silkski/ENERAD huggingface dataset:
With advancements in CubeSat technologies and low - cost launch opportunities , CubeSats could play a role in meeting NASA ’s key Earth science measurement objectives , especially in extreme weather and ecosystem processes . In this paper , we discuss the development of “ science grade ” hyperspectral imager , microwave spectrometer , IR sounder , and Ka - band radar instruments at JPL . They are scheduled to launch in early to late 2018 while the hyperspectral imager is being developed for airborne flights and for space in the future . The limitations in power , mass , and volume imposed by the CubeSat platform required the identification of new technologies in order to miniaturize instruments into a specific form factor . In conclusion , we will summarize strategies to implement small and low - cost instruments and suggest an architecture for enabling a constellation of U - class instruments .
The Thermal Infrared Sensor 2 ( TIRS-2 ) will fly aboard the Landsat 9 spacecraft and leverages the Thermal Infrared Sensor ( TIRS ) design currently flying on Landsat 8 . TIRS-2 will provide similar science data as TIRS , but is not a buildto - print rebuild due to changes in requirements and improvements in absolute accuracy . The heritage TIRS design has been modified to reduce the influence of stray light and to add redundancy for higher reliability over a longer mission life . The TIRS-2 development context differs from the TIRS scenario , adding to the changes . The TIRS-2 team has also learned some lessons along the way .
GRACE is unique among remote sensing systems in its ability to " see " below the first few centimeters of the land surface , and it has provided the first global observations of total terrestrial water storage variations . Now that we have more than seven years of GRACE measurements , it is tempting to look for trends in the data . Auxiliary information is almost always required in order to arrive at the correct diagnosis of an apparent trend . Here we will present a map of GRACE derived terrestrial water storage tendencies since 2002 and attempt to explain which are likely to continue due to climatic or human pressures , and which are short - term expressions of natural interannual variability .
A sequential filtering algorithm is presented for attitude and attitude - rate estimation from Global Positioning System ( GPS ) differential carrier phase measurements . A third - order , minimal - parameter method for solving the attitude matrix kinematic equation is used to parameterize the filter 's state , which renders the resulting estimator computationally efficient . Borrowing from tracking theory concepts , the angular acceleration is modeled as an exponentially autocorrelated stochastic process , thus avoiding the use of the uncertain spacecraft dynamic model . The new formulation facilitates the use of aiding vector observations in a unified filtering algorithm , which can enhance the method 's robustness and accuracy . Numerical examples are used to demonstrate the performance of the method .
The paper presents an on - board estimation , navigation and control architecture for multi - rotor drones flying in urban environment . It consists of adaptive algorithms to estimate vehicle 's aerodynamic drag coefficients with respect to still air and the urban wind components along the flight trajectory , with guaranteed fast and reliable convergence to the true values ; navigation algorithms to generate feasible trajectories between given way - points that take into account the estimated wind ; and of control algorithms to track the generated trajectories as long as the vehicle retains sufficient number of functioning rotors capable of compensating for the estimated wind . All components of this on - board system are computationally effective and are intended for a real time implementation . The algorithms were tested in simulations .
NASA Langley Research center is developing key structures and mechanisms technologies for micron - accuracy , in - space deployment of future space instruments . Achieving micron - accuracy deployment requires significant advancements in deployment mechanism design such as the revolute joint presented herein . The joint presented herein exhibits a load - cycling response that is essentially linear with less than two percent hysteresis , and the joint rotates with less than one in.-oz . of resistance . A prototype reflector metering truss incorporating the joint exhibits only a few microns of kinematic error under repeated deployment and impulse loading . No other mechanically deployable structure found in literature has been demonstrated to be this kinematically accurate .
