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Cfd Research Corporation

$220M obligated·409 awards·7 agencies·14 NAICS
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Federal Contracts

Showing contracts 501–534 of 534 total. Sorted by action date, most recent first. Excludes $0 modifications.

DateAgencyPIIDNAICSDescriptionAmount
Jul 14, 2016Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZLFA865016P2684541711IGF::OT::IGF REAL TIME AEROSERVOELASTICITY SIMULATION TOOL FOR A/C LIFE$150K
Jul 14, 2016Department of DefenseW4GG HQ US ARMY TACOMW56HZV16C0135541712IGF::OT::IGF$100K
Jul 13, 2016Department of DefenseFA9101 AEDC PKP PROCRMNT BRFA910116M0046541712IGF::OT::IGF SBIR PHASE I AF161-024, PREDICTION OF HYPERSONIC BOUNDARY LAYER TRANSITION IN WIND TUNNELS AND FLIGHT$150K
Jul 12, 2016Department of DefenseW4PZ USA MED RSCH ACQUIS ACTW81XWH16C0059541712IGF::OT::IGF. DHP PHASE I ENTITLED, "PERSONALIZED WARRIOR HEALTH AVATAR".$150K
Jul 6, 2016Department of DefenseOFFICE OF NAVAL RESEARCHN0001416P3034541712IGF::CT::IGF SBIRSOL2016.1$80K
Jul 5, 2016Department of DefenseW6QK ACC-APGW911SR16C0024541712IGF::OT::IGF PHASE I SBIR EFFORT$100K
Jul 5, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16WA64P541511IGF::OT::IGF ANNUAL RENEWAL OF SOFTWARE CFD-ACE$116K
Jun 29, 2016Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZLFA865016M2698541711IGF::OT::IGF PROBABILISTIC FLUID SYSTEM SOFTWARE FOR TACTICAL AIRCRAFT$150K
Jun 16, 2016Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7517541712IGF::OT::IGF SBIR PHASE I RESEARCH AND DEVELOPMENT$40K
Jun 13, 2016Department of DefenseW6QK ACC-APG DURHAMW911NF16C0081541712IGF::OT::IGF FIRST MONTHLY TECHNICAL REPORT$500K
May 31, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CG55P541712IGF::OT::IGF FUTURE NASA SCIENCE AND EXPLORATION MISSIONS REQUIRE SIGNIFICANT PERFORMANCE IMPROVEMENTS OVER THE STATE-OF-THE-ART IN POWER MANAGEMENT AND DISTRIBUTION (PMAD) SYSTEMS. SPACE QUALIFIED, HIGH VOLTAGE POWER ELECTRONICS CAN LEAD TO HIGHER EFFICIENCY AND REDUCED MASS AT THE SYSTEM ARCHITECTURE LEVEL, AND SERVE AS AN ENABLING TECHNOLOGY FOR OPERATIONAL CONCEPTS SUCH AS SOLAR ELECTRIC PROPULSION. SILICON CARBIDE (SIC) IS A ROBUST TECHNOLOGY WITH SUPERIOR ELECTRONIC PROPERTIES FOR POWER APPLICATIONS. SIC DEVICES OFFER HIGHER TEMPERATURE OPERATION, LOWER ON-RESISTANCE, HIGHER BREAKDOWN VOLTAGES, AND HIGHER POWER CONVERSION EFFICIENCY THAN SILICON POWER DEVICES. HOWEVER, HIGH VULNERABILITY TO HEAVY-ION INDUCED DEGRADATION AND CATASTROPHIC FAILURE HAS PRECLUDED THIS PROMISING TECHNOLOGY FROM SPACE PMAD APPLICATIONS. IMPORTANTLY, PHYSICAL MECHANISMS FOR THIS VULNERABILITY ARE NOT WELL UNDERSTOOD, RESULTING IN THE INABILITY TO DEVELOP RADIATION HARDENED SIC DEVICES. CFDRC, IN COLLABORATION WITH VANDERBILT UNIVERSITY