted in Mars Global Surveyor gravity fields . Once proposed to represent buried fluvial channels , it is now believed that these gravity troughs mainly arise from partial compensation of the hemispheric dichotomy topographic scarp . A recent inversion for crustal structure finds that mantle compensation of the scarp is offset from the present - day topographic expression of the dichotomy boundary . The offset suggests that erosion or other forms of mass wasting occurred after lithosphere thickened and no longer accomodated topographic change through viscous relaxation .
In the near future NASA intends to explore Mars in preparation for a sample return mission using robotic devices such as landers rovers , orbiters , airplanes , and/or balloons . Such platforms will likely carry imaging devices to characterize the surface morphology , and a variety of analytical instruments intended to evaluated the chemical and mineralogical nature of the environment(s ) that they encounter . Historically , mission operations have involved the following sequence of activities : ( 1 ) return of scientific data from the vehicle ; ( 2 ) evaluation of the data by space scientists ; ( 3 ) recommendations of the scientists regarding future mission activity ; ( 4 ) transmission of commands to the vehicle to achieve this activity ; and ( 5 ) new activity by the vehicle in response to those commands .
The allowable operating currents of electrical wiring when used in the space vacuum environment is predominantly determined by the maximum operating temperature of the wire insulation . For Kapton insulated wire this value is 200 C. Guidelines provided in the Goddard Space Flight Center ( GSFC ) Preferred Parts List ( PPL ) limit the operating current of wire within vacuum to ensure the maximum insulation temperature is not exceeded . For 20 AWG wire , these operating parameters are : 3.7 amps per wire , bundle of 15 or more wires , 70 C environment , and vacuum of 10(exp -5 ) torr or less . To determine the behavior and temperature of electrical wire at different operating conditions , a thermal vacuum test was performed on a representative electrical harness of the Hubble Space Telescope ( HST ) power distribution system . This paper describes the test and the results .
The motivation of the testing was to reduce noise generated by eddy Mach wave emission via enhanced mixing in the jet plume . This was to be accomplished through the use of an ejector shroud , which would bring in cooler ambient fluid to mix with the hotter jet flow . In addition , the contour of the mixer , with its chutes and lobes , would accentuate the merging of the outer and inner flows . The objective of the focused schlieren work was to characterize the mixing performance inside of the ejector . Using flow visualization allowed this to be accomplished in a non - intrusive manner .
This viewgraph presentation reviews the sources , problems and some solutions to dust on the moon . While there appeared to be no long term effects from Lunar Dust in Apollo astronauts , the future lunar missions will be longer in duration , and therefore more problems may present themselves . Some of the se problems are reviewed , and plans to deal with them are reviewed .
The Advanced Technology Microwave Sounder ( ATMS ) is a satellite - based microwave radiometer that provides temperature and humidity sounding observations from low Earth orbit . The instrument utilizes 22 channels that cover a frequency range of 23 to 183 GHz . The first ATMS instrument was launched in 2011 on the Suomi National Polar - orbiting   Partnership ( S - NPP ) satellite and the second ATMS was launched in 2017 on the Joint Polar Satellite System-1 ( JPSS-1 )   satellite ( now NOAA-20 ) ; both on - orbit ATMS instruments are currently operational . This paper will describe the pre - launch performance of the third ATMS instrument , designated for the JPSS-2 satellite , during ground testing and calibration .
Limitations to the performance of laser - cooled earth and space - based Cs clocks will be critically discussed . The most significant limitation to the stability and accuracy of laser - cooled atomic clocks is the frequency shift due to cold collisions . Because of it , laser - cooled Cs clocks must be operated at low density and this implies that space based Cs clock performance will not be significantly better than earth based . To regain some of the high accuracy and stability lost to the low density , clocks can be designed to multiply launch ( or juggle ) atoms . Clocks based on other atoms , in particular Rb-87 or possibly Rb-85 , may have much smaller cold collision frequency shifts and therefore be capable of higher stability and accuracy , especially in a space environment .
Several methods of packaging high speed ( 75 - 330 GHz ) InP HEMT MMIC devices are discussed . Coplanar wirebonding is presented with measured insertion loss of less than 0.5dB and return   loss better than -17 dB from DC to 110 GHz . A motherboard / daughterboard packaging scheme is presented which supports minimum loss chains of MMICs using this coplanar wirebonding method .   Split waveguide block packaging approaches are presented in G - band ( 140 - 220 GHz ) with two types of MMIC - waveguide transitions : E - plane probe andantipodal finline .
Visualization of the flow field around a generic re - entry capsule in subsonic flow and shock wave visualization with cylindrical explosives have been conducted to demonstrate sensitivity and applicability of background - oriented schlieren ( BOS ) for field experiments . The wind tunnel experiment suggests that BOS with a fine - pixel imaging device has a density change detection sensitivity on the order of 10(sup -5 ) in subsonic flow . In a laboratory setup , the structure of the shock waves generated by explosives have been successfully reconstructed by a computed tomography method combined with BOS .
