silkski/ENERAD huggingface dataset:
The National Combustion Code ( OpenNCC ) was used to perform non - reacting and two - phase reacting flow computations for a unique pre - filming type LDI-3 fuel injector for a three - cup , nineteen - element flametube configuration . All computations were performed with a consistent approach of mesh - generation , spray modeling , reduced finite - rate kinetics and turbulence - chemistry interaction , as developed for CFD analysis of single - element and multi - element LDI-3 designs with OpenNCC . Emissions and flowfield characteristics were predicted for a generic NASA N+3 engine cycle , with particular focus on the 7 % and 30 % ICAO power operating conditions . For both the conditions studied , the CFD analysis provided very good predictions for EINOx when compared with experimental data measured at NASA Glenn Research Center .
The Dust , Thermal and Radiation Engineering Measurement ( DTREM ) packages ( figure 1 ) mounted on the central stations of the Apollo 11 , 12 , 14 , and 15 ALSEPs ( Apollo Lunar Surface Experiments Packages ) measured the outputs of exposed solar cells and thermistors over time . The goal of the experiment , also commonly known as the dust detector , was to study the long - term effects of dust , radiation , and temperature at the lunar surface on solar cells . The monitors returned data for up to almost 8 years from the lunar surface .
Wark - Lovering ( WL ) rims are thin multi - layered mineral sequences that surround many CAIs . These rim layers consist of the primary minerals found in the CAI interiors , but vary in their mineralogy . Several models for their origin have been proposed including condensation , reaction with a nebular gas , evaporation , or combinations of these . However , there still is little consensus on how and when the rims formed . Here , we describe the microstructure and mineralogy of a WL rim on a type B CAI from the Vigarano CV(sub red ) chondrite using FIB / TEM to better understand the astrophysical significance of WL rim formation .
This slide presentation visualizes the NASA space center and research facility sites , as well as the geography , launching sites , launching pads , rocket launching , pre - flight activities , and space shuttle ground operations located at NASA Kennedy Space Center . Additionally , highlights the international involvement behind the International Space Station and the space station mobile servicing system . Extraterrestrial landings , surface habitats and habitation systems , outposts , extravehicular activity , and spacecraft rendezvous with the Earth return vehicle are also covered .
Main stream industry software development practice has gone from a traditional waterfall process to agile iterative development that allows for fast response to customer inputs and produces higher quality software at lower cost . How can we , the space ops community , adopt state of the art software development practice , achieve greater productivity at lower cost , and maintain safe and effective space flight operations ? At NASA Ames , we are developing Mission Control Technologies Software , in collaboration with Johnson Space Center ( JSC ) and , more recently , the Jet Propulsion Laboratory ( JPL ) .
Heavy - ion latchup is investigated for analog - to - digital converters . Differences in cross section for various ions shows that charge is collected at depths beyond 50 um , causing the   cross section to be underestimated unless long - range ions are used . Current distributions and thermal imaging were used to identify latchup - sensitive regions . Latchup in one of the   circuittypes was catastrophic , even when the power was turned off within 10 ms of a latchup event .
HiPAT is a Penning - Malmberg trap designed to contain 10(exp 12 ) particles diagnostics of the plasma . Destructive particle detection is performed by extracting trapped ions from HiPAT and colliding them with a microchannel plate detector ( providing number and energy information ) . The improved RF system has been used to detect various plasma modes for both electron and ion plasmas in the two traps at MSFC , including axd , cyclotron , and diocotron modes . New diagnostics are also being added to HiPAT to measure the axial density distribution of the trapped cloud to match measured RF plasma modes to plasma conditions . In addition , plasma modeling efforts have been started using the XOOPIC code .
This paper describes a training program to provide Early Career Hires ( ECHs ) in the aerospace industry with real , rapid , hands - on exposure to multiple phases and multiple disciplines of flight project development . Such a program has become necessary to close the Generation Gap and ensure that aerospace organizations maintain a highly skilled workforce as experienced personnel begin to retire . This paper discusses the specific motivations for and implementation of such a program at the Jet Propulsion Laboratory . However , the essential features are widely applicable to other NASA centers and organizations delivering large llight systems . This paper details the overall program concept , stages of participation by an ECH , oversight and mentoring , program assessment , training project selection , and facilities requirements .
A novel apparatus for determining the viscosity and electrical conductivity of semiconducting liquids has been developed at NASA / MSFC . The apparatus is based on the transient torque technique and utilizes a 125 micrometer diameter quartz fiber as a torsion wire and a sensitive angular detector to measure the deflection angle of the crucible containing the liquid . A rotating flow is induced in the semiconducting melt by the application of a rotating magnetic field and measurement of the magnitude and transient behavior of the induced deflection angle allows the simultaneous determination of the viscosity and electrical conductivity of the melt . Measurements at room temperature and up to 900 C were made on high purity melts .