AND WOLFSPEED, A CREE COMPANY, WILL UTILIZE A COUPLED EXPERIMENTAL AND PHYSICSBASED MODELING APPROACH TO ADDRESS THIS CHALLENGE. IN PHASE I, WE WILL PERFORM HEAVY ION TESTING OF COMMERCIAL WOLFSPEED SIC SCHOTTKY DIODE AND POWER MOSFET TO GENERATE RESPONSE DATA. DETAILED TCAD MODELS FOR THE DIODE WILL BE DEVELOPED, VALIDATED, AND APPLIED TO IDENTIFY PHYSICAL MECHANISMS BEHIND MEASURED RADIATION RESPONSE. IN PHASE II, WE WILL FOCUS ON SIC POWER MOSFETS AND PERFORM ADDITIONAL HEAVY ION AND TOTAL DOSE TESTING AS A FUNCTION OF TEMPERATURE AND BIAS. EXTENSIVE TCAD MODELING WILL BE PERFORMED TO IDENTIFY RADIATION AND TEMPERATURE DEPENDENT RESPONSE MECHANISMS, AND TO INVESTIGATE DEVICE STRUCTURE/PROCESS MODIFICATIONS FOR IMPROVED RADIATION HARDNESS. PROMISING SOLUTIONS WILL BE PROTOTYPED FOLLOWED BY ELECTRICAL/RADIATION CHARACTERIZATION. PARTICIPATION BY WOLFSPEED IN PHASE II AND BEYOND WILL ENSURE SUPERIOR SPACE-QUALIFIED, SIC POWER MOSFETS FOR NASA APPLICATIONS.$125K
May 25, 2016Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZLFA865016C5004541712IGF::OT::IGF SBIR II: INTEGRATED SOFTWARE TO PREDICT MATERIAL DEGRADATION IN SPECIAL TECHNOLOGY COATINGS$563K
May 25, 2016Department of DefenseFA8651 AFRL RWKFA865116C0171541712IGF::OT::IGF HIGH PERFORMANCE GELLED DACS$187K
May 24, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CM37P541712IGF::OT::IGF ADVANCED TURBOMACHINERY COMPONENTS PLAY A CRITICAL ROLE IN LAUNCH VEHICLE AND SPACECRAFT LIQUID ROCKET PROPULSION SYSTEMS. TO ACHIEVE DESIRED EFFICIENCIES, EXTREMELY TIGHT TOLERANCES ARE OFTEN IMPOSED BETWEEN INDUCER BLADES AND SHROUDS OR OTHER SYSTEM COMPONENTS WHICH SETS UP STRONG INTERACTIONS THAT INFLUENCE BOTH THE AERODYNAMICS AND THE STRUCTURAL PERFORMANCE OF BLADES AND VANES. THESE TRANSIENT INTERACTIONS, INCLUDING ROTOR-STATOR INTERACTIONS (RSI), CAN DEFORM THE BLADES AND SIGNIFICANTLY IMPACT THE VIBRATIONAL AND ACOUSTIC CHARACTERISTICS OF THE ENGINE, GREATLY REDUCE THE EFFICIENCY, AND EVEN LEAD TO BLADE OR VANE FAILURE. CURRENT PRODUCTION DESIGN TOOLS FOR TURBOMACHINERY DO NOT ACCOUNT FOR THE COUPLED FLUID-STRUCTURE INTERACTION (FSI) PHYSICS ASSOCIATED WITH THESE PHENOMENA. THIS STTR EFFORT WILL DEVELOP AND DELIVER A MULTIDISCIPLINARY DESIGN TOOL FOR ADVANCED TURBOMACHINERY COMPONENTS TO ACCOUNT FOR FSI PHENOMENA AND ENABLE MORE ACCURATE MODELING OF SYSTEMS AND SUBSCALE DEMONSTRATORS. CFDRC WILL SUPPLEMENT THE NASA MASSIVELY PARALLEL LOCI FRAMEWORK WITH HIGHLY ACCURATE AND EFFICIENT INTEGRATED FSI CAPABILITIES TO ENABLE BETTER UNDERSTANDING OF CRITICAL TURBOMACHINERY PROBLEMS IN LIQUID ROCKET PROPULSION SYSTEMS THAT DEFY CONVENTIONAL PREDICTIONS. LOCI WILL BE ENHANCED TO ENABLE CONSTRAINED DEFORMATIONS IN MOVING OVERSET GRID SYSTEMS TO SUPPORT PREDICTION OF STRUCTURAL RESPONSE AND FLUID-INDUCED VIBRATION IN ROTATING COMPONENTS. PHASE I WILL DEMONSTRATE IMPROVED MODELING FIDELITY AND PROVIDE GREAT INSIGHT INTO FSI PHENOMENA IN TURBOMACHINERY, AND PHASE II WILL BRING THE COMPLETE PREDICTIVE CAPABILITIES TO PRODUCTION FOR DETAILED INVESTIGATIONS INTO ADVANCED TURBOMACHINERY FOR LIQUID ROCKET PROPULSION SYSTEMS.$125K
