Ajit Kelkar, Ph.D. - Nanomanufacturing Conference

NANOENGINEERED MATERIALSAND THEIR APPLICATIONSByAjit D. KelkarProfessor and Chairman, NanoengineeringJoint School of Nanoscience and NanoengineeringAssociate Director, Center for Advanced Materials and Smart StructuresGreensboro, NC 27401Nanomanufacturing ConferenceAugust 15, 2012, Greensboro, NC

AEROSPACE MATERIALS• Strength and stiffness• Impact resistance (delamination resistance)• Longer fatigue life• Lightweight– increased load carrying capacity– Increased range– low noise– comfort– low maintenance costs

NASA Nanotechnology RoadmapC A P A B I L I T YMulti-Functional MaterialsHigh StrengthMaterials(>10 GPa)ReusableLaunch Vehicle(20% less mass,20% less noise)RevolutionaryAircraft Concepts(30% less mass,20% lessemission, 25%increased range)AutonomousSpacecraft(40% less mass)Bio-Inspired Materialsand ProcessesAdaptiveSelf -RepairingSpace MissionsIncreasing levels of system design and integrationMaterials• Single-wallednanotube fibers• Nanotubecomposites• Integralthermal/shapecontrol• Smart “skin”materials• BiomimeticmaterialsystemsElectronics/computing• Low-Power CNTelectroniccomponents• Molecularcomputing/datastorage• Fault/radiationtolerantelectronics• Nano electronic“brain” for spaceExploration• BiologicalcomputingSensors, s/ccomponents• In-spacenanoprobes• Nano flightsystemcomponents• Quantumnavigationsensors• Integratednanosensorsystems2002 2004 2006 2011 2016• NEMS flightsystems @ 1 µW>

POLYMER NANOCOMPOSITES• Layered silicate– reduce flammability and maintain the transparency of apolymer matrix, typical loadings 2% to 4%• Nanofibers and Carbon nanotube-polymernanocomposites– PNC properties are dependent upon SWNT, MWNT, purity,defects, aspect ratios, loading, functionalization, dispersion ,alignment of nanotubes• High-Performance Resins

• Structural Composites• Applications• Typical failure mechanismsOUTLINE• Role of Nanoengineered Materials• Electrospun nanofibers• Multifunctional materials using XD-CNTs• Alumina particles• Atomistic Modeling of Nanoengineered Materials

Increasing Use of Composite Materials78777711%50%757/7673%7471%MaterialsCompositeSteelTitaniumAluminumMiscellaneousBilly Roeseler, Boeing -Composite Structures first 100 Years

Boeing 787Carbon laminateCarbon sandwichOther compositesAluminumTitaniumTitanium/steel/aluminumTitanium15%Steel10%Aluminum20%Other5%Billy Roeseler, Boeing -Composite Structures first 100 Years

LIGHT BUSINESS JETS(TAKE-OFF WEIGHT LESS THAN 12,500 LBS.)Wing FlapFuture small business jet utilizing braided composites

FAILURE PATTERNS OF STATIC TENSILE AND FATIGUELOADED CARBON/ VINYL ESTER SPECIMENS(BRAID ANGLE 25 0 )StaticTensile85% ofUTS75% ofUTS65% ofUTS55% ofUTS45% ofUTSSpecimen which was loaded 45% of UTS failed but didn’t break intotwo pieces. The test was stopped.

H-46/SEA KNIGHT REENGINEERINGSPONSOR: NAVAIR-CHERRY POINT/L3/VX AEROSPACE

INSTALLED TUNNEL COVERS

FLOORBOARD DESIGN

Before Testing

Only area to visibly see fiber damage

At 8,006 lbs pull in the 90 degree orientation, mountingfasteners failed. Panel displacement – 1.852 @ 8,000 lbs.Original panel test, 90 degree pull failed at 5,619 lbs. w/1.081 in. displacement.New panel at 5,619 lbs. – 1.2 in. panel displacement

ELECTROSPUN FIBERS ARE BEING ADDEDTO PREVENT INTERLAMINAR SHEAR

Reengineering of Nose Bay DoorPossible front face impact damage/delaminations

Composite Armored Vehicle (CAV)PROGRESSIVE FATIGUE DAMAGES2-GLASS/C-50Phenolic LinerEMI MeshRubberThick S2 Glass/Vinyl EsterCompositeAluminaCeramic TileDurability Cover1.000.9531.2%41.6%36.4%E / E o0.9026%28.5%0.850.800.0 0.2 0.4 0.6 0.8 1.0N / N fSPONSOR: US ARMY