The REST simulator includes many parameters : a ) Inertial < - > Fix to Earth reference system ; b ) Geodetic < - > Geocentric coordinates ; c ) Rotational velocity of the Atmosphere ; d ) Effect of the rotation of the Earth ; e ) Bulge effect of the Earth ; f ) Spherical harmonic expansion for the Earth s gravitational potential , J2 ( zonal ) ; g ) Heat flux , temperature in the wall ; h ) Drag coefficient for different regimes ; i ) Flow regime status ; j ) Density model NRLMSISE-00 ; k ) Wind model HWM-93 ; l ) G2S atmospheric model with the latest meteorological conditions and m ) Landing area ( Monte Carlo Simulations )
The Keck interferometer currently under development will include a midinfrared nulling experiment that is designed to search for extrazodiacal dust around nearby stars . The potential of this technique , as wel1 as the basic experimental approach , will be discussed . The initial goal is to search for extrazodiacal emission around nearby stars at the 10 - solar zodi - equivalent level , with a long - term goal of I solar zodi .
A coordinated experimental and theory / simulation effort has been carried out to investigate the physics of the Traveling Wave Direct Energy Converter ( TWDEC ) , a scheme that has been proposed in the past for the direct conversion into electricity of the kinetic energy of an ion beam generated from fusion reactions . This effort has been focused in particular on the TWDEC process in the high density beam regime , thus accounting for the ion beam expansion due to its space charge .
The NASA Advanced Air Vehicles Program , Commercial Supersonics Technology Project seeks to advance tools and techniques to make over - land supersonic flight feasible . In this study , preliminary computational results are presented for future tests in the NASA Ames 9 foot x 7 foot supersonic wind tunnel to be conducted in early 2016 . Shock - plume interactions and their effect on pressure signature are examined for six model geometries . Near- field pressure signatures are assessed using the CFD code USM3D to model the proposed test geometries in free - air . Additionally , results obtained using the commercial grid generation software Pointwise Reigistered Trademark are compared to results using VGRID , the NASA Langley Research Center in - house mesh generation program .
Simulator studies of the deep - stall problem encountered with modern airplanes are discussed . The results indicate that the basic deep - stall tendencies produced by aerodynamic characteristics are augmented by operational considerations . Because of control difficulties to be anticipated in the deep stall , it is desirable that adequate safeguards be provided against inadvertent penetrations .
The EPOXI mission is a NASA Discovery Mission of Opportunity combining two separate investigations : Extrasolar Planet Observation and Characterization ( EPOCh ) and Deep Impact eXtended Investigation ( DIXI ) . Both investigations reused the DI instruments and spacecraft that successfully flew by the comet Tempel-1 ( 4 July 2005 ) . For EPOCh , the goal was to find exoplanets with the high resolution imager , while for DIXI it was to fly by the comet Hartley 2 ( 4 Nov 2010 ) . This paper documents the navigation experience of the earlier ma - neuver analyses critical for the EPOXI mission including statistical ? V analyses and other useful analyses in designing maneuvers . It also recounts the trajectory design leading up to the final reference trajectory to Hartley 2 .
The physiological and psychological factors of manned space flight had a particular significance in the Skylab missions during which astronauts were subjected to a life in a space environment for longer   periods of time than on previous space missions . The Skylab missions   demonstrated again the great adaptability of human physiology to the   environment of man . The results of Skylab have indicated also approaches for enhancing the capability of man to tolerate the physiological and psychological stresses of space flight .
Communications , Navigation and Surveillance ( CNS ) requirements must be developed in order to establish a CNS architecture supporting Unmanned Air Systems integration in the National Air Space ( UAS in the NAS ) . These requirements must address cybersecurity , future communications , satellite - based navigation and APNT , and scalable surveillance and situational awareness . CNS integration , consolidation and miniaturization requirements are also important to support the explosive growth in small UAS deployment . Air Traffic Management ( ATM ) must also be accommodated to support critical Command and Control ( C2 ) for Air Traffic Controllers ( ATC ) . This document therefore presents UAS CNS requirements that will guide the architecture .