May 24, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CM38P541712IGF::OT::IGF CHEMICAL CONTAMINATION OF SPACECRAFT COMPONENTS AS WELL AS THERMAL AND FORCE LOADING FROM FIRING LIQUID PROPELLANT THRUSTERS ARE CRITICAL CONCERNS FOR IN-SPACE PROPULSION APPLICATIONS. GAS MOLECULAR CONTAMINATION AND LIQUID DROPLET DEPOSITION DUE TO INCOMPLETE COMBUSTION THREATEN TO DAMAGE SURFACE MATERIALS, SENSITIVE INSTRUMENTS AND OPTICAL SENSORS, AND POSES MAJOR RISKS FOR MISSION SUCCESS. LIQUID PROPELLANT THRUSTERS OPERATE IN SPACE AT NEAR-VACUUM CONDITIONS, AND CONTAMINANTS TRAVERSE A COMPLEX MIXED CONTINUUM-RAREFIED ENVIRONMENT UPON EXITING THE THRUSTER NOZZLE. CURRENT CFD MODELING CAPABILITIES FOR IN-SPACE PROPULSION ANALYSIS HAVE MADE GREAT STRIDES, BUT FALL SHORT OF PROVIDING THE FIDELITY REQUIRED TO SIMULATE THE CONTAMINANT TRANSPORT AROUND THE SPACECRAFT WITH SUFFICIENT EFFICIENCY AND ACCURACY. THIS STTR WILL DEVELOP AND DELIVER AN INNOVATIVE COMPUTATIONAL ARCHITECTURE FOR PREDICTION OF PLUME FLOW IMPINGEMENT AND CONTAMINANT DISPERSAL THROUGH MIXED FLOW ENVIRONMENTS FOR IN-SPACE PROPULSION ANALYSIS. CFDRC WILL SUPPLEMENT THE MASSIVELY PARALLEL LOCI FRAMEWORK WITH A HIGHLY ACCURATE UNIFIED SOLVER FOR PREDICTION OF MIXED CONTINUUM-RAREFIED FLOWS WITH CONTAMINANT DISPERSAL. THIS WILL ENABLE BETTER UNDERSTANDING AND PREDICTION OF THERMAL AND FORCE LOADING AND CONTAMINATION OF SPACECRAFT COMPONENTS, AND ENABLE DESIGN OF A NEW ERA OF SAFER NEXT-GENERATION IN-SPACE PROPULSION SYSTEMS. PHASE I WILL DEMONSTRATE IMPROVED MODELING FIDELITY AND PROVIDE GREAT INSIGHT INTO IN-SPACE THRUSTER PLUME CONTAMINANT ENVIRONMENTS. PHASE II WILL BRING THE COMPLETE PREDICTIVE CAPABILITIES TO PRODUCTION FOR DETAILED INVESTIGATIONS INTO CONTAMINANT ENVIRONMENTS FOR FULL SPACECRAFT CONFIGURATIONS.$125K
May 19, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CC32P541712IGF::OT::IGF CONCERNS IN RECENT YEARS ABOUT THE TOXICITY AND SAFE HANDLING OF THE ?STORABLE? CLASS OF PROPELLANTS HAVE LED TO EFFORTS IN ?GREENER? MONOPROPELLANTS AND BI-PROPELLANTS. CFDRC HAS WORKED WITH RESEARCHERS IN DESIGNING AND SYNTHESIZING PROPELLANTS CALLED IONIC LIQUIDS. THESE ARE GENERALLY NOT AS HIGH-PERFORMING AS TRADITIONAL STORABLES AND STILL HAVE TOXICITY ISSUES. OTHER WORK BY CFDRC AND ARMY RESEARCHERS (AMONG OTHERS) HAS DEMONSTRATED THAT GELLING OF LIQUID PROPELLANTS, EVEN TOXIC HYPERGOLS, CAN ENHANCE THEIR INSENSITIVE MUNITIONS (IM) PROPERTIES TO A SIGNIFICANT DEGREE. BESIDES THE IM