The HZETRN code has been identified by NASA for engineering design in the next phase of space exploration highlighting a return to the Moon in preparation for a Mars mission . In response , a new series of algorithms beginning with 2005 HZETRN , will be issued by correcting some prior limitations and improving control of propagated errors along with established code verification processes . Code validation processes will use new / improved low Earth orbit ( LEO ) environmental models with a recently improved International Space Station ( ISS ) shield model to validate computational models and procedures using measured data aboard ISS . These validated models will provide a basis for flight - testing the designs of future space vehicles and systems of the Constellation program in the LEO environment .
A NASA Mars technology project is described that is building a prototype embedded real time Mars approach navigation capability which can be hosted on the Mars Network 's Electra transceiver . The paper motivates the reason for doing real time Mars approach navigation via a set of analyses demonstrating its utility for enabling Mars pin - point landing ( less than 1 - km landing error ) . The development approach , software design , and test results are discussed . Finally , the way forward towards a flight demonstration on the Mars Science Laboratory ( MSL ) is presented .
The latest improvements and results generated by ENSAERO - MPI are presented in this paper . ENSAERO - MPI is a parallelized , high - fidelity , multi - block code with fluids , structures and controls capabilities developed at NASA Ames Research Center under the support of HPCC . It is capable of multidisciplinary simulations by simultaneously integrating the Navier - Stokes equations , the finite element structural equations as well as control dynamics equations using aeroelastically adaptive , patched grids . Improvements have been made to the code 's robustness , moving grid capabilities and performance .
In January 1988 , representatives from NASA , NOAA , academia , and industry gathered at the NASA Langley Research Center to assess the status of understanding of the sonic boom which accompanies supersonic flight . As a result of that meeting , a research program on sonic boom within the NASA High - Speed Research ( HSR ) Program was implemented . This paper discusses the elements of the sonic - boom program , progress which has been made since 1988 , and the current change in direction for the Sonic - Boom Element of the NASA HSR Program .
Whether putting rovers on Mars or sustaining life in extreme conditions , NASA develops technologies to solve some of the most difficult challenges ever faced . Through its Technology Transfer Program , the agency makes the innovations behind space exploration available to industry , academia , and the general public . This paper describes the primary mechanisms through which NASA disseminates technology to solve real - life problems ; illustrates recent program accomplishments ; and provides examples of spinoff success stories currently impacting everyday life .
Since 1997 , Desert Research and Technology Studies ( D - RATS ) has conducted hardware and operations tests in the Arizona desert that advance human and robotic planetary exploration capabilities . D - RATS 2010 ( 8/31 - 9/13 ) simulated geologic traverses through a terrain of cinder cones , lava flows , and underlying sedimentary units using a pair of crewed rovers and extravehicular activities ( EVAs ) for geologic fieldwork . There were two sets of crews , each consisting of an engineer / commander and an experienced field geologist drawn from the academic community . A major objective of D - RATS was to examine the functions of a science support team , the roles of geologist crewmembers , and protocols , tools , and technologies needed for effective data collection and sample documentation . Solutions to these problems must consider how terrestrial field geology must be adapted to geologic fieldwork during EVAs
NASA space exploration should largely address a problem class in reliability and risk management stemming primarily from human error , system risk and multi - objective trade - off analysis , by conducting research into system complexity , risk characterization and modeling , and system reasoning . In general , in every mission we can distinguish risk in three possible ways : a ) known - known , b ) known - unknown , and c ) unknown - unknown . It is probably almost certain that space exploration will partially experience similar known or unknown risks embedded in the Apollo missions , Shuttle or Station unless something alters how NASA will perceive and manage safety and reliability
The objective of NASA 's Microgravity Research Program is to utilize the low gravity environment of space to explore the nature of physical phenomena that contributes to progress in science and technology on Earth . Under the oversight of NASA Headquarters , the Microgravity Research Program Office ( MRPO ) at the Marshall Space Flight Center ( MSFC ) assumes all program management responsibilities associated with Microgravity Research and Space Product Development . One program management responsibility that plays a vital role to the success of the MRPO is the flight manifesting process for MRPO - sponsored payloads . In this paper , the authors will examine the various processes utilized by MRPO personnel in acquiring flight opportunities for MRPO - sponsored payloads .
This paper will describe the Entry , Descent and Landing simulation tradeoffs and techniques that were used to provide the Monte Carlo data required to approve entry during a critical period just before entry of the Genesis Sample Return Capsule . The same techniques will be used again when Stardust returns on January 15 , 2006 . Only one hour was available for the simulation which propagated 2000 dispersed entry states to the ground . Creative simulation tradeoffs combined with parallel processing were needed to provide the landing footprint statistics that were an essential part of the Go / NoGo decision that authorized release of the Sample Return Capsule a few hours before entry .