A feasibility study was conducted to explore the applicability of a POD / MAC basis selection technique to a nonlinear structural response analysis . For the case studied the application of the POD / MAC technique resulted in a substantial improvement of the reduced order simulation when compared to a classic approach utilizing only low frequency modes present in the excitation bandwidth . Further studies are aimed to expand application of the presented technique to more complex structures including non - planar and two - dimensional configurations . For non - planar structures the separation of different displacement components may not be necessary or desirable .
An efficient strategy for propagating sonic boom signatures from a near - field Computational Fluid Dynamics ( CFD ) solution to the mid - field is presented . The method is based on a high - order accurate finite - difference discretization of the 3D Euler equations on a specially designed curvilinear grid and a single sweep space marching solution algorithm . The new approach leads to more than a factor of two reduction in overall computational resources compared to the current method used to propagate near - field sonic booms to the ground . Accuracy and efficiency of the near - field to mid - field process is demonstrated using a selection of test cases from the AIAA Sonic Boom Prediction Workshops . Azimuthal dependence of nonlinear wave propagation from the near - field to mid - field is analyzed along with its effects on the ground level noise .
NASA 's Advanced Composites Project is investigating technologies that increase automated remote inspection of aircraft composite structures . Therefore , microwave Frequency Domain Reflectometry ( FDR ) is being investigated as a method of enabling rapid remote measurement of strain occurring at the first ply of a composite fiber reinforced polymer ( CFRP ) structure using Radio Frequency ( RF ) Electro - Magnetic ( EM ) radiation . While microwave reflectometry has been used to detect disbonds in CFRP structures , its use in detecting strain has been limited . This work will present data demonstrating the measurement of the reactance changes due to loading conditions that are indicative of strain in a CFRP structure . In addition , the basic EM signature will be presented along with an analysis of temperature and humidity effects .
The testing of a thermal protection system ( TPS ) in multiple arc jets and laser facilities is critical not only to determine the ability of a material to withstand the harsh aerothermal environments but is also required to collect relevant data that allows construction of a thermal response model of the TPS for flight design . The present talk provides an overview of recent arcjet testing of the HEEET material , one of the families of materials from the 3D Woven TPS program , being developed under NASAs Heatshield for Extreme Entry Environment Technology ( HEEET ) project .
Pure metallic hydrogen is predicted to have a specific impulse ( Isp ) of 1700 seconds , but the reaction temperature is too high for current engine materials . Diluting metallic hydrogen with liquid hydrogen can reduce the reaction temperature to levels compatible with current material limits and still provide an Isp greater than 900 s. Metallic hydrogen has not yet been produced on earth , but experimental techniques exist that may change this situation . This paper will provide a brief description of metallic hydrogen and the status of experiments that may soon produce detectable quantities of this material in the lab . Also provided are some characteristics for diluted metallic hydrogen engines and launch vehicles .
Handling qualities have always been vitally important to the pilot . Before the current series of lifting body flight tests , there was speculation and concern about how this class of wingless vehicle would handle . The general behavior of the three lifting bodies in flight is described in broad terms in this paper , and some specific examples of behavior that may be of special interest from the pilot 's viewpoint are presented . In addition , comments are offered concerning simulation requirements .
As the operation of large systems becomes ever more dependent on extensive automation , the need for an effective solution to the problem of design and validation of the underlying software becomes more critical . Large systems possesses much detailed structure , typically hierarchical , and they are hybrid . Information processing at the top of the hierarchy is by means of formal logic and sentences ; on the bottom it is by means of simple scalar differential equations and functions of time ; and in the middle it is by an interacting mix of nonlinear multi - axis differential equations and automata , and functions of time and discrete events . The lecture will address the overall problem as it relates to flight vehicle management , describe the middle level , and offer a design approach that is based on Differential Geometry and Discrete Event Dynamic Systems Theory .
