software tech briefs september 2013

September 2013

Special Supplement to

Sponsored by

Co-sponsored by

Inside: 40 New Software Programs

Picking the Pattern for a Stealth Antenna

Cov ToC + – ➭

➮

AIntro

http://www.abpi.net/ntbpdfclicks/l.php?201309SSP3



© Copyright 2013 COMSOL. COMSOL, COMSOL Multiphysics, Capture the Concept, COMSOL Desktop, and LiveLink are either registered trademarks or trademarks of COMSOL AB. All other trademarks are the property of their

Verify and optimize your COMSOL Multiphysics. ®

RF DESIGN:

Cov ToC + – ➭

➮

AIntro

designs with

Multiphysics tools let you build simulations that accurately replicate the important characteristics of your designs. The key is the ability to include all physical eff ects that exist in the real world.

To learn more about COMSOL Multiphysics, visit www.comsol.com/introvideo

ELECTRICALAC/DC ModuleRF ModuleWave Optics ModuleMEMS ModulePlasma ModuleSemiconductor Module

MECHANICALHeat Transfer ModuleStructural Mechanics ModuleNonlinear Structural Materials ModuleGeomechanics ModuleFatigue ModuleMultibody Dynamics ModuleAcoustics Module

FLUIDCFD ModuleMicrofl uidics ModuleSubsurface Flow ModulePipe Flow ModuleMolecular Flow Module

CHEMICALChemical Reaction Engineering ModuleBatteries & Fuel Cells ModuleElectrodeposition ModuleCorrosion ModuleElectrochemistry Module

MULTIPURPOSEOptimization ModuleMaterial LibraryParticle Tracing Module

INTERFACINGLiveLink™ for MATLAB®

LiveLink™ for Excel®

CAD Import ModuleECAD Import ModuleLiveLink™ for SolidWorks®

LiveLink™ for SpaceClaim®

LiveLink™ for Inventor®

LiveLink™ for AutoCAD®

LiveLink™ for Creo™ ParametricLiveLink™ for Pro/ENGINEER®

LiveLink™ for Solid Edge®

File Import for CATIA® V5

Product Suite

COMSOL Multiphysics

Free Info at http://info.hotims.com/45607-914

Cov ToC + – ➭

➮

AIntro



F E A T U R E S

4 Picking the Pattern for a Stealth Antenna

D E S I G N & A N A L Y S I S S O F T W A R E

6 Simulation and Analysis Drive TransmissionDevelopment

8 Conjugate Thermal Analysis of a Generic LED Light Bulb

10 Analysis of Spiral Resonator Filters

11 Enigma Version 12

12 ISSM: Ice Sheet System Model

12 Planetary Protection Bioburden Analysis Program

13 Micrometeoroid and Orbital Debris (MMOD) ShieldBallistic Limit Analysis Program

13 Wing Leading Edge RCC Rapid Response DamagePrediction Tool (IMPACT2)

14 Covariance Analysis Tool (G-CAT) for ComputingAscent, Descent, and Landing Errors

E L E C T R O N I C S / C O M P U T E R S

14 Phoenix Telemetry Processor

15 Contact Graph Routing Enhancements Developed inION for DTN

15 Spitzer Telemetry Processing System

15 Advanced Strategic and Tactical Relay RequestManagement for the Mars Relay Operations Service

M E C H A N I C S / M A C H I N E R Y

18 Automated Loads Analysis System (ATLAS)

18 GFEChutes Lo-Fi

19 Integrated Main Propulsion System PerformanceReconstruction Process/Models

P H Y S I C A L S C I E N C E S

19 Sally Ride EarthKAM — Automated Image Geo-Referencing Using Google Earth Web Plug-In

20 Ionospheric Specifications for SAR Interferometry(ISSI)

20 Acoustic Emission Analysis Applet (AEAA) Software

21 Software for Generating Troposphere Correctionsfor InSAR Using GPS and Weather Model Data

21 Implementation of a Wavefront-Sensing Algorithm

22 Advanced Multimission Operations System (ATMO)

I N F O R M A T I O N T E C H N O L O G Y

22 Memory-Efficient Onboard Rock Segmentation

23 Kinect Engineering with Learning (KEWL)

24 Automating Hyperspectral Data for Rapid Responsein Volcanic Emergencies

25 Spacecraft 3D Augmented Reality Mobile App

25 Trade Space Specification Tool (TSST) for RapidMission Architecture (Version 1.2)

26 Raster-Based Approach to Solar Pressure Modeling

27 Space Images for NASA JPL Android Version

28 SIM_EXPLORE: Software for Directed Exploration ofComplex Systems

29 Robot Sequencing and Visualization Program (RSVP)

29 MPST Software: grl_pef_check

30 Real-Time Multimission Event Notification Systemfor Mars Relay

30 Jettison Engineering Trajectory Tool

31 PredGuid+A: Orion Entry Guidance Modified forAerocapture

31 Mobile Timekeeping Application Built on Reverse-Engineered JPL Infrastructure

31 Advanced Query and Data Mining Capabilities forMaROS

32 MPST Software: grl_suppdoc

32 Planning Coverage Campaigns for Mission Designand Analysis: CLASP for DESDynl

32 Space Place Prime

2 www.techbriefs.com Software Tech Briefs, September 2013

September 2013

Supplement to NASA Tech Briefs’ September 2013 issue. Published by Tech Briefs Media Group, an SAE International Company

On the Cover:This model of the swashplate mechanismto control orientation of helicopter rotorblades was developed using the Multi bodyDynamics Module in COMSOL Multiphysicssoftware from COMSOL, Inc. (Burlington,MA). Transient simulation with both rigidand flexible blade designs provides insightinto useful performance metrics such asblade deformation and lift force.

Cov ToC + – ➭

➮

AIntro


Cov ToC + – ➭

➮

AIntro



Picking the Patternfor a Stealth Antenna

For roughly 30 years, the AltranGroup has been a global leaderin innovation and high-techengineering and consulting,

providing services covering every stageof project development — from strategicplanning through manufacturing — tokey players in the aerospace, automo-tive, energy, railway, finance, healthcare,and telecom sectors.

Antenna as the Weak PointThe team works mainly in the aero-

space and defense industry, and hasdeveloped projects related to studies ofantenna placement as well as radarcross-section prediction and control.One of them is addressing one of thelargest leaps in defense technologydeveloped in recent years — stealth air-

planes and ships that avoid radar detec-tion. They generally do so by combiningseveral technologies including the shapeof the target’s surfaces to reflect energyaway from the source, and the use of

radar-absorbent materials. However, if aship’s or aircraft’s antenna is to operateproperly, it cannot be completely cov-ered up — and that makes it one of theremaining components with a largeradar cross-section (RCS), and it canessentially destroy the overall system’sinvisibility to radar.

The RCS depends on the polariza-tion and frequency of the incidentwave. When an electromagnetic wave isincident on a target, electric currentsare induced in the target and a second-ary radiation from that target producesa scattered wave. The scattered field ispartially reflected straight back to thesource of the incident wave, and this isthe principle upon which radar isbased. The peak reflected wave is relat-ed to the standard antenna gain and its

Figure 1: An example of a frequency selective sur-face (FSS) made up of a series of metallic strips.

A frequency selective surface that acts as an RF filter and helpsreduce the radar cross-section of antennas consists of a

pattern of geometrical objects. There are literally thousands ofpossibilities, and testing each one physically would take

enormous amounts of time. With simulation, though,promising candidates can be found in just minutes.

Cov ToC + – ➭

➮

AIntro

Software Tech Briefs, September 2013 www.techbriefs.com 5

peak effective surface area. In this case,there is an ironic twist: antenna design-ers normally look to maximize antennagain, but to lower the RCS, they mustdo the opposite of what they normallydo; specifically, reduce the gain.

One way around this problem is toemploy a frequency selective surface(FSS). It consists of a pattern of shapedholes or surfaces on a substrate, andessentially creates a bandpass filter. Inthe intended frequency range, forinstance where radio operators aretransmitting or receiving, the antennaacts as normal; at other frequencies, theFSS absorbs rather than scatters incidentradiation. Antennas are generallyhoused in a protective enclosure called aradome; for aircraft, often located at thenose. If that enclosure is made of such aFSS, its RCS is significantly reduced at allbut the operating frequencies.

Geometric Patterns as a FilterFrequency selective surfaces are

usually constructed from periodicallyarranged metallic patterns of an arbi-trary geometry. They have openings sim-ilar to patches within a metallic screen(see Figure 1). The performance of aFSS is linked to its shape, thickness,choice of substrate, and the phasingbetween individual elements. AltranGroup focused on the physical configu-rations and the resonant frequencies for certain bandwidths. COMSOLMultiphysics has been an invaluable toolin these studies.

As shown in Figure 1, a FSS consistsof a series of geometrical objects. TheFSS can be electrically large in terms of wavelength with many instances ofthe object, which would make simulat-ing the entire surface extremely cum-bersome and expensive in terms ofcompute power and time. COMSOLMultiphysics has a very convenient

answer to this problem in the PeriodicBoundary Condition (PBC) feature. Itallows the simulation of a single cellunit and thus a less time-consumingprocess (see Figure 2). This featureprovides for continuity of the electricand magnetic fields so the team getsequivalent results as if they had simu-lated an entire array of objects.

Altran realized time and memory sav-ings possible with a PBC while keepingthe level of accuracy necessary to studythe behavior of a given geometry. For asimple structure without a dielectric sub-strate, it is estimated that simulationtime was cut by a factor of 100; for a verylarge electrical structure, this could evenbe 1,000 times or more.

Figure 3 shows an example FSS madeof simple metallic strips surrounded byair. The simulation mesh was created forone of the metallic strips, and the fre-quency plot shows that it has a passbandin the region of 40 GHz. To validate the

simulation, the team first analyzed a casealready dealt with in the literature andreplicated the known results in COM-SOL Multiphysics with the aim of tuningthe simulation procedure. In a secondstep, the team took this same validatedsimulation and modeled other types ofFSS while changing geometries andmaterials, and evaluating the impact ofthese changes on FSS performance.

The software has been used to investi-gate the frequency responses of a varietyof simple shapes and sizes, and how theyare distributed on a surface. It is alsopossible to make the design more com-plicated by using two structures withcomplementary behavior. In this way, adesign can be created with multiple res-onant frequencies.

The ability to try any number ofshapes highlights the capacity of thesoftware to help the team be efficientin finding a good solution. The alterna-tive would be actually fabricating vari-ous shapes for the FSS and physicallytesting them, which would involve farmore time and expense. With model-ing, in a few minutes, the team candetermine if a pattern is worth pursu-ing in detail.

Altran is now starting to expand itsmodel to include the effects of thedielectric substrate. In addition, thecompany hopes to soon start workingwith optimization algorithms to help incases where it face constraints such asmaximum unit cell size.

This article was written by Francesca DeVita, Simone Di Marco, Fabio Costa, and PaoloTurchi of Altran Italy. For more information,visit http://info.hotims.com/45607-126.

Figure 2: PBC functionality from COMSOL significantly speeds up the solution to the FSS study by sim-ulating only a unit cell.

Figure 3: A simple example FSS based on a metallic strip array, with its meshed geometry (right), andfrequency response curve (lower left). The latter shows the S11 parameter in dB, and is at a scale of1010 with a resonance at about 40 GHz. The dip corresponds to maximum transmitted power.

Cov ToC + – ➭

➮

AIntro



Design & Analysis Software

Simulation and Analysis Drive Transmission Development3D software enables design and optimization of complex geometry and structures.Vicura AB, Trollhättan, Sweden, and SpaceClaim Corp., Concord, Massachusetts

Vicura is a developer of manual trans-missions and dry dual clutch transmis-sions, as well as powertrain integrationin a large number of front wheel driveand all wheel drive applications. Thecompany’s engineers are responsible fora broad range of complex simulationand analysis testing including system,structure, and fluid mechanics. Theteam performs critical simulation andanalysis to ascertain the strength, stiff-ness, thermal, and dynamic behaviors ofall possible transmission assemblies andcomponents (housings, shafts, gears,synchronizers, clutches, etc.).

Designs created in CAD software aresent for simulation and analysis. Beforeimporting the designs into a meshing pro-gram, the geometry has to be simplified,and this process was difficult and time-consuming. Often, files would have to besent back and forth to CAD experts, los-ing time — usually days for each iteration.

The company starting using SpaceClaim®’s3D Direct Modeler more than a year ago,and found that it solved many simulationand analysis challenges. When designerssend CAD models, SpaceClaim is used tosort out what to include in the analysis,saving time and improving the simula-tion process.