BENEFITS, GELLING OF THE FUEL ALLOWS THE SUSPENSION OF ULTRAFINE PARTICLES THAT BOTH DENSIFY THE PROPELLANT AND ADD TO THE COMBUSTION ENERGY, AND THEREBY THE SPECIFIC IMPULSE. CFDRC PROPOSES TO COMBINE THESE RESEARCH ELEMENTS INTO A COMPREHENSIVE ASSESSMENT IN PHASE I TO DETERMINE THE DEGREE TO WHICH THE GELATION OF INNOVATIVE PROPELLANT COMBINATIONS CAN ENHANCE THE SYSTEM BENEFITS, INCLUDING PERFORMANCE, SAFETY, AND LAUNCH COSTS. THEN IN PHASE II, THE DESIRED PROPELLANTS WILL BE OBTAINED OR SYNTHESIZED, AND THEN GELLED. A LIQUID APOGEE MOTOR-CLASS THRUSTER WILL BE FABRICATED AND THE GELLED PROPELLANTS WILL BE HOT-FIRED IN THE THRUSTER FOR EVALUATION. THE END PHASE II WILL FOCUS ON IDENTIFICATION OF OPPORTUNITIES TO TRANSITION AND INTEGRATE THIS TECHNOLOGY INTO NASA, DOD AND COMMERCIAL PRODUCT LINES, WITH SPECIAL EMPHASIS ON NASA SECONDARY PAYLOAD PROPULSION APPLICATIONS.$123K
May 12, 2016Department of Health and Human ServicesNATIONAL INSTITUTES OF HEALTH NIDAHHSN271201600009C541712IGF::OT::IGF SMARTPLATE TECHNOLOGY FOR ADVANCED CELLULAR MODELS (STAC-M)$225K
May 12, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CL21C541712IGF::OT::IGF INNOVATIVE LOW COST, LIGHT-WEIGHT AIRLOCK TECHNOLOGIES ARE REQUIRED TO INTEGRATE WITH DEEP SPACE AND SURFACE PLATFORM HOSTING EXTRA-VEHICULAR ACTIVITY. CFDRC TEAM PROPOSES AN INFLATABLE AIRLOCK STRUCTURE THAT EMPLOYS UNIQUE FABRIC ARCHITECTURE CAPABLE OF DELIVERING THE LOWEST MASS AND GREATEST VERSATILITY OF ANY COMPETING DESIGN. THE PROPOSED DESIGN FEATURES A COMPLETELY INTEGRATED AIR BEAM INTER-WALL TO PASSIVELY GENERATE THE WALL STIFFNESS REQUIRED FOR AIRLOCK DEPRESSURIZATION WITHOUT THE MASS AND BULK OF ALUMINUM PRESSURE HULLS OR COMPLEXITY OF MULTI-STRUCTURE ADAPTATIONS OF COMPETING INFLATABLE HABITAT ARCHITECTURES. THIS UNIQUE ARCHITECTURE UTILIZES A MATRIX OF BRAIDED FIBER TENDONS TO CONTAIN THE STRUCTURE S GLOBAL PRESSURE LOADS. THE UNDERLYING WOVEN FABRIC AND GAS BARRIER ENVELOPES ARE THEREBY ONLY EXPOSED TO MINIMAL LOCAL SHELL LOADS WHERE THEY BULGE OUTWARDS BETWEEN ADJACENT TENDONS. WORKING IN PURE TENSION IN THE ABSENCE OF LOAD COUPLING, THE TENDON ARRAY ARCHITECTURE HAS BEEN SHOWN TO BE STATICALLY DETERMINATE AND AUTO-STABILIZING UNDER EXTREME DEFLECTION. THE PROPOSED AIRLOCK STOWS COMPACTLY FOR TRANSPORT TO THE HABITAT FURTHER REDUCING LOGISTIC COSTS. PHASE I EFFORT FOCUSED ON CONCEPTUAL DESIGN OF THE AIRLOCK SYSTEM, IDENTIFICATION AND EVALUATION OF CANDIDATE MATERIALS, AND CHARACTERIZATION OF THE AIRLOCK SYSTEM. PHASE II EFFORT WILL FOCUS ON DESIGN REFINEMENT, INTEGRATED TESTING, ANALYSIS, AND INTEGRATION PLAN THAT WILL CULMINATE IN THE FABRICATION AND DEMONSTRATION OF A SUBSCALE PROTOTYPE INFLATABLE AIRLOCK STRUCTURE.$750K
