Stennis Space Center Awarded Contracts - Systems Engineering | Federal Compass

Stennis Space Center Awarded Contracts - Systems Engineering

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80SSC019D0029 - RESEARCH AND DEVELOPMENT SERVICES FROM THE MISSISSIPPI RESEARCH CONSORTIUM. SECTION 1 INTRODUCTION: THE CONTRACTOR SHALL PROVIDE ENGINEERING AND SCIENTIFIC RESEARCH TO NASA AND THE TENANTS AT THE JOHN C. STENNIS SPACE CENTER (SSC) IN THE AREAS OFROCKET ENGINE AND PROPULSION SYSTEM TESTING, UNMANNED SYSTEMS, AUTONOMOUS SYSTEMS, MACHINE LEARNING, COMPUTATIONAL MODELING AND SIMULATION, COMPONENT ENGINEERING, CYBERSECURITY, ADVANCED MANUFACTURING, MATERIALS SCIENCE, ADVANCED SENSORS AND INSTRUMENTATION, MODEL-BASED SYSTEMS, ENGINEERING, PROCESS OPTIMIZATION, ACOUSTICS, MAGNETO HYDRODYNAMICS, AND ASSOCIATED SCIENTIFIC, COMPUTATIONAL AND ENGINEERING. EXAMPLES OF THE ANTICIPATED RESEARCH IN THESE AREAS ARE DESCRIBED IN SECTION 5 BELOW. THE MISSISSIPPI RESEARCH CONSORTIUM (MRC) IS A COLLABORATION OF FOUR MISSISSIPPI UNIVERSITIES DEDICATED TO PROVIDING RESEARCH AND TECHNOLOGY DEVELOPMENT TO VARIOUS STATE AND FEDERAL AGENCIES. THE MRC CONSISTS OF JACKSON STATE UNIVERSITY (JSU), MISSISSIPPI STATE UNIVERSITY (MSU), UNIVERSITY OF SOUTHERN MISSISSIPPI (USM) AND UNIVERSITY OF MISSISSIPPI (UM). SECTION 2 ADMINISTERING INSTITUTION: THE CONTRACT WILL BE ADMINISTERED BY A SINGLE MRC INSTITUTION THAT WILL SERVE AS THE MRC LIAISON TO NASA IN THE PERFORMANCE OF THIS CONTRACT. THE ADMINISTERING INSTITUTION WILL BE RESPONSIBLE FOR: A. RECEIVING STATEMENTS OF WORK FROM THE NASA OFFICE OF PROCUREMENT. B. DISTRIBUTE THE SOW WITHIN THREE WORK DAYS TO EACH MRC INSTITUTION OFFICE OF SPONSORED RESEARCH WITH INSTRUCTIONS ON THE PROCEDURE AND REQUIRED SCHEDULE FOR SUBMITTING PROPOSALS. C. COLLECTING AND REVIEWING THE PROPOSALS TO VERIFY THE TECHNICAL REQUIREMENTS ARE MET, INCLUDING BUDGET AND SCHEDULE. D. PROVIDING ALL SUBMITTED PROPOSALS TO NASA, ALONG WITH MRC RECOMMENDATION OF THE PROPOSAL THAT BEST MEETS THE REQUIREMENTS OF THE INDIVIDUAL SOW AND PROVIDES BEST VALUE TO THE GOVERNMENT. E. PROVIDE THE TOTAL COST OF THE PROPOSAL TO GOVERNMENT. F. ENTERING INTO A CONTRACT WITH THE MRC INSTITUTION SELECTED BY NASA WHEN A FIXED COST RESEARCH PROPOSAL IS FUNDED BY NASA G. PERFORMING GENERAL OVERSIGHT AND ADMINISTRATIVE FUNCTIONS. H. PROVIDING MONTHLY INVOICES. 1. PROVIDING STATUS REPORTS ON PROJECT SCHEDULES TO THE MRC INSTITUTIONS, THE NASA CONTRACTING OFFICER (CO) AND THE NASA CONTRACTING OFFICER REPRESENTATIVES (COR) J. REQUIRE EACH PRINCIPAL INVESTIGATOR (PI) TO PROVIDE A TECHNICAL REPORT AT THE CONCLUSION OF THE RESEARCH BEFORE FINAL PAYMENT IS MADE TO THE PI OR THE PI INSTITUTION K. PROVIDE NASA CO AND COR ONE COPY OF ALL FINAL REPORTS WITHIN 90 DAYS OF THE COMPLETION OF EACH PROJECT. 1. INCLUDE THE FINAL REPORT IN THE SSC'S TECHNICAL DOCUMENTATION SYSTEM PRIOR TO CLOSEOUT OF A PROJECT. M. CLOSE OUT ALL PROJECTS WITHIN 90 DAYS OF COMPLETION OF EACH PROJECT. THE ADMINISTERING INSTITUTION WILL PROVIDE A MANAGEMENT PLAN DESCRIBING THE STATISTICS TO BE COLLECTED AND PERIODICALLY REPORTED. NASA WILL SELECT THE ADMINISTERING INSTITUTION BASED ON AN EVALUATION OF "PROPOSALS FOR ADMINISTRATION" WHICH MAY BE SUBMITTED BY ANY MRC INSTITUTION. THE PROPOSAL FOR ADMINISTRATION MUST INCLUDE A DETAILED MANAGEMENT PLAN THAT DESCRIBES THE PROCESS FLOW THAT WOULD BE USED FOR OPERATION OF THE MRC. THE MANAGEMENT PLAN NARRATIVE IS LIMITED TO 10 PAGES AND THE ENTIRE PROPOSAL INCLUDING PRICING AND PERSONNEL QUALIFICATIONS IS LIMITED TO A TOTAL OF 20 PAGES INCLUDING ATTACHMENTS.