For each design, the CAD data isopened in SpaceClaim, which removes

features that would complicate themesh, such as rounds, small holes, andgeometry outside the region that needsto be analyzed. When performing CFD,SpaceClaim extracts volumes to be ana-lyzed. Once ready, a Parasolid file is sentto SimLab or to HyperMesh to create amesh and add couplings, contact infor-mation, and boundary conditions.Finally, the mesh is saved as an Abaqusinput file, the preprocessing is complet-

ed, and the simula-tion is run in Abaqus.

Once results areobtained, SpaceClaimis used to modify thegeometry; for exam-ple, adding material,fillets, and bolts untilthere is confidencethat the concept willaddress issues discov-ered in the simula-t i o n . W h e n t h edesign is optimized,the CAD team is senta vers ion of the

model in which they can reconcile thechanges in the detailed model.

Vicura offers customers design andoptimization services to ascertain durabil-ity, noise, and vibration issues and efficien-cy. The company focuses on analysis tooptimize structures for manufacturingfeasibility, stress analysis, and casting opti-mization. Prior to SpaceClaim, if the teamfound that concept work had to be doneon the model, it would be sent back to thedesigner. SpaceClaim provides more flex-ibility and can conduct a quick simula-tion, identify high-stress areas, and makedesign changes.

Customer communications have beenvastly improved, leveraging SpaceClaimwith KeyShot to create realistic render-ings. This approach is used in the bid-ding process and when presentingdesign proposals to the customer. Forcross-section views of large assembliesSpaceClaim enables clarity for discus-sions with the designers.

This work was done by Vicura using softwareby SpaceClaim. For more information, visithttp://info.hotims.com/45607-125.

Figure 1. The Original Design fulfills the requirements, but as much massas possible had to be reduced.

Figure 2. A rendered image of the Final Design using SpaceClaim and KeyShot.

Cov ToC + – ➭

➮

AIntro



Cov ToC + – ➭

➮

AIntro




Conjugate Thermal Analysis of a Generic LED Light BulbThermal and fluid modeling is used to understand temperature fields and airflow around the bulb.Veryst Engineering, LLC, Needham Heights, Massachusetts

The design and application of LED(Light Emitting Diode) lighting solutionsprovides new opportunities for thermo-fluid-mechanical modeling enabled bymultiphysics analysis. A coupled thermaland fluid modeling effort was used tounderstand the temperature fields andairflow around a generic LED light bulb.

There is no question that LED light-ing provides significant advantages overother lighting technologies. In the past,the color quality of LEDs has inhibitedtheir penetration of the lighting indus-try, as the emitted light spectrum wasconsidered to be “colder” than that provided by incandescent lights. LEDmanufacturers, however, implementedstrategies to provide “warmer” colors,removing this obstacle to acceptance.With this accomplished, the significantadvantages of LEDs could show theirworth beyond the steadily improvingenergy efficiency in terms of increasedlumens per Watt. Other substantialadvantages include:

Dramatic increase in lifetime, repre-senting multiples of a compact fluores-cent bulb life and potentially decadesof life beyond an incandescent lightImproved resistance to vibration andtemperature fluctuationsRapid-on performance with no warm-up period

Environmental compatibility withnone of the potential disposal issuesassociated with compact fluorescentbulbsSubstantial design flexibility with theuse of multiple LEDs in a myriad oforientations and geometriesLike all lighting technologies, howev-

er, issues of thermal managementremain. The compact geometry of LEDsemphasizes thermal management, as thelocalization of heat generation negatesthe effect of improved efficiency. Hightemperatures reduce the effective life ofthe LED, and additionally can acceleratematerial degradation and produceundesirable thermal stresses. Heat sinkgeometry and the removal of the veryconcentrated temperatures may be theprimary constraint for many proposedlighting configurations.

Thermal modeling is therefore impor-tant, and the variety of lighting configura-tions results in a large number of poten-tial modeling analyses to ensure long life

and energy efficiency. Analytical heattransfer equations for natural convectionprovide a rough estimate of the LED ther-mal response. However, the complexity ofthe geometry and the need for higheraccuracy necessitate the use of more accu-rate computational modeling. COMSOLMultiphysics is ideally suited for solvingthe coupled thermal, fluid flow, and struc-tural equations, and simulates radiationand natural convection.

Veryst Engineering performed a steadystate conjugate heat transfer simulationon a generic LED light bulb to illustrate afew of the issues associated with appropri-ate thermal design. An image of the bulbis provided in Figure 1. The simulationmodels the single, vertically oriented bulbin a cylindrical enclosure with constantambient temperature. Conductionbetween the LED and bulb body, convec-tion within the enclosure, and radiationbetween surfaces are included.

One-sixth of the LED bulb was mod-eled due to symmetry, and a finer mesh

density was used at the vicinity of the finsto capture the high thermal gradients inthat region. The model involved severalassumptions for simplicity that do notaffect the main observations. The LEDwas assumed to dissipate heat uniformlythroughout its core section. Natural con-vection in the air was modeled using theBousinnesq approximation, and a con-stant heat transfer coefficient wasassumed at the external surfaces of theenclosure. The material properties usedin the model were assumed to be tem-perature-invariant.

Using COMSOL, it is quite straightfor-ward to eliminate the above statedassumptions. It is also possible to addmore physics to the model as needed,such as a thermal structural analysis ofthe resulting stresses, or a Joule heatinganalysis to better capture the heat gener-ation distribution.

One simulation result including theparticle tracing capability of COMSOL isprovided in Figure 2. Particle tracing isused here as a visualization aid only. TheLED was assumed to dissipate 7 Watts.Notice the localization of temperature inthe heat sink portion of the bulb, as wellas the proximate rapid airflow convectingheat away from the bulb. Also notice, how-ever, the low flow velocities in many por-tions of the enclosure, indicating a subop-timal thermal design. The geometry ofthe enclosure can certainly be changed toincrease the influence of natural convec-tion on the removal of heat from the bulb.In addition, the relative large thermal gra-dients above and below the heat sink onthe bulb translate to high thermal stressesin those locations. These secondaryeffects can reduce bulb performance andlife just as effectively as the localized tem-peratures directly at the LED.

Veryst Engineering uses the COMSOLsoftware regularly to evaluate the ther-mal performance of products in addi-tion to LEDs. LED lighting designs areperfect applications for COMSOL multi-physics analysis, as the flexibility of theiruse in a multiplicity of geometries makessuch coupled thermal analyses essentialfor both rapidly implemented and reli-able designs.

This work was done by Nagi Elabbasi,Michael Heiss, and Stuart Brown of VerystEngineering, LLC. For more information,visit http://info.hotims.com/45607-122.

Figure 2. Air Velocity around bulb using particletracing.

Figure 1. Solid Model of the LED bulb.


Cov ToC + – ➭

➮

AIntro



Cov ToC + – ➭

➮

AIntro



Increasing demand for more ad -vanced wireless systems necessitates theintroduction of novel designs that arecapable of simultaneously fulfilling mul-tiple operating and performance crite-ria. The implementation of high-data-rate transmission systems has requiredthe development of innovative designsfor microwave filters that must fit withina reduced volume to allow integration ofmultiple filters in more compact wirelesssystems. Additionally, the filter’s specificpassband frequencies and quality factorsmust be achieved within the system’sgeometrical and topological constraints.

Spiral resonator filters offer one optionfor significantly reduced size compared toconventional ring resonators. An array ofspiral resonators can be directly fabricat-ed on a printed circuit board and becauseof their characteristic response, they canbe designed to occupy minimal volume.

To characterize the operation of thesedevices, a mathematical construct namedthe scattering matrix (S-matrix) is usedthat describes how the RF signal interactswith the device. The signal may reflect,exit other ports, and dissipate via heat orelectromagnetic radiation; the S-matrixrepresents each of these signal paths.The order of this matrix is n × n with nequaling the number of ports in the sys-tem; thus, Sij represents the scattering forthe j input port and the i output portsuch that S11 specifies the ratio of signalreflected from port 1 for an input onport 1, and S21 specifies the response atport 2 due to a signal at port 1.

A compact microstrip filter (seeFigure 1) using spiral resonators wasdesigned to produce a resonant fre-quency of 7.2 GHz (Lim et al.). Amodel was set up using COMSOLMultiphysics (see Figure 2) in which

the microstrip line is represented as aperfect electric conductor (PEC) sur-face on a dielectric substrate, withanother PEC surface on the bottom ofthis substrate acting as a ground plane.Two lumped ports are modeled assmall rectangular faces that bridge thegap between the PEC faces of theground plane and the microstrip lineat each port. A small air domainbounded by a scattering boundary(SBC) surface is added to avoid backreflection of radiated fields and reducethe size of the modeling domain. Themodel includes the dielectric substratedefined as a volume with the relativepermittivity of the dielectric.

The experimental and simulationresults for and over a range of frequen-cies of interest are shown in Figure 3,where S11 specifies the ratio of signalreflected from port 1 for an input on

Analysis of Spiral Resonator FiltersImproved performance coupled with reduced size requires the development of novel filter designs for use in advanced wireless systems.AltaSim Technologies, Columbus, Ohio


Figure 1: Microstrip Filter based on rectangular type spiral resonators etchedon the center line of the microstrip.

Figure 2: Model of the Bandstop Resonator Filter.Some exterior faces are removed for visualization.

Figure 3: Frequency Response of the bandstop spiral resonator filter com-paring experimental measurement (Lim et al.) with COMSOL simulation.

Figure 4: Electric Field below (left) and at (right) Resonant Frequency.

Cov ToC + – ➭

➮

AIntro


port 1, while S21 specifies the response atport 2 due to a signal at port 1.

The simulation results agree well withexperimental data for the transmitted andreflected signals, and demonstrate rejec-tion of frequencies outside the requiredfrequency cutoff. The resonant frequencyis 7.2 GHz and the bandwidth of the stop-band is 0.5 GHz ( 7.1-7.6 GHz), with thereference level of |S21| = -10 dB. A deeprejection band (S21 > -50 dB) is obtainedat the resonant frequency with a steep cut-off; a flat passband (S21< 1.2 dB) is

observed, suggestingthe proposed spiralfilter design has lowinsertion losses, thuslimiting its effect ontransmitted signalwhen integrated intoa circuit.

The data can alsobe visualized by theelectric field distri-bution below and at the resonant fre-quency (see Figure4). Below the reso-nant frequency, ahigh level of signal istransmitted throughthe device; at the res-onant frequency of7.2 GHz, a high level

of signal is attenuated, thus demonstrat-ing the degree of signal selectivity devel-oped by the filter design.

A fractal spiral resonator developed byPalandöken & Henke is shown in Figure5. The filter is composed of two unit cellsof electrically small artificial magneticmetamaterials formed with the direct con-nection of two concentric Hilbert fractalcurves. Operation is based on the excita-tion of two electrically coupled fractal spi-ral resonators through direct connectionwith the feeding line. Simulation results

for the transmission (S21) and reflection(S11) losses are shown in Figure 6; theselectivity of the filter is 100 dB/GHz witha 3 dB reference insertion loss.

The electric field distribution devel-oped by the fractal spiral resonator isshown in Figure 7; below the resonantfrequency, signal passes through the fil-ter; at resonance, the signal is highlyattenuated with an extremely low levelof signal transmitted.

The performance of a spiral resonatorfilter has been analyzed using COMSOLMultiphysics, and shown to demonstrateagreement with experimental data. Acompact microstrip-based spiral res-onator filter with a resonant frequencyof 7.2 GHz shows low insertion losseswith a high level of performance andsharp cutoff over the specified frequen-cy range. Analysis of a fractal spiral res-onator consisting of two unit cells ofmagnetic metamaterials operating at aresonant frequency of ~1.3 GHz alsoshows a high level of selectivity at 100dB/GHz. Analyses of this type can beextended to assess the performance ofother filter designs prior to fabricationand integration into operating circuits.

This article was written by Sergei P.Yushanov, Jeffrey S. Crompton, and Kyle C.Koppenhoefer of AltaSim Technologies. For more information, visit http://info.hotims.com/45607-127.

Figure 5: Geometry of Metamaterials FractalSpiral Resonator: two fractal resonators are con-nected anti-symmetrically along the feeding line.

Figure 6: Reflection and Transmission Param eters of the fractal spiralresonator.

Figure 7: Electric Field at a frequency below the resonant frequency (left) and at the resonantfrequency (right).