May 6, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX14CA66P541712IGF::OT::IGF NASA IS INVESTIGATING THE DEVELOPMENT OF FLEXIBLE CARBON FABRICS FOR IMPLEMENTATION IN DEPLOYABLE AEROSHELLS USED IN ENTRY, DESCENT AND LANDING. THE CARBON FABRIC AND THE JOINTS BETWEEN FABRIC PANELS ON THE AEROSHELL NEED TO WITHSTAND THE HARSH AEROTHERMODYNAMIC AND STRUCTURAL LOADING ENVIRONMENTS IMPARTED BY HIGH SPEED ENTRIES INTO PLANETARY ATMOSPHERES. ONE OF THE KEY CHALLENGES FACING THE DEVELOPMENT OF DEPLOYABLE AEROSHELLS CONSTRUCTED FROM CARBON CLOTH IS THE JOINING OF GORE SECTIONS TO CLOSE-OUT THE AEROSHELL STRUCTURE AND TO INTERFACE WITH UNDERLYING RIGID STRUCTURAL ELEMENTS. IT IS ESSENTIAL THAT THE STITCHING USED TO JOIN GORE SECTIONS BE CAPABLE OF MAINTAINING INTEGRITY AT HIGH TEMPERATURE, WHICH SUGGESTS THAT CARBON FIBER THREADS WILL BE NEEDED. IT IS ALSO IMPORTANT THAT MULTILAYER FABRICS CAN BE STITCHED IN INCREMENTAL LAYERS, SO THAT FAILURE OF THE TOP LAYER DOES NOT COMPROMISE THE ENTIRE STACK. HOWEVER, STITCHING WITH CARBON THREAD IS CHALLENGING, AS THE HANDLING AND STRESS INVOLVED IN THE STITCHING PROCESS TENDS TO ADVERSELY AFFECT ITS STRUCTURAL PROPERTIES, LEADING TO LOW SEAM STRENGTH. CFD RESEARCH CORPORATION (CFDRC) AND THIN RED LINE AEROSPACE (TRLA), THROUGH NASA SBIR PHASE I, PHASE II, AND PHASE II ENHANCEMENT PROGRAMS (NNX11CA28C) HAVE BEEN SUPPORTING NASA FOR THE DEVELOPMENT AND TESTING OF A HIGHLY SCALABLE, MASS-OPTIMIZED UHPVBASED INFLATABLE STRUCTURE. CFDRC AND TRLA HAVE BEEN ALSO SUPPORTING NASA FOR APPLYING UNIQUE TECHNOLOGY FOR TPS STITCHING. THIS PROPOSAL IS AN EXTENSION OF THAT EFFORT. CFDRC AND TRLA ARE SENDING THIS PROPOSAL RESPONDING TO NASA S RELEASED STATEMENT OF WORK, DATED JUNE 25, 2014 FOR THE DEVELOPMENT OF CARBON FABRIC STITCHED SEAM.$30K
Apr 28, 2016Department of DefenseW6QK ACC-RSAW31P4Q15C0063541712IGF::OT::IGF ARMY SBIR PHASE II ENTITLED "LONGLIFE BATTERY FOR ELECTRONIC HEALTH MONITORING".$500K
Apr 27, 2016Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZLFA865015C2543541712IGF::OT::IGF A GENERAL SOLVER FRAMEWORK FOR RADIATIVE HEAT TRANSFER MODELS IN COMPUSTION SYSTEMS$187K
Apr 24, 2016Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7023541712IGF::OT::IGF SBIR/STTR PHASE I RESEARCH&DEVELOPMENT$100K
Apr 20, 2016Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7017541712::IGF::OT::IGF SBIR/STTR PHASE I RESEARCH&DEVELOPMENT$100K
Mar 16, 2016Department of DefenseW6QK ACC-RSAW31P4Q15C0063541712IGF::OT::IGF ARMY SBIR PHASE II ENTITLED "LONGLIFE BATTERY FOR ELECTRONIC HEALTH MONITORING".$82K
Jan 12, 2016Department of DefenseFA8651 AFRL RWKFA865116C0171541712IGF::OT::IGF HIGH PERFORMANCE GELLED DACS$563K
Dec 23, 2015Department of DefenseW6QK ACC-APG NATICKW911QY16P0049541712IGF::OT::IGF$100K
Dec 18, 2015Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7517541712IGF::OT::IGF SBIR PHASE I RESEARCH AND DEVELOPMENT$100K