The Wilcox 2006 stress - omega model ( also referred to as WilcoxRSM - w2006 ) has been implemented in the NASA Langley code CFL3D and used to study a variety of 2 - D and 3 - D configurations . It predicted a variety of basic cases reasonably well , including secondary flow in a supersonic rectangular duct . One- and two - equation turbulence models that employ the Boussinesq constitutive relation were unable to predict this secondary flow accurately because it is driven by normal turbulent stress differences . For the NASA trapezoidal wing at high angles of attack , the WilcoxRSM - w2006 model predicted lower maximum lift than experiment , similar to results of a two - equation model .
The global modeling of plasmaspheric plasma has remained fairly rudimentary over the last 30 - years , owing to our limited ability to validate model results experimentally . The realization that voids and filamentary structures covering a range of scales sizes are formed in the distribution of thermal plasma has only been possible with global imaging and enables entirely new advances in modeling the near Earth space environment . Advances in modeling in the context of these new observations will be presented and discussed .
This viewgraph presentation reviews changes that are required in Space Transportation . This new transportation paradigm from the reliance on the Space Shuttle to a mixture of space transportation vehicles , i.e. , the Russian Progress , vehicle , the Japanese HTV , the European ATV and other commercial orbital transportation systems , requires a new cultural paradigm . This new paradigm is outlined , and reviewed .
Nuclear Thermal Propulsion ( NTP ) is under consideration for potential use in deep space exploration missions due to desirable performance properties such as a high specific impulse ( > 850 seconds ) . Tungsten ( W)-60vol%UO2 cermet fuel elements are under development , with efforts emphasizing fabrication , performance testing and process optimization to meet NTP service life requirements [ 1 ] . Fuel elements incorporate design features that provide redundant protection from crack initiation , crack propagation potentially resulting in hot hydrogen ( H2 ) reduction of UO2 kernels . Fuel erosion and fission product retention barriers include W coated UO2 fuel kernels , W clad internal flow channels and fuel element external W clad resulting in a fully encapsulated fuel element design as shown .
In this paper we will discuss : the steps for adequately designing such a complex telecommunications system ' Smart Data Node In The Sky ( SDNITS ) ' ; algorithm development for this process ;   specifications to be levied on the interfacing subsystems ; type of the system e.g. , the usual Radio Frequency system or a laser communications system .
This paper presents new results of a flight test of the L1 adaptive control architecture designed to directly compensate for significant uncertain cross - coupling in nonlinear systems . The flight test was conducted on the subscale turbine powered Generic Transport Model that is an integral part of the Airborne Subscale Transport Aircraft Research system at the NASA Langley Research Center . The results presented include control law evaluation for piloted offset landing tasks as well as results in support of nonlinear aerodynamic modeling and real - time dynamic modeling of the departure - prone edges of the flight envelope .
The Devana Chasma quadrangle ( V-29 ; 0 - 25degN/270 - 300degE ) is situated over the northeastern apex of the Beta - Atla - Themis ( BAT ) province and includes the southern half of Beta Regio , the northern and transitional segments of the Devana Chasma complex , the northern reaches of Phoebe Regio , Hyndla Regio , and Nedolya Tesserae , and several smaller volcano - tectonic centers and impact craters .
In this paper , the design of a beacon transmitter that will be flown as a hosted payload on a geostationary satellite to enable propagation experiments at Q - band ( 37 - 41 GHz ) frequencies is presented . The beacon uses a phased locked loop stabilized dielectric resonator oscillator and a solid - state power amplifier to achieve the desired output power . The satellite beacon antenna is configured as an offset - fed cut - paraboloidal reflector .
Loss of control remains one of the largest contributors to aircraft fatal accidents worldwide . Aircraft loss - of - control accidents are highly complex in that they can result from numerous causal and contributing factors acting alone or ( more often ) in combination . Hence , there is no single intervention strategy to prevent these accidents . This paper presents future system concepts and research directions for preventing aircraft loss - of - control accidents .