Typical Failures in Composites due toDelaminations

INTERLAMINAR PROPERTIES• Delamination of composite laminates is critical because ofthe sub-surface nature of delamination.• Traditional methods such as Stitching, Z-pinning, whileimproving interlaminar properties in woven composites,lead to a reduction of the in-plane properties.• Other methods for delamination resistance leads toincrease in weight or are too costly and time consuming.• Clearly there is a need for an alternate method to improveinterlaminar properties of woven compositesWould Nanoengineered Materials help?

Myth vs. Reality• Nano materials are built atom by atom, hence theywill be very expensive and will not have practicalapplications• However, there is no need to build an entirestructure atom by atom.– Will nano fibers and nano particles, which are justa small fraction by weight, if hybridized withtraditional composite materials, have a dramaticeffect on the multi functional properties ofstructures?

NANOENGINEERED MATERIAL - IElectrospun Nanofibers

Nanofibers Manufacturing usingElectrospinning• Electrospinning is a non-contact drawing process in which apolymer solution droplet emanating from the tip of a spinneret isattracted towards a grounded collector under the action of ahydrostatic surface tension and a potential difference

Effects of Processing Parameters669 nm 740 nmSetup 1: 669 nm15 kV and 70 mmSetup 2: 740 nm15 kV and 100 mmSetup 3: :515 nm18 kV and 70 mmSetup 4: 665 nm18 kV and 100 mm515 nm 665 nm

Temperature EffectsNON-SINTEREDSINTERED AT 600 0 CSINTERED AT 900 0 CSintering of Electrospun Nanofibers is an important procedure as it leadsto reduction in diameter of nanofibers and also there is refinement incomposition and porosity due to evaporation of solvents and shrinkage.

TEOS Electrospun Nanofibers• TEOS electrospun nanofibers are suitable for the development ofdelamination resistant composites.• Delamination of composites due to low velocity impacts is highlycritical due to its subsurface nature.• Wind Mill Blades, Composite Bridge Decks, Naval Floor Boards areprone to low and high velocity impacts.

Homogenized Properties• Improvement in the moduluswas observed with nanofiberreinforcement than with NeatEpon Resin.• Improvement in tensilemodulus compared tomicrofiber specimen.SpecimenMax.Load(Kip)Tensilestrength(Ksi)Modulus(Msi)E-Glass 1 0.412 6.697 0.535E-Glass 2 0.473 7.759 0.506Espun 1 0.642 10.538 0.484Espun 2 0.616 10.017 0.493• If area under the curve isanalyzed, toughness of nanofiber composite is almostdouble than the micro fibercomposites.

Microfiber Vs. Nanofiber• Homogeneous Dispersion of Nanofibers• Reinforcement Effect in Resin Reach Zones• Improvement in Tensile Strength over 40%as compared to Microfiber Specimen

TABLE 2. SUMMARY OF MSBS ANDSBS TEST (ASTM D2344)SpecimenMSBS forNeatSpecimenMSBS withElectrospunFibersSBS withElectrospunFibersMSBS withElectrospunFibersPercentage ofElectrospunFibersSinteringTemperatureAvg. SBSStrength(psi)PercentageChange-N.A- -N.A.- 5.51 E+3 Base Value15% 300 0 C 5.17 E+3 -6.17 %15% 900 0 C 6.42 E+3 +16.51 %15% 900 0 C 7.12 E+3 +29.21 %

Failure Analysis for SBS TestSpecimen ShowingTEOS Fiber layersFailure During SBS TestInteraction of Individual Fibersand layers during MSBS FourPoint Test

NANOENGINEERED MATERIAL - IICarbon Nanotubes (XD-CNTs)

MOTIVATIONThere is a considerable interest to develop nanocomposites with multifunctional propertiesPresently, XD-CNTs are being considered as aprime constitutive material in conjunction withcarbon fibers and epoxy resin systemThis newly developed multifunctional materialis expected to have superior electrical andthermal propertiesAlso it is important to study XD-CNTs effect onmechanical properties