Enigma Version 12 software com-bines model building, animation, andengineering visualization into one con-cise software package. Enigma employsa versatile user interface to allow aver-age users access to even the most com-plex pieces of the application. Using

Enigma eliminates the need to buy andlearn several software packages to cre-ate an engineering visualization.Models can be created and/or modifiedwithin Enigma down to the polygonlevel. Textures and materials can beapplied for additional realism. Within

Enigma, these models can be combinedto create systems of models that have ahierarchical relationship to one anoth-er, such as a robotic arm. Then thesesystems can be animated within the pro-gram or controlled by an external appli-cation programming interface (API). In

Enigma Version 12Lyndon B. Johnson Space Center, Houston, Texas

Cov ToC + – ➭

➮

AIntro



Planetary Protection Bioburden Analysis ProgramNASA’s Jet Propulsion Laboratory, Pasadena, California

This program is a Microsoft Access pro-gram that performed statistical analysis ofthe colony counts from assays performedon the Mars Science Laboratory (MSL)spacecraft to determine the bioburdendensity, 3-sigma biodensity, and the totalbioburdens required for the MSLprelaunch reports. It also contains numer-

ous tools that report the data in variousways to simplify the reports required. Theprogram performs all the calculationsdirectly in the MS Access program. Priorto this development, the data was export-ed to large Excel files that had to be cutand pasted to provide the desired results.The program contains a main menu and

a number of submenus. Analyses can beperformed by using either all the assays,or only the accountable assays that will beused in the final analysis.

There are three options on the firstmenu: either calculate using (1) the oldMER (Mars Exploration Rover) statistics,(2) the MSL statistics for all the assays, or


In order to have the capability to usesatellite data from its own missions toinform future sea-level rise projections,JPL needed a full-fledged ice-sheet/ice-shelf flow model, capable of modelingthe mass balance of Antarctica andGreenland into the near future. ISSMwas developed with such a goal in mind,as a massively parallelized, multi-pur-pose finite-element framework dedicat-ed to ice-sheet modeling.

ISSM features unstructured meshes(Tria in 2D, and Penta in 3D) along withcorresponding finite elements for bothtypes of meshes. Each finite element cancarry out diagnostic, prognostic, tran-sient, thermal 3D, surface, and bed slopesimulations. Anisotropic meshing enablesadaptation of meshes to a certain metric,and the 2D Shelfy-Stream, 3D Blatter/Pattyn, and 3D Full-Stokes formulationscapture the bulk of the ice-flow physics.These elements can be coupled together,based on the Arlequin method, so that ona large scale model such as Antarctica,each type of finite element is used in themost efficient manner.

For each finite element referencedabove, ISSM implements an adjoint.

This adjoint can be used to carry outmodel inversions of unknown modelparameters, typically ice rheology andbasal drag at the ice/bedrock interface,using a metric such as the observedInSAR surface velocity. This data assimi-lation capability is crucial to allow spin-ning up of ice flow models using avail-able satellite data.

ISSM relies on the PETSc library forits vectors, matrices, and solvers. Thisallows ISSM to run efficiently on any par-allel platform, whether shared or distrib-uted. It can run on the largest clusters,and is fully scalable. This allows ISSM totackle models the size of continents.

ISSM is embedded into MATLAB andPython, both open scientific platforms.This improves its outreach within the sci-ence community. It is entirely written inC/C++, which gives it flexibility in itsdesign, and the power/speed thatC/C++ allows. ISSM is svn (subversion)hosted, on a JPL repository, to facilitateits development and maintenance.

ISSM can also model propagation ofrifts using contact mechanics and meshsplitting, and can interface to theDakota software. To carry out sensitivityanalysis, mesh partitioning algorithmsare available, based on the Scotch,Chaco, and Metis partitioners thatensure equal area mesh partitions canbe done, which are then usable for sam-pling and local reliability methods.

This work was done by Eric Larour andJohn E. Schiermeier of Caltech, and HeleneSeroussi and Mathieu Morlinghem of EcoleCentrale Paris for NASA’s Jet PropulsionLaboratory. For more information, seehttp://issm.jpl.nasa.gov/.

This software is available for commerciallicensing. Please contact Dan Broderick [email protected]. Refer toNPO-48164.

ISSM: Ice Sheet System ModelNASA’s Jet Propulsion Laboratory, Pasadena, California

Modeled Antarctic Surface Velocity using ISSM.

addition, Enigma provides the ability touse plug-ins. Plug-ins allow the user tocreate custom code for a specific appli-cation and access the Enigma modeland system data, but still use theEnigma drawing functionality.

CAD files can be imported intoEnigma and combined to create systemsof computer graphics models that canbe manipulated with constraints. AnAPI is available so that an engineer canwrite a simulation and drive the com-puter graphics models with no knowl-

edge of computer graphics. An anima-tion editor allows an engineer to set upsequences of animations generated bysimulations or by conceptual trajecto-ries in order to record these to high-quality media for presentation.

Commercially, because it is so generic,Enigma can be used for almost any proj-ect that requires engineering visualiza-tion, model building, or animation.Models in Enigma can be exported tomany other formats for use in otherapplications as well. Educationally,

Enigma is being used to allow universitystudents to visualize robotic algorithmsin a simulation mode before using themwith actual hardware.

This work was done by David Shores andSharon P. Goza of Johnson Space Center;Cheyenne McKeegan, Rick Easley, Janet Way,and Shonn Everett of MEI Technologies;Mark Manning of PTI; and Mark Guerra,Ray Kraesig, and William Leu of TietronixSoftware, Inc. For further information, con-tact the JSC Innovation Partnerships Officeat (281) 483-3809. MSC-24211-1

Cov ToC + – ➭

➮

AIntro


This software implements penetrationlimit equations for common micromete-oroid and orbital debris (MMOD) shieldconfigurations, windows, and thermalprotection systems. Allowable MMODrisk is formulated in terms of the proba-bility of penetration (PNP) of the space-craft pressure hull.

For calculating the risk, spacecraftgeometry models, mission profiles,debris environment models, and pene-tration limit equations for installedshielding configurations are required.Risk assessment software such as NASA’s

BUMPER-II is used to calculate missionPNP; however, they are unsuitable foruse in shield design and preliminaryanalysis studies.

The software defines a single equationfor the design and performance evalua-tion of common MMOD shielding con-figurations, windows, and thermal protec-tion systems, along with a description oftheir validity range and guidelines fortheir application. Recommendations arebased on preliminary reviews of funda-mental assumptions, and accuracy in pre-dicting experimental impact test results.

The software is programmed in VisualBasic for Applications for installation asa simple add-in for Microsoft Excel. Theuser is directed to a graphical user inter-face (GUI) that requires user inputs andprovides solutions directly in MicrosoftExcel workbooks.

This work was done by Shannon Ryan ofthe USRA Lunar and Planetary Institute forJohnson Space Center. For more information,download the Technical Support Package(free white paper) at www.techbriefs.com/tsp under the Software category. MSC-24582-1

Micrometeoroid and Orbital Debris (MMOD) Shield BallisticLimit Analysis ProgramLyndon B. Johnson Space Center, Houston, Texas

(3) the MSL statistics for only the account-able assays. Other options on the mainmenu include a data editing form andutility programs that produce variousreports requested by the microbiologistsand the project, and tools to generate thegroupings for the final analyses.

The analyses can be carried out inthree ways: Each assay can be treatedseparately, the assays can be collectivelytreated for the whole zone as a group, orthe assays can be collected in groups des-ignated by the JPL Planetary ProtectionManager. The latter approach was usedto generate the final report becauseassays on the same equipment or similar

equipment can be assumed to have beenexposed to the same environment andcleaning. Thus, the statistics areimproved by having a larger population,thereby reducing the standard deviationby the square root of N.

For each method mentioned above,three reports are available. The first is adetailed report including all the data.This version was very useful in verifyingthe calculations. The second is a briefreport that is similar to the full detailedreport, but does not print out the data.The third is a grand total and summaryreport in which each assay requires onlyone line. For the first and second reports,

most of the calculations are performed inthe report section itself. For the third, allthe calculations are performed directly inthe query bound to the report. All thenumerical results were verified by com-paring them with Excel templates, thenexporting the data from the PlanetaryProtection Analysis program to Excel.

This work was done by Robert A. Beaudeto f Cal t ech for NASA’s J e t Propuls ionLaboratory. For more information, [email protected].


This rapid response computer pro-gram predicts Orbiter Wing LeadingEdge (WLE) damage caused by ice orfoam impact during a Space Shuttlelaunch (Program “IMPACT2”). The pro-gram was developed after the Columbiaaccident in order to assess quickly WLEdamage due to ice, foam, or metalimpact (if any) during a Shuttle launch.IMPACT2 simulates an impact event in afew minutes for foam impactors, and inseconds for ice and metal impactors.

The damage criterion is derived fromresults obtained from one sophisticatedcommercial program, which requireshours to carry out simulations of the

same impact events. The program wasdesigned to run much faster than thecommercial program with prediction ofprojectile threshold velocities within 10to 15% of commercial-program values.The mathematical model involves cou-pling of Orbiter wing normal modes ofvibration to nonlinear or linear spring-mass models.

IMPACT2 solves nonlinear or linearimpact problems using classical normalmodes of vibration of a target, and non-linear/linear time-domain equations forthe projectile. Impact loads and stressesdeveloped in the target are computed asfunctions of time.

This model is novel because of itsspeed of execution. A typical model offoam, or other projectile characterizedby material nonlinearities, impacting anRCC panel is executed in minutesinstead of hours needed by the commer-cial programs. Target damage due toimpact can be assessed quickly, providedthat target vibration modes and allow-able stress are known.

This work was done by Robert Clark, Jr.,Paul Cotter, and Constantine Michalopoulosof The Boeing Company for Johnson SpaceCenter. For further information, contact theJSC Innovation Partnerships Office at (281)483-3809. MSC-24988-1

Wing Leading Edge RCC Rapid Response Damage PredictionTool (IMPACT2)Lyndon B. Johnson Space Center, Houston, Texas

Cov ToC + – ➭

➮

AIntro

http://www.abpi.net/ntbpdfclicks/l.php?201309NTBPTSP

G-CAT is a covariance analysis tool thatenables fast and accurate computation oferror ellipses for descent, landing, ascent,and rendezvous scenarios, and quantifiesknowledge error contributions neededfor error budgeting purposes. Because G-CAT supports hardware/system tradestudies in spacecraft and mission design,it is useful in both early and late mis-sion/proposal phases where Monte Carlosimulation capability is not mature,Monte Carlo simulation takes too long torun, and/or there is a need to performmultiple parametric system design tradesthat would require an unwieldy numberof Monte Carlo runs.

G-CAT is formulated as a variable-ordersquare-root linearized Kalman filter(LKF), typically using over 120 filterstates. An important property of G-CAT isthat it is based on a 6-DOF (degrees offreedom) formulation that completelycaptures the combined effects of both atti-tude and translation errors on the propa-gated trajectories. This ensures its accura-cy for guidance, navigation, and control(GN&C) analysis. G-CAT provides thedesired fast turnaround analysis neededfor error budgeting in support of missionconcept formulations, design trade stud-ies, and proposal development efforts.

The main usefulness of a covarianceanalysis tool such as G-CAT is its abilityto calculate the performance envelopedirectly from a single run. This is insharp contrast to running thousands ofsimulations to obtain similar informa-tion using Monte Carlo methods. It doesthis by propagating the “statistics” of theoverall design, rather than simulatingindividual trajectories.

G-CAT supports applications to lunar,planetary, and small body missions. Itcharacterizes onboard knowledge prop-agation errors associated with inertialmeasurement unit (IMU) errors (gyroand accelerometer), gravity errors/dis-

persions (spherical harmonics, mass-cons), and radar errors (multiple altime-ter beams, multiple Doppler velocimeterbeams). G-CAT is a standalone MAT-LAB-based tool intended to run on anyengineer’s desktop computer.

This work was done by Dhemetrios Boussalisand David S. Bayard of Caltech for NASA’s JetPropulsion Laboratory. For more information,download the Technical Support Package(free white paper) at www.techbriefs.com/tspunder the Software category.


Covariance Analysis Tool (G-CAT) for Computing Ascent,Descent, and Landing ErrorsNASA’s Jet Propulsion Laboratory, Pasadena, California


Landing Site Reconstruction based on descent camera imagery. Copyright 2010 California Institute ofTechnology. Government sponsorship acknowledged.

Reconstructed Landing Error Ellipse

Descent camera imagery

Rendered Lunar topography model

Electronics/Computers

Phoenix Telemetry ProcessorNASA’s Jet Propulsion Laboratory, Pasadena, California

Phxtelemproc is a C/C++ basedtelemetry processing program thatprocesses SFDU telemetry packets fromthe Telemetry Data System (TDS). Itgenerates Experiment Data Records(EDRs) for several instruments includ-ing surface stereo imager (SSI); roboticarm camera (RAC); robotic arm (RA);

microscopy, electrochemistry, and con-ductivity analyzer (MECA); and the opti-cal microscope (OM). It processes bothuncompressed and compressed teleme-try, and incorporates unique subrou-tines for the following compression algorithms: JPEG Arithmetic, JPEGHuffman, Rice, LUT3, RA, and SX4.