Mars landers to date have flown ballistic entry trajectories with no trajectory control after the final maneuver before entry . Improvements in landing accuracies ( from approx.150 km from the target for Mars Pathfinder to approx.30 - 40 km for MER and Phoenix ) have been driven by approach navigation improvements . MSL will fly the first guided - entry trajectory to Mars , further improving accuracy to approx.10 - 12 km from the target .
I will give a brief description of Gamma - ray burst Coordinates Network ( GCN ) ( distribution methods , filtering criteria , etc ) plus the types of notices currently being distributed ( GRBs , transients , & monitoring ) . Then cover how Stellar Observations Network Group ( SONG ) telescopes could make use of these notice types to fill in some of their observing time . I will then make a pitch to get SONG telescopes to contribute those data products that are consistant with the real - time transient aspects of GCN .
This viewgraph presentation reviews the Stardust mission . The objectives of the mission is to rendezvous with the Wild 2 comet , and using a specially designed aerogel capture some of the cometary material , and then return a capsule with the material to Earth . Other objectives are to provide images of the comet , and capture interstellar dust . There is a description of the aerogel , the trajectory , and views of the Stardust Sample Return Capsule ( SRC ) , Cometary and Interstellar Dust Analyzer ( CIDA ) instrument , and the JPL designed camera . Also included is a timeline of the projected release of data to the Planetary Data System .
Runtime verification has primarily been developed and evaluated as a means of enriching the software testing process . While many researchers have pointed to its potential applicability in online approaches to software fault tolerance , there has been a dearth of work exploring the details of how that might be accomplished . In this paper , we describe how a component - oriented approach to software health management exposes the connections between program execution , error detection , fault diagnosis , and recovery . We identify both research challenges and opportunities in exploiting those connections . Specifically , we describe how recent approaches to reducing the overhead of runtime monitoring aimed at error detection might be adapted to reduce the overhead and improve the effectiveness of fault diagnosis .
Ilmenite ( FeTiO3 ) is a wide bandgap semiconductor with an energy gap of about 2.5eV. Initial radiation studies indicate that ilmenite has properties suited for radiation tolerant applications , as well as a variety of other electronic applications . Two scanning probe microscopy methods have been used to characterize the surface of samples taken from Czochralski grown single crystals . The two methods , atomic force microscopy ( AFM ) and scanning tunneling microscopy ( STM ) , are based on different physical principles and therefore provide different information about the samples . AFM provides a direct , three - dimensional image of the surface of the samples , while STM give a convolution of topographic and electronic properties of the surface . We will discuss the differences between the methods and present preliminary data of each method for ilmenite samples .
This viewgraph presentation describes tether - cutting reconnection in the production of Coronal Mass Ejections ( CMEs ) . The topics include : 1 ) Birth and Release of the CME Plasmoid ; 2 ) Resulting CME in Outer Corona ; 3 ) Governing Role of Surrounding Field ; 4 ) Testable Prediction of the Standard Scenario Magnetic Bubble CME Model ; 5 ) Lateral Pressure in Outer Corona ; 6 ) Measured Angular Widths of 3 CMEs ; 7 ) LASCO Image of each CME at Final Width ; 8) Source of the CME of 2002 May 20 ; 9 ) Source of the CME of 1999 Feb 9 ; 10 ) Source of the CME of 2003 Nov 4 ; and 11 ) Test Results .
PRISM is an airborne pushbroom imaging spectrometer intended to address the needs of airborne coastal ocean science research . Its critical characteristics are high throughput and signal - to - noise ratio , high uniformity of response to reduce spectral artifacts , and low polarization sensitivity . We give a brief overview of the instrument and results from laboratory calibration measurements regarding the spatial , spectral , radiometric and polarization characteristics .
The goal of this talk is to extend our recently developed highly parallelizable nonlinear stable high order schemes for complex multiscale hydrodynamic applications to the viscous MHD equations . These schemes employed multiresolution wavelets as adaptive numerical dissipation controls to limit the amount and to aid the selection and/or blending of the appropriate types of dissipation to be used . The new scheme is formulated for both the conservative and non - conservative form of the MHD equations in curvilinear grids .
HPCMP CREATE - AV Conservative Field Finite Element ( COFFE ) is a modular , extensible , robust numerical solver for the Navier - Stokes equations that invokes modularity and extensibility from its first principles . COFFE implores a flexible , class - based hierarchy that provides a modular approach consisting of discretization , physics , parallelization , and linear algebra components . These components are developed with modern software engineering principles to ensure ease of uptake from a user 's or developer 's perspective . The Streamwise Upwind / Petrov - Galerkin ( SU / PG ) method is utilized to discretize the compressible Reynolds - Averaged Navier - Stokes ( RANS ) equations tightly coupled with a variety of turbulence models . The mathematics and the philosophy of the methodology that makes up COFFE are presented .