Lightning Strikes

498 K448 K398 K298 K348 KDEVELOPMENT OF MULTIFUNCTIONALPOLYMER USING XD-CNTS

OBJECTIVESTo disperse XD-CNTs into neat resinTo use EPON 862-W resin dispersed with XD-CNTs inconjunction with H-VARTM process to manufactureIM7-EPON 862-W (mixed with XD-CNTs) compositesTo study effects of two different XD-CNTs loadings[0.015% and 0.15% by weight] on tensile and flexuralproperties of compositesTo study effects of functionalized XD-CNTs on theproperties of composites

XD-CNTsManufacturer: Unidym, Inc.Chemical Name: Fullerene NanotubeFormula: CarbonChemical Family: Graphitic carbon

XD-CNTsXD nanotubes are a mixture of single wallCNT, multi wall CNT, and carbon blackAre specifically made for electricalconductivity purposes.Due to the similar transport mechanisms ofheat and electric potential, XD gradenanotubes are also very effective inincreasing thermal conductivity

Dispersion of XD-CNTsBefore XD-CNTs are used, they need to beuniformly dispersed in the resinVarious methods which are used for dispersionincludes:High Shear MixtureUltrasonicationFunctionalisationOxidationAcid TreatmentAnnealingMagnetic PurificationMicor Filttration

Dispersion of XD-CNTsHigh rate Shear MixerProblems encounteredAir bubbles in the resinDamage to XD-CNTs outer wallReversible high rate Shear MixerTwo different loadings were used0.015% by weight0.15% by weight

Dispersion of XD-CNTs usingUltrasonicationIn this technique particles are separated due to ultrasonicvibrations.Agglomerates of different nanoparticles are forced to vibrateThe dispersion is highly dependable on the surfactant, solventand reagent used.When an acid is used, the quality of the SWCNTs depends onthe exposure time.When the tubes are exposed to the acid for a short time, onlythe metal solvates, but for a longer exposure time, the tubescan have chemical damageIn the present study CNTs of different loadings were mixed in asolvent composed of ethanol and tolueneThe mixture was sonicated for one hourThis mixture was then used in H-VARTM procedure aspresented next

TENSILE TESTS0%, 0.015% and 0.15% CARBONNANOTUBES TENSILE COUPONS

FLEXURAL TESTTHREE POINT BEND NEAT RESIN, 0.015% AND 0.15%SWCNTS COUPONS

FRACTOGRAPHYCross Section of 0.015% CNTResin FractureCross Section of 0.15% CNTResin FractureCross Section of Neat Resin FractureMICROSCOPIC EXAMINATION OF FAILED THREE POINT BEND SPECIMENS

XD-CNTs FunctionalizationUse of HNO 3 removes the metal catalyst.Usually pure SWCNTs remain in suspended formHNO 3 only interacts with the metal catalyst.SWCNTs does not get affected

COUPONS WITH FUNCTIONALIZED XD-CNTs

TENSILE AND FLEXURALCHARACTERIZATIONAll specimens were manufactured usingultrasonication (functionalized and nonfunctionalizedXD-CNTs)Tensile tests were performed using ASTM D638standard.Flexural tests were performed using ASTM D790standard.Neat resin and resin with 0.015% and 0.15% byweight XD-CNTs concentration were used.

Sample Set 1 Preparation – LayoutSample 1-1(0.015 wt% XD CNT)Sample 1-2(0.15 wt% XD CNT)T1 T2 T3 T4 T5 T6Sample 1-3(0.015 wt% f-XD CNT)Sample 1-4(0.15 wt% f-XD CNT)At least 1” marginfrom the edgesResin flow directionF1 F3 F5F2 F4 F6

Tensile modulus (GPa)Tensile modulusTensile Modulus1201008060402000.015 wt%0.15 wt%f-0.015 wt%f-0.15 wt%Tensile modulus was minimally affected by CNT loading andfunctionalization at 0.015 wt% and 0.15 wt%.

Flexural modulus (GPa)Flexural modulus (GPa)Flexural Modulus7060504030201000.015 wt%0.15 wt%f-0.015 wt%f-0.15 wt%Flexural modulus was minimally affected by CNT loading andfunctionalization at 0.015 wt% and 0.15 wt%.

Flexural strength (MPa)Flexural strength (MPa)Flexural Strength100080060040020000.015 wt%0.15 wt%f-0.015 wt%f-0.15 wt%Flexural strength increases with CNT loading and functionalization.