This program was in the critical pathfor the daily command cycle of thePhoenix mission. The products generatedby this program were part of the RA com-manding process, as well as the SSI, RAC,OM, and MECA image and science analy-sis process. Its output products were usedto advance science of the near polar


Cov ToC + – ➭

➮

AIntro



Spitzer Telemetry Processing SystemNASA’s Jet Propulsion Laboratory, Pasadena, California

The Spitzer Telemetry ProcessingSystem (SirtfTlmProc) was designed toaddress objectives of JPL’s Multi-mis-sion Image Processing Lab (MIPL) inprocessing spacecraft telemetry anddistributing the resulting data to thescience community. To minimize costsand maximize operability, the softwaredesign focused on automated errorrecovery, performance, and informa-tion management.

The system processes telemetry fromthe Spitzer spacecraft and delivers Level 0products to the Spitzer Science Center.SirtfTlmProc is a unique system with auto-mated error notification and recovery,with a real-time continuous service thatcan go quiescent after periods of inactivity.

The software can process 2 GB oftelemetry and deliver Level 0 scienceproducts to the end user in four hours. Itprovides analysis tools so the operator can

manage the system and troubleshootproblems. It automates telemetry process-ing in order to reduce staffing costs.

This work was done by Alice Stanboli,Elmain M. Martinez, and James M. McAuleyof Caltech for NASA’s Jet PropulsionLaboratory. For more information, [email protected].

This software is available for commercial licens-ing. Please contact Dan Broderick at [email protected]. Refer to NPO-47803.

Advanced Strategic and Tactical Relay Request Management for the Mars Relay Operations ServiceNASA’s Jet Propulsion Laboratory, Pasadena, California

This software provides a new set ofcapabilities for the Mars Relay OperationsService (MaROS) in support of Strategicand Tactical relay, including a highlyinteractive relay request Web user inter-face, mission control over relay planningtime periods, and mission management ofallowed strategic vs. tactical request

param eters. Together, these new capabili-ties expand the scope of the system toinclude all elements critical for Tacticalrelay operations.

Planning of replay activities spans a timeperiod that is split into two dis tinct phases.The first phase is called Strategic, whichbegins at the time that relay opportunities

are identified, and concludes at the pointthat the orbiter generates the flightsequences for on board execution. Anyrelay request changes from this point onare called Tactical.

Tactical requests, otherwise called Orbit -er Relay State Changes (ORSC), are high-

Contact Graph Routing Enhancements Developed in ION for DTNNASA’s Jet Propulsion Laboratory, Pasadena, California

The Interplanetary Overlay Network(ION) software suite is an open-source,flight-ready implementation of net-working protocols including theDelay/Disruption Tolerant Networking(DTN) Bundle Protocol (BP), theCCSDS (Con sul tative Committee forSpace Data Systems) File DeliveryProtocol (CFDP), and many othersincluding the Contact Graph Routing(CGR) DTN routing system. WhileDTN offers the capability to toleratedisruption and long signal propagationdelays in transmission, without an

appropriate routing protocol, no datacan be delivered.

CGR was built for space explorationnetworks with scheduled communicationopportunities (typically based on trajecto-ries and orbits), represented as a contact-graph. Since CGR uses knowledge offuture connectivity, the contact graph cangrow rather large, and so efficient process-ing is desired. These enhancements allowCGR to scale to predicted NASA spacenetwork complexities and beyond.

This software improves upon CGR byadopting an earliest-arrival-time cost met-

ric and using the Dijkstra path selectionalgorithm. Moving to Dijkstra path selec-tion also enables construction of an earli-est-arrival-time tree for multicast routing.The enhancements have been rolled intoION 3.0 available on sourceforge.net.

This work was done by John S. Segui andScott Burleigh of Caltech for NASA’s JetPropulsion Laboratory. For more information,contact [email protected].


regions of Mars, and were used to provethat water is found in abundance there.

Phxtelemproc is part of the MIPL(Multi-mission Image ProcessingLaboratory) system. This softwareproduced Level 1 products used to ana-

lyze images returned by in situ space-craft. It ultimately assisted in opera-tions, planning, commanding, science,and outreach.

This work was done by Alice Stanboli of Caltech for NASA’s Jet Propulsion

Laboratory. For more information, [email protected].


Continued on page 18

Cov ToC + – ➭

➮

AIntro

© Copyright 2013. COMSOL®, COMSOL Multiphysics®, Capture the Concept®, COMSOL Desktop™, and LiveLink™ are either registered trademarks or trademarks of COMSOL AB. All other trademarks are the property of their respective owners,

Breakthrough analyCOMSOL Multiphysic

Multibody Dynamics ModuleDynamics of assemblies of rigid and fl exible bodies connected with joints. Multibody dynamics analyses can be time-dependent, stationary, frequency-domain, or eigenfrequency. Joints can be assigned applied forces and moments as well as prescribed motion as a function of time.

Semiconductor ModuleDetailed analysis of semiconductor device operation at the fundamental physics level with electron-hole transport of PN junctions, transistors, and diodes.

Molecular Flow ModuleAccurate modeling of low pressure gas fl ows in complex CAD geometries of vacuum systems. Free molecular fl ow simulations based on the angular coeffi cient method with fast parametric sweeps of geometric dimensions.

Wave Optics ModuleElectromagnetic wave propagation in linear or nonlinear optical media. The groundbreaking Beam Envelope Method enables 3D simulation of elongated optical devices with greater accuracy.

New Modules

ChemicaEngineerin

CFDModule

Heat TransferModule

AC/DCModule

BatteFuel CellModule

Structural MechanicsModule

RFModule

ElectrodMo

ElectrocMo

Subsurface FlowModule

Molecular FlowModule

Nonlinear Structural Materials Module

Wave OpticsModule

PlasmaModule

CorrMo

Pipe FlowModule

GeomechanicsModule

MEMSModule

SemiconductorModule

FatigueModule

Acoustics Module

Multibody Dynamics Module

chem

ical

flui

d

mec

han

ical

elec

tric

al

COMSOL M

New

NewNew

New

Cov ToC + – ➭

➮

AIntro

sis tools expand the cs® simulation platform

COMSOL MultiphysicsProductivity enhancements throughout the simulation workfl ow such as:• 2D Model Work Planes from the Cross Section

of 3D Geometries• Coordinate Systems for Curvilinear Shapes• Increased Automation for Swept Meshing

CFD Module• Frozen Rotor Feature for Rotating Machinery in CFD

Applications• SST Turbulence Model and a New CFD Solver• Thin Screens for CFD Applications

Heat Transfer Module• Multi-Wavelength Surface-to-Surface

Heat Radiation• Heat Transfer with Phase Change• Thermal Contact

Structural Mechanics Module• Bolt Pre-tension• Beam Cross-Section Analysis

AC/DC and RF Modules• New Magnetics Solver• Electrical Contact

dependent on Mechanical Pressure

• Periodic Structures for Electromagnetic Waves

New in COMSOL Version 4.3b

Electrochemistry ModuleFor the modeling of electrolysis, electroanalysis & electro-dialysis applications as well as electrochemical sensors & the electrochemistry of biomedical devices.

OptimizationModule

l Reactionng Module

LiveLinkTM for MATLAB®

LiveLinkTM for Excel®

ECAD ImportModule

MaterialLibrary

eries & ls Module

CAD ImportModule

LiveLinkTM for SpaceClaim®

Particle Tracing Module

eposition dule

chemistry dule

LiveLinkTM for SolidWorks®

LiveLinkTM for AutoCAD®


rosion dule

LiveLinkTM for Inventor®

LiveLinkTM for Solid Edge®

LiveLinkTM for Pro/ENGINEER®

LiveLinkTM for CreoTM Parametric

mul

tipu

rpo

se

inte

rfac

ing

ultiphysics®

New


Cov ToC + – ➭

➮

AIntro




Electronics/Computers

ly restricted in terms of what types ofchanges can be made, and the types ofparameters that can be changed may differfrom one orbiter to the next. For exam-ple, one orbiter may be able to delay thestart of a relay request, while another maynot. The legacy approach to ORSC man-agement involves exchanges of e-mail with“requests for change” and “acknowledge-ment of approval,” with no other trackingof changes outside of e-mail folders.

MaROS Phases 1 and 2 provided theinfrastructure for strategic relay for all

supported missions. This new version,3.0, introduces several capabilities thatfully expand the scope of the system toinclude tactical relay. One new featureallows orbiter users to manage and“lock” Planning Periods, which allowsthe orbiter team to formalize thechangeover from Strategic to Tacticaloperations. Another major featureallows users to interactively submit tacti-cal request changes via a Web user inter-face. A third new feature allows orbitermissions to specify allowed tacticalupdates, which are automatically incor-

porated into the tactical change process.This software update is significant inthat it provides the only centralized serv-ice for tactical request managementavailable for relay missions.

This work was done by Daniel A. Allard,Michael N. Wallick, Roy E. Gladden, PaulWang, and Franklin H. Hy of Caltech forNASA’s Jet Propulsion Laboratory. For moreinformation, contact [email protected].


Mechanics/Machinery

GFEChutes Lo-FiLyndon B. Johnson Space Center, Houston, Texas

NASA needed to provide a softwaremodel of a parachute system for amanned re-entry vehicle. NASA hasparachute codes, e.g., the DescentSimulation System (DSS), that dateback to the Apollo Program. Since thespace shuttle did not rely on para-chutes as its primary descent controlmechanism, DSS has not been main-tained or incorporated into modernsimulation architectures such as Osirisand Antares, which are used for newmission simulations. GFEChutes Lo-Fiis an object-oriented implementationof conventional parachute codesdesigned for use in modern simulationenvironments.

The GFE (Government FurnishedEquipment), low-fidelity (Lo-Fi) para-chute model (GFEChutes Lo-Fi) is asoftware package capable of modelingthe effects of multiple parachutes,deployed concurrently and/or sequen-tially, on a vehicle during the subsonicphase of re-entry into planetary atmos-phere. The term “low-fidelity” distin-guishes models that represent the para-chutes as simple forces acting on thevehicle, as opposed to independentaerodynamic bodies. GFEChutes Lo-Fiwas created from these existing modelsto be clean, modular, certified as NASAClass C software, and portable, or “plugand play.”

The GFE Lo-Fi Chutes Model providesbasic modeling capability of a sequentialseries of parachute activities. Actionsinclude deploying the parachute, chang-ing the reefing on the parachute, and cut-ting away the parachute. Multiple chutescan be deployed at any given time, but allchutes in that case are assumed to behaveas individually isolated chutes; there is nomodeling of any interactions betweendeployed chutes. Drag characteristics of adeployed chute are based on a coefficientof drag, the face area of the chute, andthe local dynamic pressure only. The ori-entation of the chute is approximatelymodeled for purposes of obtainingtorques on the vehicle, but the dynamic

Automated Loads Analysis System (ATLAS)Lyndon B. Johnson Space Center, Houston, Texas

ATLAS is a generalized solution thatcan be used for launch vehicles. ATLAS isused to produce modal transient analysisand quasi-static analysis results (i.e., accel-erations, displacements, and forces) forthe payload math models on a specificShuttle Transport System (STS) flight

using the shuttle math model and associ-ated forcing functions. This innovationsolves the problem of coupling of payloadmath models into a shuttle math model.It performs a transient loads analysis sim-ulating liftoff, landing, and all flightevents between liftoff and landing.

ATLAS utilizes efficient and numericallystable algorithms available in MSC/NASTRAN.

This work was done by Stephen Gardner, ScotFrere, and Patrick O’Reilly of The Boeing Com -pany for Johnson Space Center. For further infor-mation, contact the JSC Innovation Partner -ships Office at (281) 483-3809. MSC-24987-1

Continued from page 15

Cov ToC + – ➭

➮

AIntro


Integrated Main Propulsion System PerformanceReconstruction Process/ModelsLyndon B. Johnson Space Center, Houston, Texas

The Integrated Main PropulsionSystem (MPS) Performance Recon -struction process provides the MPSpost-flight data files needed for post-flight reporting to the project integra-tion management and key customers to verify flight performance. Thisprocess/model was used as the base-line for the currently ongoing SpaceLaunch System (SLS) work.

The process utilizes several methodolo-gies, including multiple software pro-grams, to model integrated propulsionsystem performance through space shut-tle ascent. It is used to evaluate integratedpropulsion systems, including propellanttanks, feed systems, rocket engine, andpressurization systems performancethroughout ascent based on flight pres-sure and temperature data. The latest

revision incorporates new methods basedon main engine power balance modelupdates to model higher mixture ratiooperation at lower engine power levels.

This work was done by Eduardo Lopez,Katie Elliott, Steven Snell, and MichaelEvans of The Boeing Company for JohnsonSpace Center. For further information, contactthe JSC Innovation Partnerships Office at(281) 483-3809. MSC-25066-1

state of the chute as a separate entity isnot integrated — the treatment is simplyan approximation.