The levels of vacuum that proceed past the high vacuum range into the ultra high and then the extremely high vacuum range become more difficult to achieve each decade that a system progresses through . This paper will explore the difficulties and cover some of the design principles used in achieving vacuum levels in the low 10 - 12 torr pressure range . This system was entirely built with commercially - available off the shelf ( COTS ) components . This chamber was designed in 1998 to provide a very low outgassing environment for the processing and sealing of charge - coupled devices ( CCD 's ) for some of the Hubble Space Telescope replacement optics .
Infrared ozone spectra from near nadir observations have provided atmospheric ozone information from the sensor to the Earth 's surface . Simulations of the NPOESS Airborne Sounder Testbed - Interferometer ( NAST - I ) from the NASA ER-2 aircraft ( approximately 20 km altitude ) with a spectral resolution of 0.25 / cm were used for sensitivity analysis . The spectral sensitivity of ozone retrievals to uncertainties in atmospheric temperature and water vapor is assessed in order to understand the relationship between the IR emissions and the atmospheric state . In addition , ozone spectral radiance sensitivity to its ozone layer densities and radiance weighting functions reveals the limit of the ozone profile retrieval accuracy from NAST - I measurements . Statistical retrievals of ozone with temperature and moisture retrievals from NAST - I spectra have been investigated and the preliminary results from NAST - I field campaigns are presented .
Current interest in advanced propulsion within NASA and research activities in advanced propulsion concepts at the Jet Propulsion Laboratory are reviewed .   The concepts , which include   high power plasma thrusters such as lithuim - fueled Lorentz - Force - Accelerators , MEMS - scale propulsion systems , in - situ propellant utilization techniques , fusion propulsion systems and   methods of using antimatter , offer the potential for either significantly enhancing space transportation capability as compared with that of traditional chemical propulsion , or enabling   ambitious new missions .
A developmental test program was conducted for the touchdown event of the Mars Science Laboratory rover . The test hardware consisted of a full - size 3/8th mass scaled test rover , a descent stage mass mock - up , and a Vectran triple - bridle system over 6 meters in length . More than eighty landing tests were performed on terrains of various types , including level rigid surfaces , level and sloped sand surfaces , and level and sloped surfaces with rocks . Landing velocities ranged between 0.4 m / s and 1.4 m / s. A computational model of the landings was developed using the ADAMS analysis program , and validation of this model has been performed through test - analysis comparisons .
The work presented in this paper describes an approach , including a methodology and tools , which allows system engineers to capture failure - related information in a model and generate automatically key failure analysis products : the Failure Modes , Effects and Criticality Analysis ( FMECA ) and the Fault Tree Analysis ( FTA ) . The work has been developed by Tietronix Software , Inc. and the NASA ’s Jet Propulsion Laboratory ( JPL ) , and the resulting auto - generated artifacts shown in this paper demonstrate the ability to obtain powerful reliability and fault management products in a model - based environment .
During the Second Servicing Mission ( SM2 ) of the Hubble Space Telescope ( HST ) severe degradation was observed on the outer layer of the thermal control blankets . Astronaut observations and photographs revealed large cracks in the metallized Teflon(trademark ) FEP ( fluorinated ethylene propylene ) , the outer layer of the multi - layer insulation ( MLI ) , in many locations around the telescope . In an effort to understand what elements of the space environment might cause such damage , pristine Teflon(trademark ) FEP was tested for durability to radiation and thermal cycling . Specimens were subjected to electron and proton fluences comparable to those experienced by HST and were subsequently thermal cycled in a custom - built rapid thermal cycle chamber . Tensile tests of the specimens showed that radiation followed by thermal cycling significantly reduced the ultimate strength and elongation of Teflon(trademark ) FEP .
During the last decade , NASA Ames has been developing new , Ultra - High Temperature Ceramic ( UHTC ) materials for Thermal Protection Systems applications . The UHTC s are a family of materials including compositions of HfE32 and ZrB2 with a Sic second phase . A collaboration with Glenn was recently initiated to evaluate the viability of some UHTC materials that had been produced by an outside vendor for use in gas turbine en,@ne environments . Results from this collaboration have indicated that compositions based on HfB2 show the most promise , among the UHTC compositions evaluated , for use in these environments . Work at ARC has been initiated to fabricate these materials in - house and evaluate methods of improving their properties for use in engine environments .
Smart structures research and development , with the ultimate aim of rapid commercial and military production of these structures , are at the forefront of the Synthesis and Processing of Intelligent Cost - Effective Structures ( SPICES ) program . As part of this ARPA - sponsored program , MDA - E is using fiber placement processes to manufacture integrated smart structure systems . These systems comprise advanced composite structures with embedded fiber optic sensors , shape memory alloys , piezoelectric actuators , and miniature accelerometers . Cost - effective approaches and solutions to smart material synthesis in the fiber - placement process , based upon integrated product development , are discussed herein .