Flexural strength (MPa)Flexural strength (MPa)% Strain to Break (MPa)%Strain to breakTensile modulus (GPa)Tensile modulusFlexural modulus (GPa)Flexural modulus (GPa)Effects of CNT Filtration1207010080606040200Resin flow direction504030Resin flow directionInlet Outlet Inlet Outlet0.015 wt% 0.15 wt% f-0.015 wt% f-0.15 wt%0.015 wt% 0.15 wt% f-0.015 wt% f-0.15 wt%10002.580026004002000Resin flow direction1.510.50Resin flow directionInlet Outlet Inlet Outlet0.015 wt% 0.15 wt% f-0.015 wt% f-0.15 wt%0.015 wt% 0.15 wt% f-0.015 wt% f-0.15 wt%Mechanical properties show no apparent CNT filtration effect.

THERMAL/COMPRESSION PROPERTIES

Compression PropertiesSampleDescriptionMax. StressksiYield StressksiCompressiveModulusksiNeat resin 31.3 18.3 173.00.015% 40.8 12.2 175.00.150% 56.3 10.7 196.60.500% 25.1 26.6 173.51.000% 25.7 22.9 180.6

THERMAL PROPERTIESSampleAVG ThermalConductivity (W/mK)Standard Deviation(W/mK)0.000% 0.2386 0.00080.015% 0.2391 0.00200.150% 0.2394 0.00070.500% Top 0.2577 0.00210.500% Bottom 0.2610 0.00071.000% Top 0.2777 0.00121.000% Bottom 0.2760 0.0012

NANOENGINEERED MATERIAL - IIIAlumina Nanoparticles

Material System/ Composition• Hybrid composite material system of:– Matrix component (Thermoset epoxy based)• EPON 9554 (Bis-phenol A)• Epicure 9504 (polyamine)– S2 Fiberglass reinforcement• 10k Plain Weave• Ballistic grade– 110nm Particulate alumina (manufacturer: Sasol Inc)• Dispal D23 Virgin• Dispal D23 Silane functionalized– Tris-2-methylethyl vinyl silane -T2MEVS (from Sigma-Aldrich)- Additive coupling agent

Material System Configuration• Hybrid composite of alumina nanoparticles andepoxy– With reinforcing glass fibers• Alumina nanoparticle integration– Resin Modification• Particle grafted in polymer matrix– Fiber Modification• Particles dispersed on interfacing ply layersWoven PlyParticulate Film

Particulate DispersionSonication and FunctionalizationSonicationAluminadispersed byultrasonicagitation @2KHz frequencyNanomaterial FunctionalizationAlumina particle is coated with silanecompound Tris-2-methylethyl Vinyl Silane(T2MEVS)S onicationCoated ParticleNano - sizedAluminaparticleSolution of 50%water/ 50%methanol withsilane T2MEVSFurther Processing afterresin/fiber modificationby VARTM60

ProcessingResin ModificationPure Resin+Alumina particlesResin Modification/SonicationModified 9504 ResinNano-particulateAlumina (F/NF)Epikure 9554 Curing AgentMold setup and infusion (VARTM)Formulation WindowSonicationMixing andDegassingResinModifiedResinMoldVARTM Processing61

ProcessingFiber Modification• Silane is added after sonication for functionalizedalumina laminateW ater +Methanol ( 1 :1 )Nano - partic ulateA luminaSilane added forFunctionalizationSonicationAtomizedsprayModifiedF iberVARTM ProcessingMoldHeating andDrying @ 220F62

Alumina Hybrid Composite LaminateMaterialConfiguration1 Baseline: EPON/ S2 Glass2 Resin Modification with pristine Alumina3 Resin Modification with Functionalized Alumina4 Fiber Modification with pristine Alumina5 Fiber Modification with Functionalized Alumina

Mode I Fracture Toughness• Fracture toughness observations– Stick and slip profile were observed in all load –displacement response possibly due to large towsize of 3/16"– Fiber bridging was observed all material systemsshow good energy dissipation in the materialsystem– Alumina inclusion showed improved G IC over 2phase composite systemFracture toughness at initiation G IC– Functionalization improved crackresistance in both resin and fibermodificationMAT 1 MAT 2 MAT 3 MAT 4 MAT 5G IC MBT289.7± 5.61%377.9± 5.26%429.5± 7.48%439.3±10.78%505.9±7.96%AverageMAT 1 289% DiffFunct Non-Func % DiffResin Modification 429 377 13 %Fiber Modification 505 439 15 %MAT 2 377 30 %MAT 3 429 48 %MAT 4 439 51 %MAT 5 505 74 %