The large transequatorial coronal hole that was observed in the solar corona at the end of August 1996 is presented . It consists of a north polar coronal hole called the ' elephant 's trunk or tusk ' . The observations of this coronal hole were carried out with the coronal diagnostic spectrometer onboard the Solar and Heliospheric Observatory ( SOHO ) . The magnetic field associated with the equatorial coronal hole is strongly connected to that of the active region at its base , resulting in the two features rotating at almost the same rate .
We report on the petrography , mineralogy and trace - element abundances of individual carbonate grains in the Early Proterozoic Gunflint BIF ( Banded Iron Formation ) . Trace - element data may be used as environmental recorders of the fluid evolution from which the various carbonate phases precipitated . Additional information is contained in the original extended abstract .
Session JA5 includes short reports concerning : ( 1 ) NASA / NIH Neurolab Collaborations ; ( 2 ) Neurolab Mission : An Example of International Cooperation ; ( 3 ) Neurolab : An Overview of the Planned Scientific Investigations ; ( 4 ) EDEN : A Payload for NEUROLAB , dedicated to Neuro Vestibular Research ; ( 5 ) Neurolab Experiments on the Role of Visual Cues in Microgravity Spatial Orientation ; and ( 6 ) The Role of Space in the Exploration of the Mammalian Vestibular System .
We report our recent developments of antimonide based infrared photodetectors utilizing a complementary barrier infrared detector ( CBIRD ) design . The new generation of devices can operate close to zero bias with the same quantum efficiency as the initial design . 320x256 pixel long - wavelength infrared focal plane arrays utilizing optimized design have been demonstrated with 8.8 µm cutoff wavelength and noise equivalent differential temperature of 26 mK at operating temperature of 80 K for 300 K background and f/2 optics . As CBIRD detectors became valuable candidates for space - based instruments , question of their radiation tolerance became important . Here , we report our investigations of the proton irradiation effects on the photodetector performance .
Nakhlites are unbrecciated , olivine - bearing clinopyroxenites that probably came from Mars . A total of eight nakhlites have been identified , including five recent finds : two samples ( 104 g and 456 g ) from the hot desert of Morocco ( NWA 817 and NWA 998 ) , and three samples , a total weight of approx.15 kg , from the Yamato Mountains of Antarctica ( Y000593 , Y000749 and Y000802 ) . Preliminary isotopic results for Y000593 have been given by Shih et al .. In this report , we present Rb - Sr and Sm - Nd isochron data for Y000593 and discuss the age correlation with other nakhlites and the timing of aqueous alteration on Mars .
We present comparisons between numerical simulations of Fe II emission spectra and HST high - resolution and signal - to - noise spectra of the Eta Carinae Weigelt B & D blobs . The spectra show a wealth of FeII and [ FeII ] lines . We investigate the dependence of the spectrum on electron density and on pumping by blackbody radiation . Using the photoionization code Cloudy we were able successfully reproduce the fluxes of few hundred FeII & [ Fe II ] lines in the range from 4000A to 6000A. Fe II emission analysis in Eta Car ejecta is very important because it provides information about excitation conditions , the electron temperature and density solved in a selfconsistent way . Moreover , for the first time we were able to use Fe II emission analysis itself to put limits on CNO abundances in emitting regions .
The Lockheed Blackbirds hold a unique place in the development of aeronautics . In their day , the A-12 , YF-12 , M-21 , D-21 , and SR-71 variants outperformed all other jet airplanes in terms of altitude and speed . Now retired , they remain the only production aircraft capable of sustained Mach 3 cruise and operational altitudes above 80,000 feet . In this paper the author describes the design evolution of the Blackbird from Lockheed 's early Archangel studies for the Central Intelligence Agency through Senior Crown , production of the Air Force 's SR-71 . He describes the construction and materials challenges faced by Lockheed , the Blackbird 's performance characteristics and capabilities , and the National Aeronautics and Space Administration 's role in using the aircraft as a flying laboratory to collect data on materials , structures , loads , heating , aerodynamics , and performance for high - speed aircraft .