The innovation in GFEChutes Lo-Fi isto use an object design that closely fol-lowed the mechanical characteristicsand structure of a physical system ofparachutes and their deployment mech-anisms. Software objects represent the

components of the system, and use of anobject hierarchy allows a progressionfrom general component outlines tospecific implementations. These extrachutes were not part of the baselinedeceleration sequence of drogues andmains, but still had to be simulated. Themajor innovation in GFEChutes Lo-Fi isthe software design and architecture.

This work was done by Emily Gist, GaryTurner, Robert Shelton, Mana Vautier, andAshraf Shaikh of Odyssey Space Research.LLC for Johnson Space Center. For moreinformation, download the TechnicalSupport Package (free white paper) atwww.techbriefs.com/tsp under the Softwarecategory. MSC-25004-1

Physical Sciences

Sally Ride EarthKAM — Automated Image Geo-ReferencingUsing Google Earth Web Plug-InNASA’s Jet Propulsion Laboratory, Pasadena, California

Sally Ride EarthKAM is an education-al program funded by NASA that aims toprovide the public the ability to pictureEarth from the perspective of theInternational Space Station (ISS). Acomputer-controlled camera is mountedon the ISS in a nadir-pointing window;however, timing limitations in the systemcause inaccurate positional metadata.Manually correcting images within anorbit allows the positional metadata tobe improved using mathematical regres-sions. The manual correction process istime-consuming and thus, unfeasible fora large number of images.

The standard Google Earth programallows for the importing of KML (key-hole markup language) files that previ-ously were created. These KML file-based overlays could then be manuallymanipulated as image overlays, saved,and then uploaded to the project serverwhere they are parsed and the metadatain the database is updated. The newinterface eliminates the need to save,download, open, re-save, and upload theKML files. Everything is processed onthe Web, and all manipulations godirectly into the database. Ad min -istrators also have the control to discard

any single correction that was made andvalidate a correction.

This program streamlines a processthat previously required several criticalsteps and was probably too complex for the average user to complete suc-cessfully. The new process is theoreti-cally simple enough for members ofthe public to make use of and con-tribute to the success of the Sally RideEarthKAM project.

Using the Google Earth Web plug-in,EarthKAM images, and associated meta-data, this software allows users to interac-tively manipulate an EarthKAM image

Cov ToC + – ➭

➮

AIntro



overlay, and update and improve theassociated metadata. The Web interfaceuses the Google Earth JavaScript APIalong with PHP-PostgreSQL to presentthe user the same interface capabilitieswithout leaving the Web. The simplergraphical user interface will allow thepublic to participate directly and mean-ingfully with EarthKAM. The use of sim-

ilar techniques is being investigated toplace ground-based observations in aGoogle Mars environment, allowing theMSL (Mars Science Laboratory) ScienceTeam a means to visualize the rover andits environment.

This work was done by Paul M. Andres ofCaltech, Dennis K. Lazar of PurdueUniversity, and Robert Q. Thames of Loyola

Marymount University for NASA’s JetPropulsion Laboratory. For more information,download the Technical Support Package(free white paper) at www.techbriefs.com/tspunder the Software category.


Ionospheric Specifications for SAR Interferometry (ISSI)NASA’s Jet Propulsion Laboratory, Pasadena, California

The ISSI software package is designedto image the ionosphere from space bycalibrating and processing polarimetricsynthetic aperture radar (PolSAR) datacollected from low Earth orbit satellites.Signals transmitted and received by aPolSAR are subject to the Faraday rota-tion effect as they traverse the magnet-ized ionosphere. The ISSI algorithmscombine the horizontally and verticallypolarized (with respect to the radar sys-tem) SAR signals to estimate Faradayrotation and ionospheric total electroncontent (TEC) with spatial resolutions

of sub-kilometers to kilometers, and toderive radar system calibration parame-ters. The ISSI software package has beendesigned and developed to integrate thealgorithms, process PolSAR data, andimage as well as visualize the ionospher-ic measurements.

A number of tests have been conduct-ed using ISSI with PolSAR data collectedfrom various latitude regions using thephase array-type L-band synthetic aper-ture radar (PALSAR) onboard JapanAerospace Exploration Agency’s Ad -vanced Land Observing Satellite mission,

and also with Global Positioning Systemdata. These tests have demonstrated and validated SAR-derived ionosphericimages and data correction algorithms.

This work was done by Xiaoqing Pi, BruceD. Chapman, Anthony Freeman, WalterSzeliga, Sean M. Buckley, Paul A. Rosen,and Marco Lavalle of Caltech for NASA’s JetPropulsion Laboratory. For more information,contact [email protected].


Acoustic Emission Analysis Applet (AEAA) SoftwareJohn H. Glenn Research Center, Cleveland, Ohio

NASA Glenn Research and NASAWhite Sands Test Facility have developedsoftware supporting an automated pres-sure vessel structural health monitoring(SHM) system based on acoustic emis-sions (AE). The software, referred to asthe Acoustic Emission Analysis Applet(AEAA), provides analysts with a toolthat can interrogate data collected onDigital Wave Corp. and PhysicalAcoustics Corp. software using a widespectrum of powerful filters and charts.This software can be made to work withany data once the data format is known.The applet will compute basic AE statis-tics, and statistics as a function of timeand pressure (see figure). AEAA pro-vides value added beyond the analysisprovided by the respective vendors’analysis software. The software can han-dle data sets of unlimited size.

A wide variety of government and com-mercial applications could benefit fromthis technology, notably requalificationand usage tests for compressed-gas and hydrogen-fueled vehicles. Future en hancements will add features similar to

a “check engine” light on a vehicle. Onceinstalled, the system will ultimately beused to alert International Space Stationcrewmembers to critical structural insta-

bilities, but will have little impact to mis-sions otherwise. Diagnostic informationcould then be transmitted to experiencedtechnicians on the ground in a timely

Physical Sciences

The Front Panel is divided into the following main sections: (1) Run-time menu; File, Options, Help; (2)AE & Fast Fourier Transform graphs; (3) AE analysis settings; and (4) AE statistics.

Cov ToC + – ➭

➮

AIntro



Software for Generating Troposphere Corrections for InSARUsing GPS and Weather Model DataNASA’s Jet Propulsion Laboratory, Pasadena, California

Atmospheric errors due to the tropo-sphere are a limiting error source forspaceborne interferometric syntheticaperture radar (InSAR) imaging. Thissoftware generates tropospheric delaymaps that can be used to correct atmos-pheric artifacts in InSAR data. The soft-ware automatically acquires all neededGPS (Global Positioning System), weath-er, and Digital Elevation Map data, andgenerates a tropospheric correction mapusing a novel algorithm for combiningGPS and weather information whileaccounting for terrain.

Existing JPL software was prototypicalin nature, required a MATLAB license,required additional steps to acquire andingest needed GPS and weather data, anddid not account for topography in inter-polation. Previous software did notachieve a level of automation suitable forintegration in a Web portal. This softwareovercomes these issues.

GPS estimates of tropospheric delay area source of corrections that can be used toform correction maps to be applied toInSAR data, but the spacing of GPS sta-tions is insufficient to remove short-wave-length tropospheric artifacts. This soft-ware combines interpolated GPS delaywith weather model precipitable watervapor (PWV) and a digital elevationmodel to account for terrain, increasingthe spatial resolution of the tropospheric

correction maps and thus removing short-wavelength tropospheric artifacts to agreater extent. It will be integrated into aWeb portal request system, allowing use ina future L-band SAR Earth radar missiondata system. This will be a significant con-tribution to its technology readiness,building on existing investments in in situspace geodetic networks, and improvingtimeliness, quality, and science value ofthe collected data.

This work was done by Angelyn W. Moore,Frank H. Webb, Evan F. Fishbein, Eric J.Fielding, Susan E. Owen, and Stephanie L.

Granger of Caltech; Fredrik Björndahl andJohan Löfgren of Chalmers University ofTechnology; and Peng Fang, James D.Means, Yehuda Bock, and Xiaopeng Tong ofUC San Diego’s Scripps Institution ofOceanography for NASA’s Jet PropulsionLaboratory. For more information, down-load the Technical Support Package (freewhite paper) at www.techbriefs.com/tspunder the Software category.


Advanced Land Observing Satellite (ALOS) Data. At left, the original stack of 33 interferograms.Center: The stacked correction maps, showing typical distribution of moisture in the Coachella Valley,CA. At right, the corrected stacked image.

ALOS ALOS

Stack Correction Corrected

34°

33°-117° -116°

-10 -5 0 5 10

34°

33°-117° -116°

-10 -5 0 5 10

34°

33°-117° -116°

-10 -5 0 5 10

Implementation of a Wavefront-Sensing AlgorithmGoddard Space Flight Center, Greenbelt, Maryland

A computer program has been writtenas a unique implementation of an image-based wavefront-sensing algorithm report-ed in “Iterative-Transform Phase RetrievalUsing Adaptive Diversity” (GSC-14879-1),NASA Tech Briefs, Vol. 31, No. 4 (April2007), page 32. This software was original-ly intended for application to the James

Webb Space Telescope, but is also applica-ble to other segmented-mirror telescopes.

The software is capable of determiningoptical-wavefront information using, as in -put, a variable number of irradiance measure -ments collected in defocus planes aboutthe best focal position. The software alsouses input of the geometrical definition of

the telescope exit pupil (otherwise denot-ed the pupil mask) to identify the locationsof the segments of the primary telescopemirror. From the irradiance data and maskinformation, the software calculates an esti-mate of the optical wavefront (a measureof performance) of the telescope generallyand across each primary mirror segment

manner to determine whether pressurevessels have been impacted, are struc-turally unsound, or can be safely used tocomplete the mission.

This work was done by Don J. Roth andCharles T. Nichols of Glenn Research Center,

and was sponsored by the NASA Non -destructive Evaluation Working Group. Formore information, download the TechnicalSupport Package (free white paper) atwww.techbriefs.com/tsp under the Softwarecategory.

Inquiries concerning rights for the commer-cial use of this invention should be addressed toNASA Glenn Research Center, InnovativePartnerships Office, Attn: Steven Fedor, MailStop 4–8, 21000 Brookpark Road, Cleveland,Ohio 44135. Refer to LEW-19032-1

Cov ToC + – ➭

➮

AIntro



The HiiHat toolboxdeveloped for CAT/ENVIprovides principal investi-gators di rect, immediate,flexible, and seamless in -teraction with their instru-ments and data from anylocation. Offering seg-mentation and neutralregion division, it facili-tates the discovery of keyendmembers and regionsof interest larger than asingle pixel.

Crucial to the analysis ofhyperspectral data fromMars or Earth is the re -moval of unwanted at -mospheric signatures. For Mars and the Compact ReconnaissanceImaging Spectrometer for Mars (CRISM),residual atmospheric CO2 absorption isboth directly problematic and indicativeof processing errors with implications tothe scientific utility of any particularimage region. Estimating this residual

error becomes key both in selectingregions of low distortion, and also toselect mitigating methods, such as neutralregion division. This innovation, theATMO estimator, provides a simple, 0-1normalized scalar that estimates this dis-tortion (see figure). The metric is defined

as the coefficient of deter-mination of a quadratic fitin the region of distortingatmospheric absorption (≈2 μm). This mimics thebehavior of existing CRISMteam mineralogical indicesto estimate the presence ofknown, interesting mineralsignatures. This facilitatesthe ATMO metric’s assimi-lation into existing plane-tary geology workflows.

This work was done byLukas Mandrake and DavidR. Thompson of Caltech for NASA’s Jet PropulsionLaboratory. For more informa-tion, download the Technical

Support Package (free white paper) atwww.techbriefs.com/tsp under the Softwarecategory.



Information Technology

specifically. The software is capable of gen-erating irradiance data, wavefront esti-mates, and basis functions for the full tele-scope and for each primary-mirror seg-ment. Optionally, each of these pieces of

information can be measured or comput-ed outside of the software and incorporat-ed during execution of the software.

This program was written by Jeffrey S. Smith,Bruce Dean, and David Aronstein of Goddard

Space Flight Center. For more information,download the Technical Support Package(free white paper) at www.techbriefs.com/tspunder the Software category. GSC-15399-1

Advanced Multimission Operations System (ATMO)NASA’s Jet Propulsion Laboratory, Pasadena, California

Automatic Method matches manual for atmospheric correction.

Memory-Efficient Onboard Rock Segmentation NASA’s Jet Propulsion Laboratory, Pasadena, California

Rockster-MER is an autonomous per-ception capability that was uploaded tothe Mars Exploration Rover Oppor tunityin December 2009. This software pro-vides the vision front end for a largersoftware system known as AEGIS(Autonomous Exploration for Gather ing

Increased Science), which was recentlynamed 2011 NASA Software of the Year.As the first step in AEGIS, Rockster-MERanalyzes an image captured by the rover,and detects and automatically identifiesthe boundary contours of rocks andregions of outcrop present in the scene.