ATOMISTIC MODELINGTo develop fully cured stacked bonded square molecular modelswith cross-linking structure of EPON 862 resin and curing agent WTo develop MD model for the combined EPON 862-W and SWCNTsystemPredict fundamental mechanical properties ofEPON 862 – WSWCNTEPON 862-W and SWCNT systemusing Material Studio (Accelrys Inc.)The predicted properties include:‣ Density‣ Young's modulus‣ Glass transition temperature (Tg)

Modeling ApproachManufacturer suggests the ratio of EPON 862 (DGEBF) and W (DETDA) as 100:26.4Molecular weight of one DGEBF molecule is 312.3 amuMolecular weight of one DETDA is 178.279 amu8 DGEBF and 4 DETDA molecules gives the mass ratio as 2723.325:713.116 whichis equivalent to 100:26.2Hence a Quad cell with 8 DGEBF and 4 DETDA is selected to represent fully curedmodelEPON 862W DETDA

Modeling ApproachUnit Cell Development (Cross-linking of DEGBF and DETDA)8:4 DGEBF:DETDA Unit CellCure ReactionModel

Modeling ApproachMacromolecular Construction using “Amorphous Cell” ModuleAmorphous Cell DetailsForcefield => CompassTarget Density => 1.2 gm/ccPeriodic cell is used to achievemacromolecular structure8:4 DGEBF:DETDA Unit Cell

Simulated AnnealingSuggested curing cycle of epoxy resin at 250 °F (77 °C) for two hoursand then 350 °F (177 °C) for two hours.The resin is then cooled to room temperatureIn simulations following procedure was adapted:‣ Amorphous structure was subjected to energy minimization usingensemble NVT*‣ Structure was equilibrated for 100 picoseconds (ps) followed by‣ MD simulation for 200 ps at room temperature (25 °C)‣ The temperature is then raised to 225 °C‣ MD simulations were conducted using the ensemble NPT** for 200 ps‣ Temperature was then cooled in the increment of 10 °C‣ Each simulation was conducted with an interval of 1 femtosecond (fs)‣ Final configuration obtained after each run was used for the next run‣ Density was reported after each run*Constant no. of Particles, Constant Volume and Constant Temp. ** Constant no. of Particles, Constant Pressure and Constant Temp.

298 K348 KSimulated AnnealingIntermediate Atomistic Structures in Simulated Annealing498 K448 K398 K

Computational DetailsNumber of atoms: 468Simulation time per 10 °C : 200 psTime Step: 1 fsNo. of Processors: 4Time used by 200000 steps is 1 hours 0 mins 57.64 secs(0.018 secs per step)Total time for Discover Dynamics portion of annealing is approx. 21hours.Total time for Analysis portion of Discover module for onetemperature using 100 trajectories is approx. 68 hours

ResultsPredicted Glass Transition Temperature (Tg) = 125 °C

Statistical AnalysisNTabular Results for Statistical analysis‣ Table shows that increasing number of trajectories does not necessarily improvethe predicted value of Young’s modulus‣ Same trend was observed for other material properties.TrajectoriesTotal 100 50 25 10Valid 94 46 23 8Omitted (0.1 and 19.9) 6 4 2 2Mean (GPa) 4.847 4.839 4.9 4.875Std. Deviation 0.9904 1.0864 0.9065 0.58Skewness -0.207 -0.039 -0.071 0.868

SWCNT ResearchPredict fundamental mechanical properties of SWCNT (m,n)* usingMaterial Studio (Accelrys Inc.)‣ Integer parameter, N controls the overall size of the nanotube.‣ Integer parameter, M controls the chiral angle, or twist, of thegraphite sheet used to construct the nanotube.‣ In the present study N = 6, and M = 6 was used.The predicted properties include:‣ Density‣ Young's modulus, and‣ Poisson’s ratio

Modeling ApproachConstruct SWNT (6,6) in Material StudioVolume = 2976 A 3No Distortion After MinimizationVolume = 1992.2 A 3Distortion After Minimization

Modeling ApproachFor a density of 2.4 gm/cc the lattice size is 1992.2 A 3 which resultsinto distortion of SWCNTThe minimum lattice size required to avoid distortion is 2976 A 3 ,which results into a lower density of 1.61 gm/cc.Lattice volume is increased by the increment of 10% andcorresponding properties were reportedA graph of Material Property vs density was plotted.Material Properties were predicted by extrapolating the above graphat the target density of 2.4 gm/cc