NASA has defined strategic goals to invest in next - generation technologies and innovations , to inspire students to become the future leaders of space exploration , and to expand partnerships with industry and academia around the world . The Crew and Thermal Systems Division ( CTSD ) at the NASA Johnson Space Center actively supports these NASA initiatives . In July 2011 , CTSD created a strategic communications team to communicate CTSD capabilities , technologies , and personnel to internal NASA and external technical audiences for business development and collaborative initiatives , and to students , educators , and the general public for education and public outreach efforts . This paper summarizes the CTSD Strategic Communications efforts and metrics through the first nine months of fiscal year 2012 .
Porous - ceramic , thermal - protection - systems are used heavily in current reentry vehicles like the Orbiter , and they are currently being proposed for the next generation of manned spacecraft , Orion . These materials insulate the structural components and sensitive electronic components of a spacecraft against the intense thermal environments of atmospheric reentry . Furthermore , these materials are also highly exposed to space environmental hazards like meteoroid and orbital debris impacts . This paper discusses recent impact testing up to 9 km / s on ceramic tiles similar to those used on the Orbiter . These tiles have a porous - batting of nominally 8 lb / cubic ft alumina - fiber - enhanced - thermal - barrier ( AETB8 ) insulating material coated with a damage - resistant , toughened - unipiece - fibrous - insulation ( TUFI ) layer .
Simple field - portable white light LED calibration source shows promise for visible range ( 420 - 750 nm ) 1 ) Prototype demonstrated < 0.5 % drift over 10 - 40 C temperature range ; 2 ) Additional complexity ( more LEDs ) will be necessary for extending spectral range into the NIR and SWIR ; 3 ) LED long lifetimes should produce at least several hundreds of hours or more stability , minimizing need for expensive calibrations and supporting long - duration field campaigns ; and 4 ) Enabling technology for developing autonomous sites .
We demonstrate the first polarization maintaining , very - large - mode - area Er - doped fiber amplifier with ~1000 square micron effective area . The amplifier is core pumped by a Raman fiber laser and is used to generate single frequency one microsecond pulses with pulse energy of 368 microJoules , M2 of 1.1 , and polarization extinction greater than 20 dB. The amplifier operates at 1572.3 nm , a wavelength useful for trace atmospheric CO2 detection .
A new method is presented for estimating frequency responses and their uncertainties from wind - tunnel data in real time . The method uses orthogonal phase - optimized multi- sine excitation inputs and a recursive Fourier transform with a least - squares estimator . The method was first demonstrated with an F-16 nonlinear flight simulation and results showed that accurate short period frequency responses were obtained within 10 seconds . The method was then applied to wind - tunnel data from a previous aeroelastic test of the Joined- Wing SensorCraft . Frequency responses describing bending strains from simultaneous control surface excitations were estimated in a time - efficient manner .
2-(Dimethylamino)ethylazide was identified by Darren Thompson of the US Army Aviation Missile Command ( AMCOM ) as a promising candidate to replace hydrazine derivatives in certain hypergolic fuel applications , and as a monopropellant using a heated catalyst bed . The preparation of the material has been scaled up to the pilot plant level , and evaluations of its relevant properties have indicated that it may have broader application than was originally foreseen . Physical , chemical , and hazards properties are reported in this paper
This paper examines three NASA science data archive systems from the Earth , planetary , and astronomy domains , and discusses the various efforts underway to provide their science communities with not only better access to their holdings , but also with the services they need to interpret the data and understand their physical meaning . The paper identifies problems common to all three domains and suggests ways that common standards , technologies , and even implementations be leveraged to benefit each other .
Semi - empirical models of hole diameter and tip - to - tip crack length for different multi - wall shielding systems currently under development for the International Space Station are presented . These equations were developed using light gas gun test data at impact velocities of 6.5 km / s and inhibited shaped charge test data for an impact velocity of 11.3 km / s. These models are incorporated into a survivability analysis using the manned spacecraft crew survivability computer code to determine whether or not module unzipping or crew incapacitation would occur under a specific set of impact conditions .
This viewgraph document summarizes the workings of the Advanced Extravehicular Activity ( AEVA ) Breakout group in a Martian environment . The group was tasked with : identifying potential contaminants and pathways for AEVA systems with respect to forward and backward contamination ; identifying plausible mitigation alternatives and obstacles for pertinent missions ; identifying topics that require further research and technology development and discuss development strategies with uncertain Planetary Protection ( PP ) requirements ; Identifying PP requirements that impose the greatest mission / development costs ; Identifying PP requirements / topics that require further definition ;