Multiple liquid metal pump options are reviewed for the purpose of determining the technologies that are best suited for inclusion in a nuclear reactor thermal simulator intended to rest prototypical space nuclear surface power system components . Conduction , induction and thermoelectric electromagnetic pumps are evaluated based on their performance characteristics and the technical issues associated with incorporation into a reactor system . A thermoelectric electromagnetic pump is selected as the best option for use in NASA - MSFC 's Fission Surface Power - Primary Test Circuit reactor simulator based on its relative simplicity , low power supply mass penalty , flight heritage , and the promise of increased pump efficiency over those earlier pump designs through the use of skutterudite thermoelectric elements .
As part of NASA s Intelligent Flight Control Systems program , parameter identification experiments were carried out with NASA Dryden s F-15B TN 837 aircraft . The canard control surfaces , whose movement is highly correlated with aircraft angle of attack , and the aircraft s aerodynamic instability in the pitch axis contribute to making parameter identification challenging . The equation - error method of analysis is applied to several longitudinal parameter identification maneuvers and a new approach for compensating for flight - data signal time lags is developed , which improves the accuracy and consistency of the results .
As next - generation exascale - class systems arrive , existing software must be updated accordingly to effectively utilize these systems . For high concurrency and energy efficiency , many of these systems utilize GPU architectures . In this work , we present a CUDA C++ implementation of FUN3D 's thermochemical nonequilibrium capability for turbulent flows . Efficiency is demonstrated at scale using the Summit system at the Oak Ridge Leadership Computing Facility which is representative of future exascale systems . This work enables faster , higher fidelity , and scale - resolving simulations of thermochemical nonequilibrium flows including reentry , hypersonics , and combustion .
A thermodynamic study of the thermal stability of conventional terrestrial minerals in a hypothetical lunar atmosphere has opened some interesting speculation . Much of the Earth 's crust is composed of oxides of silicon , aluminum , magnesium , and related compounds . These crust components may be as much a product of the Earth 's atmosphere as vegetation and animal life . Though inanimate and long considered imperishable , these materials are stable under conditions of an atmosphere equivalent to 34 ft of water at sea level and persist under adverse conditions of moisture and temperature to altitudes of roughly 29,000 ft above sea level . The oxygen content averages 21 % ) and the oxygen partial pressure would be roughly 1/5 atm .
The primary focus of my presentation is the development of the jet noise prediction code JeNo with most examples coming from the experimental work that drove the theoretical development and validation . JeNo is a statistical jet noise prediction code , based upon the Lilley acoustic analogy . Our approach uses time - average 2 - D or 3 - D mean and turbulent statistics of the flow as input . The output is source distributions and spectral directivity .
Orbit maintenance is the series of burns performed during a mission to ensure the orbit satisfies mission constraints . Low - altitude missions often require non - trivial orbit maintenance ( Delta)V due to sizable orbital perturbations and minimum altitude thresholds . A strategy is presented for minimizing this ( Delta)V using impulsive burn parameter optimization . An initial estimate for the burn parameters is generated by considering a feasible solution to the orbit maintenance problem . An example demonstrates the dV savings from the feasible solution to the optimal solution .
We have observed a new temperature - entropy wave that propagates opposite to the direction of a steady heat flux Q when the helium column is heated from above . This propagating mode is due to non - linear thermo - conductance of the helium sample in the self - organized state . Such a mode had been predicted to exist on the self - organized heat transport state for Q less than about 100 nW / sq cm . We confirm that this mode exists in this regime . However , we also observe that it propagates even when the helium is pushed away from the self - organized heat transport state into the normal state .
NASA Ames Research Center has been studying the feasibility of vertical lift aerial vehicles to support planetary science and exploration missions . Besides Earth , it appears that there are three planetary bodies within our solar system where vertical flight might not only be theoretically feasible , but would also have unique mission capabilities that no other platform ( ground - based , aerial , or orbital ) could provide . Several vertical lift vehicle configurations might be applicable for planetary science missions . This paper presents a few representative conceptual design cases and the design challenges inherent in their development . Finally , more detailed comments are directed to the issues inherent in developing a NASA Mars Scout mission employing the use of a Martian autonomous rotorcraft .
Highly loaded composite struts , representative of structural elements of a proposed truss - based lunar lander descent stage concept , were selected for design , development , fabrication and testing under NASA s Advanced Composites Technology program . The focus of this paper is the development of a capability for experimental evaluation of the structural performance of these struts . Strut lengths range from 60 to over 120 inches , and compressive launch and ascent loads can exceed -100,000 lbs , or approximately two times the corresponding tensile loads . Allowing all possible compressive structural responses , including elastic buckling , were primary considerations for designing the test hardware .