ResultsPrediction of Young’s modulus = 1.093 TPa at density = 2.4 gm/ccYoung modulus for 5 lowdensity CNT models and theextrapolation value for 2.4 g/cc

Modeling of the resin and SWCNTMaterial system models used inproperties analysis• Side view and top view of an atomisticmodel of a single unit quad cell:– 8 Epon 862 molecules– 4 DETDA moleculesSWCNT (3) + 2 QuadCells (11%)(a)SWCNT (4) + 3 QuadCells (9.78%)(b)SWCNT (4) + 4 QuadCells (7.33%)(c)Three work modelswith different CNTvolume fractions werebuilt for analysis

298318338358378398418438458478498Annealing of the three models at three different densitiesMixture density vs volume percentage of CNT1.269.78% 7.33% 11.00%1.241.221.201.181.161.141.121.101.08volume% original d final d theo dens Yc4t4r1 7.33% 1.1415 1.2117 1.2878 49.41c4t3r1 9.78% 1.1382 1.2437 1.31736 62.51c3t2r1 11.00% 1.136 1.2161 1.332 70.25

1.1551.1651.1751.1851.1951.2051.2151.2251.2351.2451.2551.2651.2751.2851.2951.3051.3151.325Y [GPa]Young modulus vs density for different SWCNT volumefractionsInput: Density, Young modulus, CNT volume fractionYoung modulus vs density for diff CNT%80.076 GPa70.068 GPa11%9.78%60.07.33%56 GPa50.040.030.07.33%9.78%11.00%Linear (7.33%)Linear (9.78%)Linear (11.00%)20.010.00.0volume% theo densdensity [g/cc]1.288 1.317 1.332Y@ right densc4t4r 7.33% 1.2878 49.41 53.54 56.28 56c4t3r 9.78% 1.31736 62.51 65.39 67.75 68c3t2r 11.00% 1.332 70.25 70 75.02 76Y

1.1551.2551.3551.4551.5551.6551.7551.8551.9552.0552.1552.2552.355[GPa]Estimated Young modulus for0% to 100% SWCNT volume fractionEstimated Young modulus vs theoretical density of the reinforced resin1,000.0900.0800.0y = 0.8294x - 56.155R 2 = 0.9987700.0600.0500.0400.0300.0200.0100.00.0mixture density [g/cc]

0.000%0.333%0.666%1.000%1.333%1.666%1.999%2.332%2.666%2.999%3.332%3.665%3.998%4.332%4.665%4.998%5.331%5.664%5.998%6.331%6.664%6.997%7.330%7.664%7.997%8.330%8.663%8.996%9.330%9.663%9.996%10.329%10.662%10.996%[GPa]Estimated Young modulus vs SWCNT volume fraction in reinforced resinEstimated Young modulus vs volume percentage of CNT in the resin8070y = 0.541x + 5.0784R 2 = 0.99676050403020100CNT volume percentage [%]

ConclusionsDeveloped MD model EPON 862-WUsed simulated annealing technique to predict glass transition temperature(Tg) and fundamental material properties‣ Predicted Tg matched with the experimental results‣ The predicted modulus of elasticity showed large deviation fromexperimental value• Developed MD model for SWCNT‣ The lattice dimensions plays critical role in preserving theconfiguration of CNT‣ Predicted density and modulus depends on the lattice dimensions‣ Study indicated linear variation of modulus with the density‣ Accurately predicted the modulus of elasticity value usingextrapolation technique• Developed MD model for EPON 862-W and SWCNT‣ Predicted Tg showed an increased value compared to the neat resinTg‣ The predicted modulus of elasticity showed an linear increase withthe SWCNT volume fraction increase

ACKNOWLEDGEMENTS• Funding from ONR, Air Force, NASA, VX AEROSPACE,NAVAIR, ARMY and FAA• Dr. Ram Mohan, Dr. Jim Ryan• Dr. Christopher Grace (GE/Rolls Royce), Dr. Jitendra Tate(University of Texas), Dr. Pramod Chaphalkar (Michigan),Dr. Oladapo Akinyede (Cummins), Dr. Francis Komuves(Volvo), Dr. Sachin Shendokar (Bharati Vidyapeeth), Dr. EvanKimbro• Center for Advanced Materials and Smart Structures

On the Lighter Side – In case Nothing Works