This initial segmentation step reducesthe data volume from millions of pixelsinto hundreds (or fewer) of rock con-tours. Subsequent stages of AEGIS thenprioritize the best rocks according to sci-entist-defined preferences and take high-resolution, follow-up observations (see

Physical Sciences

Cov ToC + – ➭

➮

AIntro




figure). Rockster-MER has performedrobustly from the outset on the Mars sur-face under challenging conditions.

Rockster-MER is a specially adapted,embedded version of the original Rocksteralgorithm (“Rock Segmentation ThroughEdge Regrouping,” (NPO-44417) SoftwareTech Briefs, September 2008, p. 25).Although the new version performs thesame basic task as the original code, thesoftware has been (1) significantly upgrad-ed to overcome the severe onboard re -source limitations (CPU, memory, power,time) and (2) “bullet-proofed” throughcode reviews and extensive testing andprofiling to avoid the occurrence of faults.Because of the limited computationalpower of the RAD6000 flight processor onOpportunity (roughly two orders of mag-nitude slower than a modern worksta-tion), the algorithm was heavily tuned toimprove its speed. Several functional ele-ments of the original algorithm wereremoved as a result of an extensivecost/benefit analysis conducted on a largeset of archived rover images. The algo-rithm was also required to operate below astringent 4MB high-water memory ceiling;hence, numerous tricks and strategieswere introduced to reduce the memoryfootprint. Local filtering operations werere-coded to operate on horizontal datastripes across the image. Data types werereduced to smaller sizes where possible.Binary-valued intermediate results weresqueezed into a more compact, one-bit-per-pixel representation through bit pack-ing and bit manipulation macros. An esti-mated 16-fold reduction in memory foot-

print relative to the original Rockster algo-rithm was achieved. The resulting memo-ry footprint is less than four times the baseimage size. Also, memory allocation callswere modified to draw from a static pooland consolidated to reduce memory man-agement overhead and fragmentation.

Rockster-MER has now been runonboard Opportunity numerous timesas part of AEGIS with exceptional performance. Sample results are avail-able on the AEGIS website at http://aegis.jpl.nasa.gov.

This work was done by Michael C. Burl,David R. Thompson, Benjamin J. Bornstein,and Charles K. deGranville of Caltech forNASA’s Jet Propulsion Laboratory. For moreinformation, download the TechnicalSupport Package (free white paper) atwww.techbriefs.com/tsp under the Softwarecategory.


The top ten objects detected by Rockster-MER running onboard the Opportunity rover on Sol 2221.Note: Rockster-MER detects and segments the objects; the ranking is provided by AEGIS according toa set of scientist-specified attribute weightings.

Kinect Engineering with Learning (KEWL)Lyndon B. Johnson Space Center, Houston, Texas

According to a Nielsen survey at thetime of this reporting, 41% of all house-holds have a game console. This is onemarket in which NASA has been absentfrom education and outreach efforts.Kinect Engineering with Learning(KEWL) is made to enter into that mar-ket and bring NASA education and out-reach to a very familiar venue. KEWLcreates an education and outreach expe-rience that is more participatory, both ina school and museum environment.

KEWL is a set of applications that runson an Xbox 360 (see Figure 1) using theKinect controller used for education andoutreach. These applications currentlyinclude: Train R2 (see Figure 2), a visualsimulation of Robonaut 2 that allows stu- Figure 1. The Xbox 360 is one of the most recognized gamng consoles.

Cov ToC + – ➭

➮

AIntro




dents to control a virtual R2 in a gameenvironment; Drive R2, an interfaceusing the Xbox 360 and Kinect con-troller that allows students to control thereal R2 using the methods they learnedplaying Train R2; ISS experience, a visualtour of the interior of the InternationalSpace Station where students use theirbody to fly through the virtual ISS;

Gravity Ball, a simulation of throwingballs in the gravity of different planets;Solar Array repair, a simulation of thesimplified STS-121 solar array repair mis-sion; and PlaySpace, a Mars/Moon appli-cation that allows students to experiencedifferent aspects of Mars/Moon.

Users can “fly through” the ISS usingtheir body, allowing an experience simi-

lar to what an astronaut would have onorbit. In PlaySpace, users can fly over thesurface of Mars and view surface dataobtained by Mars rovers. Users of TrainR2 and Drive R2 can experience what itis like to control a robot over a distancewith a time delay, simulating the timedelay that would occur between groundcontrol and an on-orbit robot. The ini-tial ISS experiences were built usingparts of code from the NASA Enigmasoftware. The models used in theseexperiences were also from theIntegrated Graphics Operations andAnalysis Lab model database. ThePlaySpace experience incorporates sur-face data obtained from NASA roversand satellites and was built by NASA JPL.

This work was done by Sharon Goza andDavid Shores of Johnson Space Center; WilliamLeu, Raymond Kraesig, Eric Richeson,Clinton Wallace, Moses Hernandez, andCheyenne McKeegan of Tietronix SoftwareInc.; and Jeffrey Norris, Victor Luo, AlexanderMenzies, Dara Kong, and Matt Clausen ofJPL. For more information, download theTechnical Support Package (free whitepaper) at www.techbriefs.com/tsp under theSoftware category. MSC-25110-1

Figure 2. In Train R2, the student learns to control a simulated R2 using simple poses.

Automating Hyperspectral Data for Rapid Response in Volcanic EmergenciesNASA’s Jet Propulsion Laboratory, Pasadena, California

In a volcanic emergency, time is ofthe essence. It is vital to quantify erup-tion parameters (thermal emission,effusion rate, location of activity) anddistribute this information as quickly aspossible to decision-makers in order toenable effective evaluation of eruption-related risk and hazard. The goal of thiswork was to automate and streamlineprocessing of spacecraft hyperspectraldata, automate product generation,and automate distribution of products.

The software rapidly processes hyper-spectral data, correcting for incidentsunlight where necessary, and atmos-pheric transmission; detects thermallyanomalous pixels; fits data with modelblack-body thermal emission spectra todetermine radiant flux; calculatesatmospheric convection thermal re -moval; and then calculates total heatloss. From these results, an estimationof effusion rate is made. Maps are gen-erated of thermal emission and loca-tion (see figure). Products are posted Visible and Short-Wave Infrared Images of volcanic eruption in Iceland in May 2010.

36

2 May 2010 – VIS 2 May 2010 – SWIR 4 May 2010 - SWIR

Cov ToC + – ➭

➮

AIntro


The Spacecraft 3D application allows users to learn about and interactwith iconic NASA missions in a newand immersive way using commonmobile devices (see figure). UsingAugmented Reality (AR) techniques toproject 3D renditions of the missionspacecraft into real-world surround-ings, users can interact with and learnabout Curiosity, GRAIL, Cassini, andVoyager. Additional updates on futuremissions, animations, and informationwill be ongoing.

Using a printed AR Target and cam-era on a mobile device, users can getup close with these robotic explorers,see how some move, and learn aboutthese engineering feats, which are usedto expand knowledge and understand-ing about space.

The software receives input from themobile device’s camera to recognizethe presence of an AR marker in thecamera’s field of view. It then displays a 3D rendition of the selected space-

craft in the user’s physical surround-ings, on the mobile device’s screen,while it tracks the device’s movementin relation to the physical position of the spacecraft’s 3D image on the AR marker.

This work was done by Kevin J. Hussey,Paul R. Doronila, Brian E. Kumanchik,Evan G. Chan, and Douglas J. Ellison ofCaltech; and Andrea Boeck and Justin M.Moore of Mooreboeck Inc. for NASA’s JetPropulsion Laboratory.. For more informa-tion access:https://play.google.com/store/apps/

details?id=gov.nasa.jpl.spacecraft3Dhttp://www.space.com/

16569-nasa-app-spacecraft-hand.htmlhttp://www.nasa.gov/mission_pages/

msl/news/app20120711.htmlhttp://www.engadget.com/2012/07/1/

nasa-spacecraft-3d-ios-app/.This software is available for commercial

licensing. Please contact Dan Broderick [email protected]. Refer toNPO-48763.


online, and relevant parties notified.Effusion rate data are added to histori-cal record and plotted to identify spikesin activity for persistently active erup-tions. The entire process from start toend is autonomous.

Future spacecraft, especially those in deep space, can react to detection

of transient processes without theneed to communicate with Earth, thus increasing science return.Terrestrially, this removes the need forhuman intervention.

This work was done by Ashley G. Davies,Joshua R. Doubleday, and Steve A. Chien of Caltech for NASA’s Jet Propulsion

Laboratory. For more information, down-load the Technical Support Package (freewhite paper) at www.techbriefs.com/tspunder the Software category.


Spacecraft 3D Augmented Reality Mobile AppNASA’s Jet Propulsion Laboratory, Pasadena, California

Spacecraft 3D Application allows one to interactand learn about different missions.

Trade Space Specification Tool (TSST) for Rapid MissionArchitecture (Version 1.2)NASA’s Jet Propulsion Laboratory, Pasadena, California

Trade Space Specification Tool(TSST) is designed to capture quicklyideas in the early spacecraft and missionarchitecture design and categorize theminto trade space dimensions and optionsfor later analysis. It is implemented as anEclipse RCP Application, which can berun as a standalone program. Users rap-idly create concept items with singleclicks on a graphical canvas, and canorganize and create linkages betweenthe ideas using drag-and-drop actionswithin the same graphical view. Various

views such as a trade view, rules view, andarchitecture view are provided to helpusers to visualize the trade space.

This software can identify, explore,and assess aspects of the mission tradespace, as well as capture and organizelinkages/dependencies between tradespace components. The tool supports auser-in-the-loop preliminary logicalexamination and filtering of tradespace options to help identify whichpaths in the trade space are feasible(and preferred) and what analyses

need to be done later with executablemodels. This tool provides multipleuser views of the trade space to guidethe analyst/team to facilitate interpre-tation and communication of the tradespace components and linkages, identi-fy gaps in combining and selectingtrade space options, and guide userdecision-making for which combina-tions of architectural options should bepursued for further evaluation.

This software provides an environ-ment to capture mission trade space

Cov ToC + – ➭

➮

AIntro


http://www.abpi.net/ntbpdfclicks/l.php?201309SSP25A

http://www.abpi.net/ntbpdfclicks/l.php?201309SSP25B

http://www.abpi.net/ntbpdfclicks/l.php?201309SSP25C

http://www.abpi.net/ntbpdfclicks/l.php?201309SSP25D

Raster-Based Approach to Solar Pressure Modeling Combinations of simple geometry yield answers to complex light pressure problems. John H. Glenn Research Center, Cleveland, Ohio

An algorithm has been developed to take advantage of the graphics pro-cessing hardware in modern comput-ers to efficiently compute high-fidelitysolar pressure forces and torques onspacecraft, taking into account the possibility of self-shading due to thearticulation of spacecraft componentssuch as solar arrays. The process is easily extended to compute otherresults that depend on three-dimen-sional attitude analysis, such as solararray power generation or free molec-ular flow drag.

The impact of photons upon aspacecraft introduces small forces andmoments. The magnitude and direc-tion of the forces depend on the mate-rial properties of the spacecraft com-ponents being illuminated. The partsof the components being lit dependson the orientation of the craft withrespect to the Sun, as well as the gim-bal angles for any significant movingexternal parts (solar arrays, typically).Some components may shield othersfrom the Sun.

The purpose of this innovation is toenable high-fidelity computation ofsolar pressure and power generationeffects of illuminated portions of space-craft, taking self-shading from space-craft attitude and movable componentsinto account. The key idea in this inno-vation is to compute results dependentupon complicated geometry by usingan image to break the problem intothousands or millions of sub-problemswith simple geometry, and then theresults from the simpler problems arecombined to give high-fidelity results forthe full geometry.

This process is performed by con-structing a 3D model of a spacecraftusing an appropriate computer lan-guage (OpenGL), and running thatmodel on a modern computer’s 3Daccelerated video processor. This quick-

ly and accurately generates a view of themodel (as shown on a computer screen)that takes rotation and articulation ofspacecraft components into account.When this view is interpreted as thespacecraft as seen by the Sun, then onlythe portions of the craft visible in theview are illuminated.

The view as shown on the comput-er screen is composed of up to mil-lions of pixels. Each of those pixels isassociated with a small illuminatedarea of the spacecraft. For each pixel,it is possible to compute its position,angle (surface normal) from the viewdirection, and the spacecraft material(and therefore, optical coefficients)associated with that area. With thisinformation, the area associated witheach pixel can be modeled as a sim-ple flat plate for calculating solarpressure. The vector sum of theseindividual flat plate models is a high-fidelity approximation of the solarpressure forces and torques on thewhole vehicle.