Dec 11, 2015Department of DefenseW6QK ACC-RSAW31P4Q16C0012541712IGF::OT::IGF ARMY SBIR PH II ENTITLED "NOVEL CATHODES FOR HIGH CAPACITY THERMAL BATTERY".$500K
Dec 10, 2015Department of DefenseFA9101 AEDC PKP PROCRMNT BRFA910116C0001541712IGF::OT::IGF CFD RESEARCH CORP SBIR 2$375K
Nov 18, 2015Department of DefenseW6QK ACC-APG DURHAMW911NF16P0008541712IGF::OT::IGF SBIR PHASE I$100K
Oct 9, 2015Department of DefenseFA2487 AFTC PZZD (EGLIN)FA248716C0327541380IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH (SBIR II) - PHYSICS BASED FAST RUNNING TOOL$386K
Oct 9, 2015Department of DefenseFA2487 AFTC PZZD (EGLIN)FA248716C0327541380IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH (SBIR II) - PHYSICS BASED FAST RUNNING TOOL$1K
Oct 9, 2015Department of DefenseFA2487 AFTC PZZD (EGLIN)FA248716C0327541380IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH (SBIR II) - PHYSICS BASED FAST RUNNING TOOL$0
Oct 1, 2015National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX14CA66P541712IGF::OT::IGF NASA IS INVESTIGATING THE DEVELOPMENT OF FLEXIBLE CARBON FABRICS FOR IMPLEMENTATION IN DEPLOYABLE AEROSHELLS USED IN ENTRY, DESCENT AND LANDING. THE CARBON FABRIC AND THE JOINTS BETWEEN FABRIC PANELS ON THE AEROSHELL NEED TO WITHSTAND THE HARSH AEROTHERMODYNAMIC AND STRUCTURAL LOADING ENVIRONMENTS IMPARTED BY HIGH SPEED ENTRIES INTO PLANETARY ATMOSPHERES. ONE OF THE KEY CHALLENGES FACING THE DEVELOPMENT OF DEPLOYABLE AEROSHELLS CONSTRUCTED FROM CARBON CLOTH IS THE JOINING OF GORE SECTIONS TO CLOSE-OUT THE AEROSHELL STRUCTURE AND TO INTERFACE WITH UNDERLYING RIGID STRUCTURAL ELEMENTS. IT IS ESSENTIAL THAT THE STITCHING USED TO JOIN GORE SECTIONS BE CAPABLE OF MAINTAINING INTEGRITY AT HIGH TEMPERATURE, WHICH SUGGESTS THAT CARBON FIBER THREADS WILL BE NEEDED. IT IS ALSO IMPORTANT THAT MULTILAYER FABRICS CAN BE STITCHED IN INCREMENTAL LAYERS, SO THAT FAILURE OF THE TOP LAYER DOES NOT COMPROMISE THE ENTIRE STACK. HOWEVER, STITCHING WITH CARBON THREAD IS CHALLENGING, AS THE HANDLING AND STRESS INVOLVED IN THE STITCHING PROCESS TENDS TO ADVERSELY AFFECT ITS STRUCTURAL PROPERTIES, LEADING TO LOW SEAM STRENGTH. CFD RESEARCH CORPORATION (CFDRC) AND THIN RED LINE AEROSPACE (TRLA), THROUGH NASA SBIR PHASE I, PHASE II, AND PHASE II ENHANCEMENT PROGRAMS (NNX11CA28C) HAVE BEEN SUPPORTING NASA FOR THE DEVELOPMENT AND TESTING OF A HIGHLY SCALABLE, MASS-OPTIMIZED UHPVBASED INFLATABLE STRUCTURE. CFDRC AND TRLA HAVE BEEN ALSO SUPPORTING NASA FOR APPLYING UNIQUE TECHNOLOGY FOR TPS STITCHING. THIS PROPOSAL IS AN EXTENSION OF THAT EFFORT. CFDRC AND TRLA ARE SENDING THIS PROPOSAL RESPONDING TO NASA S RELEASED STATEMENT OF WORK, DATED JUNE 25, 2014 FOR THE DEVELOPMENT OF CARBON FABRIC STITCHED SEAM.$30K

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