A crucial step in planet formation is the growth of solid bodies in the sub - millimeter to meter size range : too large to condense directly from the gas phase and too small to interact meaningfully through mutual gravitation . The existence of planets in our solar system demands that some growth process once operated in that size regime , but the mechanism has not been positively identified . Whatever it was , it worked despite nebular turbulence that was probably strong enough to break dust structures cohering by weak surface forces and to disrupt small - scale gravitational collapse via the Goldreich - Ward mechanism . Recent work on this topic , reviewed in , has focussed on ice and frost in the laboratory , silicate dust in drop - tower and orbital microgravity environments , and numerically modelled magnetic particles .
" Theory and simulations of solar system plasmas " aims to highlight results from microscopic to global scales , achieved by theoretical investigations and numerical simulations of the plasma dynamics in the solar system . The theoretical approach must allow evidencing the universality of the phenomena being considered , whatever the region is where their role is studied ; at the Sun , in the solar corona , in the interplanetary space or in planetary magnetospheres . All possible theoretical issues concerning plasma dynamics are welcome , especially those using numerical models and simulations , since these tools are mandatory whenever analytical treatments fail , in particular when complex nonlinear phenomena are at work . Comparative studies for ongoing missions like Cassini , Cluster , Demeter , Stereo , Wind , SDO , Hinode , as well as those preparing future missions and proposals , like , e.g. , MMS and Solar Orbiter , are especially encouraged .
The ISS - RAD instrument was activated on ISS on February 1st , 2016 . Integrated in ISS - RAD , the Fast Neutron Detector ( FND ) performs , for the first time on ISS , routine and precise direct neutron measurements between 0.5 and 8 MeV. Preliminary results for neutron dose equivalent and neutron flux energy distributions from online / on - board algorithms and offline ground analyses will be shown , along with comparisons to simulated data and previously measured neutron spectral data . On - orbit data quality and pre - launch analysis validation results will be discussed as well .
The TSIS instrument has been measuring solar irradiance on a continual basis since January 2018 as an external payload on the ISS . In 2014 when TSIS was directed to fly on the ISS , the jitter environment was highly uncertain , so TSIS designed a robust gimbaled pointing system that showed excellent disturbance attenuation throughout the design , test , and on - orbit phases of the program . This paper discusses how TSIS accounted for this uncertain jitter environment through - out the life of the program . TSIS was able to measure the ISS jitter during commissioning and determined that it was a relatively benign environment less than 4 arcseconds 1σ at low frequencies ( < 0.5 Hz ) . More importantly , the measured pointing performance of TSIS was consistently found to be 4 arcseconds 1σ , which easily satisfied the jitter requirement of 60 arcseconds 1σ .
The slide presentation provides an overview of research related to problems in quality evaluation in the mechanisms of wire bond degradation . Case studies presented examine the evaluation of reliability of hermetic and plastic microcircuits with suspected poor wire bonding . The authors conclude that in the cases when destructive physical analysis ( DPA ) or design evaluation indicate possible problems with wire bonding , a wire bond qualification testing may be required . This test should include high temperature storage ( 175 degrees C to 200 decrees C ) of the parts with periodic measurements of contact resistances followed by internal examination and wire pull or ball sear testing .
Proper Generalized Decomposition ( PGD ) is a reduced order modeling technique for the simulation of physical systems whose governing equations depend on boundary conditions , initial conditions , material properties , and geometric parameters . It uses separated representations of system covariates combined with an iterative approximation method known as successive enrichment in order to compute an accurate parameter - dependent approximation to the full governing equations . PGD can also be used as an alternative to the Singular Value Decomposition ( SVD ) of a matrix and therefore as an alternative to PCA thermography . In this paper PGD was used to analyze data derived from the inspection of a composite fuselage forward section using flash thermography , and the results were compared against the standard PCA approach .
We observed the 2 July 2019 total solar eclipse with a variety of imaging and spectroscopic instruments recording from three sites in mainland Chile : on the centerline at La Higuera , from the Cerro Tololo Inter - American Observatory , and from La Serena , as well as from a chartered flight at peak totality in mid - Pacific . Our spectroscopy monitored Fe X , Fe XIV , and Ar X lines , and we imaged Ar X with a Lyot filter adjusted from its original H - alpha bandpass . Our composite imaging has been compared with predictions based on modeling using magnetic - field measurements from the pre - eclipse month . Our time - differenced sites will be used to measure motions in coronal streamers .
This paper presents a novel , end - to - end fully integrated system being developed at JPL that is called SCAIP . SCAIP enables a rover to autonomously travel to a designated science target   from an extended distance away , and precisely place an instrument on that target with a single command without additional human interaction .