In addition to using optical coeffi-cients associated with each spacecraftmaterial to calculate solar pressure, apower generation coefficient is addedfor computing solar array power gener-ation from the sum of the illuminatedareas. Similarly, other area-based calcu-lations, such as free molecular flowdrag, are also enabled.

Because the model rendering is sep-arated from other calculations, it is rel-atively easy to add a new model toexplore a new vehicle or mission con-figuration. Adding a new model is per-formed by adding OpenGL code, but afuture version might read a mesh fileexported from a computer-aideddesign (CAD) system to enable veryrapid turnaround for new designs

This work was done by Theodore W.Wright II of Glenn Research Center. Formore information, contact kimberly.a.

[email protected] concerning rights for the com-

mercial use of this invention should beaddressed to NASA Glenn Research Center,Innovative Partnerships Office, Attn:Steven Fedor, Mail Stop 4–8, 21000Brookpark Road, Cleveland, Ohio 44135.Refer to LEW -19019-1.



A typical view (a) of the Crew Exploration Vehicle (CEV)with the solar array gimbals optimized to point thearrays in the Sun direction, and (b) a view of the CEVwith surfaces color-coded to help identify spacecraftmaterial properties.

a

b

elements rapidly and assist users fortheir architecture analysis. This is pri-marily focused on mission and space-craft architecture design, rather thangeneral-purpose design application. Inaddition, it provides more flexibility tocreate concepts and organize the ideas.

The software is developed as an Eclipseplug-in and potentially can be integrat-ed with other Eclipse-based tools.

This work was done by Yeou-Fang Wang,Mitchell Schrock, Chester S. Borden, and RobertC. Moeller of Caltech for NASA’s Jet PropulsionLaboratory. For more information, download

the Technical Support Package (free whitepaper) at www.techbriefs.com/tsp under theSoftware category.


Cov ToC + – ➭

➮

AIntro



This software addresses the demandfor easily accessible NASA JPL imagesand videos by providing a user friendlyand simple graphical user interface that

can be run via the Android platformfrom any location where Internet con-nection is available. This app is comple-mentary to the iPhone version of the

application. A backend infrastructurestores, tracks, and retrieves space imagesfrom the JPL Photojournal andInstitutional Communications Web serv-

Space Images for NASA JPL Android VersionNASA’s Jet Propulsion Laboratory, Pasadena, California

Sample Screen Shots of the Space Images Android Application: The feature graphic (a) is displayed on Google Play Android Market. The title and image thumb-nails (b) are scrollable lists. When clicked, it will show the images in detail, as well as a caption describing the image (c). The user can rate the images by givinga star rating from 1 to 5. In addition, there is an option to share the image by e-mail, Facebook/Twitter, or save it to the user’s Android device (d)

(a)

(b) (c) (d)

Cov ToC + – ➭

➮

AIntro



er, and catalogs the information into astreamlined rating infrastructure.

This system consists of four distinguish-ing components: image repository, data-base, server-side logic, and Androidmobile application. The image repositorycontains images from various JPL flightprojects. The database stores the imageinformation as well as the user rating.The server-side logic retrieves the imageinformation from the database and cate-gorizes each image for display. TheAndroid mobile application is an inter-facing delivery system that retrieves theimage information from the server foreach Android mobile device user. Also

created is a reporting and tracking systemfor charting and monitoring usage.

Unlike other Android mobile imageapplications, this system uses the latestemerging technologies to produceimage listings based directly on userinput. This allows for countless combi-nations of images returned. The back-end infrastructure uses industry-stan-dard coding and database methods,enabling future software improvementand technology updates. The flexibilityof the system design framework permitsmultiple levels of display possibilitiesand provides integration capabilities.Unique features of the software include

image/video retrieval from a selected setof categories, image Web links that canbe shared among e-mail users, sharing toFacebook/Twitter, marking as user’sfavorites, and image metadata search-able for instant results.

This work was done by Jon D. Nelson, Sandy C. Gutheinz, Joshua R. Strom, JeremyM. Arca, Martin Perez, Karen Boggs, and Alice Stanboli of Caltech for NASA’s Jet Propul -sion Laboratory. For more information, seehttp://www.jpl.nasa.gov/apps/spaceimages/.


SIM_EXPLORE: Software for Directed Exploration of Complex Systems NASA’s Jet Propulsion Laboratory, Pasadena, California

Physics-based numerical simulationcodes are widely used in science andengineering to model complex systemsthat would be infeasible to study other-wise. While such codes may provide thehighest-fidelity representation of systembehavior, they are often so slow to runthat insight into the system is limited.Trying to understand the effects ofinputs on outputs by conducting anexhaustive grid-based sweep over theinput parameter space is simply too time-consuming. An alternative ap proachcalled “directed exploration” (see fig-ure) has been developed to harvest infor-mation from numerical simulators moreefficiently. The basic idea is to employactive learning and supervised machinelearning to choose cleverly at each stepwhich simulation trials to run next basedon the results of previous trials.

SIM_EXPLORE is a new computerprogram that uses directed explorationto explore efficiently complex systemsrepresented by numerical simulations.The software sequentially identifiesand runs simulation trials that itbelieves will be most informative giventhe results of previous trials. Theresults of new trials are incorporatedinto the software’s model of the systembehavior. The updated model is thenused to pick the next round of new tri-als. This process, implemented as aclosed-loop system wrapped aroundexisting simulation code, provides ameans to improve the speed and effi-ciency with which a set of simulationscan yield scientifically useful results.

The software focuses on the case inwhich the feedback from the simulationtrials is binary-valued, i.e., the learner isonly informed of the success or failureof the simulation trial to produce adesired output. The software offers anumber of choices for the supervisedlearning algorithm (the method used tomodel the system behavior given the

results so far) and a number of choicesfor the active learning strategy (themethod used to choose which new simu-lation trials to run given the currentbehavior model). The software alsomakes use of the LEGION distributedcomputing framework to leverage thepower of a set of compute nodes. Theapproach has been demonstrated on a

Simulation Trial

Physics-Based Simulator Grading Script Simulation

Result

SupervisedLearning

Active Learning

New Trialto Run

TrainingExamples

Approximate Model of System Behavior Given Current Knowledge

Illustration of the Directed Exploration approach in an asteroid collision application. The centralimage shows the Ida-Dactyl asteroid pair observed serendipitously by the Galileo spacecraft. Planetaryscientists are interested in understanding how such systems form and more generally in how asteroidfamilies form. Physics-based numerical simulations offer a means to gain insight into such systems;however, the simulations are so slow to run that a directed exploration strategy is required.

Cov ToC + – ➭

➮

AIntro


The Robot Sequencing and Visuali za -tion Program (RSVP) is being used in theMars Science Laboratory (MSL) missionfor downlink data visualization and com-mand sequence generation. RSVP readsand writes downlink data products fromthe operations data server (ODS) andwrites uplink data products to the ODS.The primary users of RSVP are membersof the Rover Planner team (part of theIntegrated Planning and Execution Team(IPE)), who use it to perform traversabili-ty/articulation analyses, take activity planinput from the Science and MissionPlanning teams, and create a set of roversequences to be sent to the rover every sol(see figure).

The primary inputs to RSVP are down-link data products and activity plans inthe ODS database. The primary outputsare command sequences to be placed inthe ODS for further processing prior touplink to each rover. RSVP is composedof two main subsystems. The first, calledthe Robot Sequence Editor (RoSE),understands the MSL activity and com-mand dictionaries and takes care of con-verting incoming activity level inputsinto command sequences. The RoverPlanners use the RoSE component ofRSVP to put together commandsequences and to view and manage com-mand level resources like time, power,temperature, etc. (via a transparent real-time connection to SEQGEN).

The second component of RSVP iscalled HyperDrive, a set of high-fidelitycomputer graphics displays of the

Martian surface in 3D and in stereo. TheRover Planners can explore the environ-ment around the rover, create com-mands related to motion of all kinds,and see the simulated result of thosecommands via its underlying tight cou-pling with flight navigation, motor, andarm software. This software is the evolu-tionary replacement for the RoverSequencing and Visualization softwareused to create command sequences(and visualize the Martian surface) forthe Mars Exploration Rover mission.

This work was done by Brian K. Cooper,Scott A. Maxwell, Frank R. Hartman, John R.Wright, Jeng Yen, Nicholas T. Toole, and ZarehGorjian of Caltech; and Jack C. Morrison ofNorthrop Grumman for NASA’s Jet PropulsionLaboratory. For more information, downloadthe Technical Support Package (free whitepaper) at www.techbriefs.com/tsp under theSoftware category.



MER (2003)

ATHLETE (2005)

Phoenix (2008)

MSL (2012)

planetary science application in whichnumerical simulations are used to studythe formation of asteroid families.

This work was done by Michael Burl andEsther Wang of Caltech, and Brian Enke and

William J. Merline of SWRI for NASA’s JetPropulsion Laboratory. For more information,download the Technical Support Package(free white paper) at www.techbriefs.com/tspunder the Software category.


Robot Sequencing and Visualization Program (RSVP)NASA’s Jet Propulsion Laboratory, Pasadena, California

Missions using RSVP.

MPST Software: grl_pef_checkNASA’s Jet Propulsion Laboratory, Pasadena, California

This innovation is a tool used to ver-ify and validate spacecraft sequences atthe predicted events file (PEF) level forthe GRAIL (Gravity Recovery andInterior Laboratory, see http://www.nasa.gov/mission_pages/grail/main/index.html) mission as part of the

Multi-Mission Planning and Sequenc -ing Team (MPST) operations processto reduce the possibility for errors.This tool is used to catch any sequencerelated errors or issues immediatelyafter the seqgen modeling to stream-line downstream processes.

This script verifies and validates the seqgen modeling for the GRAIL MPSTprocess. A PEF is provided as input, anddozens of checks are performed on it toverify and validate the command productsincluding command content, commandordering, flight-rule violations, modeling

Cov ToC + – ➭

➮

AIntro






boundary consistency, resource limits,and ground commanding consistency. Byperforming as many checks as early in theprocess as possible, grl_pef_check stream-lines the MPST task of generating GRAILcommand and modeled products on anaggressive schedule.

By enumerating each check beingperformed, and clearly stating the crite-ria and assumptions made at each step,grl_pef_check can be used as a manualchecklist as well as an automated tool.This helper script was written with a

focus on enabling the user with theinformation they need in order to evalu-ate a sequence quickly and efficiently,while still keeping them informed andactive in the overall sequencing process.

grl_pef_check verifies and validates themodeling and sequence content prior toinvesting any more effort into the build.There are dozens of various items in themodeling run that need to be checked,which is a time-consuming and error-prone task. Currently, no software existsthat provides this functionality. Com -

pared to a manual process, this scriptreduces human error and saves consider-able man-hours by automating andstreamlining the mission planning andsequencing task for the GRAIL mission.

This work was done by Jared A. Call, JohnH. Kwok, and Forest W. Fisher of Caltech forNASA’s Jet Propulsion Laboratory. For moreinformation, contact [email protected].


Jettison Engineering Trajectory ToolLyndon B. Johnson Space Center, Houston, Texas

The Jettison Engineering TrajectoryTool (JETT) performs the jettison analy-sis function for any orbiting asset. It pro-vides a method to compute the relativetrajectories between an orbiting assetand any jettisoned item (intentional orunintentional) or sublimating particlesgenerated by fluid dumps to assesswhether an object is safe to jettison, or ifthere is a risk with an item that was inad-vertently lost overboard. The main con-cern is the interaction and possible re-contact of the jettisoned object with anasset. This supports the analysis that jet-tisoned items will safely clear the vehicle,ensuring no collisions.

The software will reduce the jettisonanalysis task from one that could takedays to complete to one that can be com-

pleted in hours, with an analysis that ismore comprehensive than the previousmethod. It provides the ability to definethe jettison operation relative toInternational Space Station (ISS) struc-ture, and provides 2D and 3D plottingcapability to allow an analyst to performa subjective clearance assessment withISS structures.

The developers followed the SMP tocreate the code and all supporting docu-mentation. The code makes extensiveuse of the object-oriented format of Javaand, in addition, the Model-View-Controller architecture was used in theorganization of the code, allowing eachpiece to be independent of updates tothe other pieces. The model category isfor maintaining data entered by the user

and generated by the analysis. The viewcategory provides capabilities for dataentry and displaying all or a portion ofthe analysis data in tabular, 2D, and 3Drepresentation. The controller categoryallows for handling events that affect themodel or view(s). The JETT utilizesorbital mechanics with complex algo-rithms. Since JETT is written in JAVA, itis essentially platform-independent.

This work was done by Mariusz Zaczek ofJohnson Space Center; and Patrick Walter,Joseph Pascucci, Phyllis Armstrong, PatriciaHallbick, Randal Morgan, and JamesCooney of the United Space Alliance. Formore information, download the TechnicalSupport Package (free white paper) atwww.techbriefs.com/tsp under the Softwarecategory. MSC-25271-1

Real-Time Multimission Event Notification System for Mars RelayNASA’s Jet Propulsion Laboratory, Pasadena, California

As the Mars Relay Network is in constantflux (missions and teams going throughtheir daily workflow), it is imperative thatusers are aware of such state changes. Forexample, a change by an orbiter team canaffect operations on a lander team. Thissoftware provides an ambient view of thereal-time status of the Mars network.

The Mars Relay Operations Service(MaROS) comprises a number of tools tocoordinate, plan, and visualize variousaspects of the Mars Relay Network. As partof MaROS, a feature set was developedthat operates on several levels of the soft-ware architecture. These levels include aWeb-based user interface, a back-end“ReSTlet” built in Java, and databases thatstore the data as it is received from the

network. The result is a real-time eventnotification and management system, somission teams can track and act uponevents on a moment-by-moment basis.

This software retrieves events fromMaROS and displays them to the enduser. Updates happen in real time, i.e.,messages are pushed to the user whilelogged into the system, and queued whenthe user is not online for later viewing.The software does not do away with the e-mail notifications, but augments themwith in-line notifications. Further, thissoftware expands the events that can gen-erate a notification, and allows user-gener-ated notifications.

Existing software sends a smaller subset of mission-generated notifications

via email. A common complaint of userswas that the system-generated e-mailsoften “get lost” with other e-mail thatcomes in. This software allows for anexpanded set (including user-generated)of notifications displayed in-line of theprogram. By separating notifications, thiscan improve a user’s workflow.

This work was done by Michael N. Wallick,Daniel A. Allard, Roy E. Gladden, PaulWang, and Franklin H. Hy of Caltech; andCorey L. Peterson for NASA’s Jet PropulsionLaboratory. For more information, [email protected].


Cov ToC + – ➭

➮

AIntro



PredGuid+A: Orion Entry Guidance Modified for AerocaptureLyndon B. Johnson Space Center, Houston, Texas

PredGuid+A software was developed toenable a unique numerical predictor-cor-rector aerocapture guidance capability thatbuilds on heritage Orion entry guidancealgorithms. The software can be used forboth planetary entry and aerocaptureapplications. Furthermore, PredGuid+Aimplements a new Delta-V minimizationguidance option that can take the place oftraditional targeting guidance and canresult in substantial propellant savings.

PredGuid+A allows the user to set amode flag and input a target orbit’sapoapsis and periapsis. Using bankangle control, the guidance will thenguide the vehicle to the appropriatepost-aerocapture orbit using one of two algorithms: Apoapsis Targeting or Delta-V Minimization (as chosen bythe user).

Recently, the PredGuid guidancealgorithm was adapted for use in skip-

entry scenarios for NASA’s Orion multi-purpose crew vehicle (MPCV). To lever-age flight heritage, most of Orion’sentry guidance routines are adaptedfrom the Apollo program.

This work was done by Jarret Lafleur ofJohnson Space Center. For more information,download the Technical Support Package(free white paper) at www.techbriefs.com/tspunder the Software category. MSC-25199-1

Mobile Timekeeping Application Built on Reverse-EngineeredJPL InfrastructureNASA’s Jet Propulsion Laboratory, Pasadena, California

Every year, non-exempt employeescumulatively waste over one man-yeartracking their time and using the time-keeping Web page to save those times.This app eliminates this waste.

The innovation is a native iPhoneapp. Libraries were built around areverse-engineered JPL API. It repre-sents a punch-in/punch-out para-digm for timekeeping. It is accessible

natively via iPhones, and features easeof access.

Any non-exempt employee can nativelypunch in and out, as well as save and viewtheir JPL timecard. This app is built oncustom libraries created by reverse-engi-neering the standard timekeeping appli-cation. Communication is through cus-tom libraries that re-route traffic throughBrowserRAS (remote access service).

This has value at any center whereemployees track their time.

This work was done by Robert J. Witoff of Caltech for NASA’s Jet PropulsionLaboratory. For more information, [email protected].


Advanced Query and Data Mining Capabilities for MaROSNASA’s Jet Propulsion Laboratory, Pasadena, California

The Mars Relay Operational Service(MaROS) comprises a number of toolsto coordinate, plan, and visualize vari-ous aspects of the Mars Relay network.These levels include a Web-based userinterface, a back-end “ReSTlet” built inJava, and databases that store the dataas it is received from the network. Aspart of MaROS, the innovators havedeveloped and implemented a featureset that operates on several levels of thesoftware architecture.

This new feature is an advancedquerying capability through either theWeb-based user interface, or througha back-end REST interface to accessall of the data gathered from the net-work. This software is not meant toreplace the REST interface, but toaugment and expand the range ofavailable data. The current RESTinterface provides specific data that is

used by the MaROS Web applicationto display and visualize the informa-tion; however, the returned informa-tion from the REST interface has typi-cally been pre-processed to returnonly a subset of the entire informationwithin the repository, particularly onlythe information that is of interest tothe GUI (graphical user interface).The new, advanced query and datamining capabilities allow users toretrieve the raw data and/or to per-form their own data processing. Thequery language used to access therepository is a restricted subset of thestructured query language (SQL) thatcan be built safely from the Web userinterface, or entered as freeform SQLby a user. The results are returned in a CSV (Comma Separated Values)format for easy exporting to third-party tools and applications that can

be used for data mining or user-defined visualization and interpreta-tion. This is the first time that a serv-ice is capable of providing access to allcross-project relay data from a singleWeb resource.

Because MaROS contains the data fora variety of missions from the Mars net-work, which span both NASA and ESA,the software also establishes an accesscontrol list (ACL) on each data recordin the database repository to enforceuser access permissions through a multi-layered approach.

This work was done by Paul Wang,Michael N. Wallick, Daniel A. Allard, RoyE. Gladden, and Franklin H. Hy of Caltechfor NASA’s Jet Propulsion Laboratory.

This software is available for commerciallicensing. Please contact Dan Broderick [email protected] 48575

Cov ToC + – ➭

➮

AIntro



Information Sciences

Space Place PrimeNASA’s Jet Propulsion Laboratory, Pasadena, California

Space Place Prime is public engage-ment and education software for use oniPad. It targets a multi-generationalaudience with news, images, videos, andeducational articles from the SpacePlace Web site and other NASA sources.

New content is downloaded daily (orwhenever the user accesses the app) viathe wireless connection. In addition tothe Space Place Web site, several NASARSS feeds are tapped to provide new con-tent. Content is retained for the previousseveral days, or some number of editions

of each feed. All content is controlled onthe server side, so features about the lat-est news, or changes to any content, canbe made without updating the app in theApple Store. It gathers many popularNASA features into one app.

The interface is a boundless, slid-able-in-any-direction grid of images,unique for each feature, and iconizedas image, video, or article. A tap opensthe feature. An alternate list modepresents menus of images, videos, andarticles separately. Favorites can be

tagged for permanent archive. Face -book, Twitter, and e-mail connectionsmake any feature shareable.

This work was done by Austin J.Fitzpatrick, Alexander Novati, Diane K.Fisher, and Nancy J. Leon of Caltech, andRuth Netting of NASA HQ for NASA’s JetPropulsion Laboratory. For more information,contact [email protected].


MPST Software: grl_suppdocNASA’s Jet Propulsion Laboratory, Pasadena, California

Due to the nature of the GRAIL mis-sion, the GRAIL Mission Planning andSequence Team (MPST) is required togenerate ground and uplink productsfaster than ever done before. The exist-ing correct_transmitter_min_dur toolthat provides a similar function togrl_suppdoc lacks the ability to operateaccurately or quickly enough to supportthe rapid turnaround required of theGRAIL MPST.

The GRAIL MPST was required tobuild this new tool to facilitate the groundand uplink generation processes to meeta tight sequence development timeline.

The grl_suppdoc tool enables the GRAILMPST to generate automatically DeepSpace Network (DSN) transmitter sup-pressions based on short uplinks that arefound in the ground/modeled PredictedEvents File (PEF).

The grl_suppdoc script automaticallygenerates applicable DSN uplink sup-pressions in the form of a SpacecraftActivity Sequence File (SASF) to protectthe GRAIL project from short DSNuplink windows, which can be cause foroperator error at the DSN antennas.Currently, no software exists that pro-vides this functionality at the efficiency

required for GRAIL sequence teamoperations. Compared to a manualprocess, this script reduces human errorand saves considerable man-hours byautomating and streamlining the mis-sion planning and sequencing task forthe GRAIL mission.

This work was done by Jared A. Call andJohn H. Kwok of Caltech for NASA’s JetPropulsion Laboratory. For more information,contact [email protected].


Planning Coverage Campaigns for Mission Design and Analysis:CLASP for DESDynlNASA’s Jet Propulsion Laboratory, Pasadena, California

Mission design and analysis presentschallenges in that almost all variables arein constant flux, yet the goal is to achievean acceptable level of performanceagainst a concept of operations, whichmight also be in flux. To increase respon-siveness, automated planning tools areused that allow for the continual modifi-cation of spacecraft, ground system,staffing, and concept of operations, whilereturning metrics that are important tomission evaluation, such as area covered,peak memory usage, and peak datathroughput. This approach was applied tothe DESDynl mission design using the

CLASP planning system, but since thisadaptation, many techniques havechanged under the hood for CLASP, andthe DESDynl mission concept has under-gone drastic changes.

The software produces mission evalua-tion products, such as memory high-water marks, coverage percentages,given a mission design in the form ofcoverage targets, concept of operations,spacecraft parameters, and orbitalparameters. It tries to overcome the lackof fidelity and timeliness of missionrequirements coverage analysis duringmission design.

Previous techniques primarily use Excelin ad hoc fashion to approximate key fac-tors in mission performance, often fallingvictim to overgeneralizations necessary insuch an adaptation. The new programallows designers to faithfully representtheir mission designs quickly, and getmore accurate results just as quickly.

This work was done by Russell L. Knight,David A. McLaren, and Steven Hu of Caltechfor NASA’s Jet Propulsion Laboratory. For moreinformation, contact [email protected].

This software is available for commercial licens -ing. Please contact Dan Broderick at [email protected]. Refer to NPO-48598.

Cov ToC + – ➭

➮

AIntro

• Sharpen your simulation skills with minicourses

• Discover new multiphysics modeling techniques

• Connect with COMSOL users

• Showcase your design projects

SIGN UP TODAY!

www.comsol.com/conference2013

OCTOBER 9-11, 2013 • BOSTON MARRIOTT NEWTON

GOLD SPONSORS

SILVER SPONSORS

MEDIA SPONSORS

The Premier Event for Multiphysics Simulation

COMSOLCONFERENCEBOSTON20 1 3

© 2013 COMSOL. COMSOL and COMSOL Multiphysics are registered trademarks of COMSOL AB.


Cov ToC + – ➭

➮

AIntro

http://www.abpi.net/ntbpdfclicks/l.php?201309SSPC3

© Copyright 2013 COMSOL. COMSOL, COMSOL Multiphysics, Capture the Concept, COMSOL Desktop, and LiveLink are either registered trademarks or trademarks of COMSOL AB. All other trademarks are the property of their respective owners, and COMSOL AB and its

®

Multiphysics tools let you build simulations that accurately replicate the important characteristics of your designs. The key is the ability to include all physical eff ects that exist in the real world. To learn more aboutCOMSOL Multiphysics, visit www.comsol.com/introvideo

Verify and optimize your designs with COMSOL Multiphysics.

ELECTRICALAC/DC ModuleRF ModuleWave Optics ModuleMEMS ModulePlasma ModuleSemiconductor Module

MECHANICALHeat Transfer ModuleStructural Mechanics ModuleNonlinear Structural Materials ModuleGeomechanics ModuleFatigue ModuleMultibody Dynamics ModuleAcoustics Module

FLUIDCFD ModuleMicrofl uidics ModuleSubsurface Flow ModulePipe Flow ModuleMolecular Flow Module

CHEMICALChemical Reaction Engineering ModuleBatteries & Fuel Cells ModuleElectrodeposition ModuleCorrosion ModuleElectrochemistry Module

MULTIPURPOSEOptimization ModuleMaterial LibraryParticle Tracing Module

INTERFACINGLiveLink™ for MATLAB®

LiveLink™ for Excel®

CAD Import ModuleECAD Import ModuleLiveLink™ for SolidWorks®

LiveLink™ for SpaceClaim®

LiveLink™ for Inventor®

LiveLink™ for AutoCAD®

LiveLink™ for Creo™ ParametricLiveLink™ for Pro/ENGINEER®

LiveLink™ for Solid Edge®


Product Suite

COMSOL Multiphysics

WATER PURIFICATION: Model of a 6 m long ozone reactor.

and allow estimation on residence time of chemical species.


Cov ToC + – ➭

➮

AIntro



software tech briefs september 2013

Documents