IDC - 541715 Research and Development in the Physical, Engineering, and Life Sciences
Contractor
UNIVERSITY OF SOUTHERN MISSISSIPPI (UNIVERSITY OF SOUTHERN MISSISSIPPI, THE)
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
11/30/2018
Obligated Amount
$5.6M
NNS17AA19B - ISHM (INTEGRATED SYSTEM HEALTH MANAGEMENT) AND AUTONOMY CAPABILITIES OF THE NASA NPAS (NASA PLATFORM FOR AUTONOMOUS SYSTEMS)WILL BE USED TO DEVELOP AUTONOMOUS SYSTEMS AND OPERATION OF NASA GROUND AND SPACE SYSTEMS, INCLUDING GROUND HIGH PRESSURE GAS FACILITY, CRYOGENIC FACILITIES, ORION CAPSULE SYSTEMS, SPACE HABITATS, ETC. WORK WILL BE DONE AT VARIOUS NASA SITES.
IDC - 541330 Engineering Services
Contractor
General Atomics (GENERAL ATOMICS)
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
04/26/2017
Obligated Amount
$119k
NNS16AA67A - IN 2008, STENNIS CONTRACTED IRISNDT INC. WHICH AT THAT TIME WAS CALLED MATRIX INSPECTION AND ENGINEERING NOW IRISNDT INC. TO PERFORM GUIDED WAVE ULTRASOUND INSPECTION (GUL) OF PIPES IN VALVE PITS. THE PIPE PENETRATED THE CEMENT WALL AND STENNIS SPACE CENTER WAS INTERESTED IN DETERMINING THE INTEGRITY OF THE CONCRETE TO PIPE INTERFACE. TO DO THIS, IRISNDT TESTED A SAMPLE PIPE WITH KNOWN DEFECTS AT THE SPACE CENTER TO DEMONSTRATE THE CAPABILITIES OF THE GUL TECHNIQUE TO REMOTELY DETECT, LOCATE, AND CLASSIFY THE RELATIVE SEVERITY OF KNOWN DEFECTS ON THAT MOCK UP SAMPLE THAT WAS PROVIDED BY STENNIS SPACE CENTER (SSC). THE TRIAL WAS SUCCESSFUL IN DETECTING AND ASSESSING THE RELATIVE SEVERITY OF THE KNOWN INDICATIONS. THE WORK THEN WAS CARRIED OUT ON PIPING IN VALVE PITS SUCCESSFULLY GUIDED WAVE ULTRASOUND GUL WAS DEVELOPED IN THE 1990S AND HAS TAKEN OFF AS A VIABLE SCREENING TOOL FOR THE INSPECTION OF LONG LENGTH OF PIPE. A RING OF PIEZOELECTRIC PROBES IS ATTACHED TO THE PIPE. THE RING GENERATES A TORSIONAL WAVE THAT WILL PROPAGATE IN THE PIPE. SYMMETRICAL FEATURES SUCH AS WELDS WILL PRODUCE SYMMETRICAL REFLECTORS. ASYMMETRICAL FEATURES SUCH AS CORROSION; NOZZLE, DRAIN, VENT, ETC. WILL PRODUCE REFLECTORS, BUT WILL ALSO GENERATE A MODE CONVERTED FLEXURAL WAVE. THE RING WILL DETECT ALL THE RETURNED SIGNALS AND DISPLAY THEM IN AN A SCAN AND C SCAN PRESENTATION. THIS TECHNOLOGY HAS BEEN EFFECTIVE IN DETECTING CUI CORROSION UNDER INSULATION WITH MINIMUM DISTURBANCE TO THE INSULATION. GUL ALSO PROVED EFFECTIVE IN CONTACT POINT CORROSION AT PIPE SUPPORTS ROAD CROSSINGS, BURIED PIPE AND CASED PIPE. NUMEROUS TESTS HAVE BEEN PERFORMED AND TECHNOLOGY HAS EVOLVED TO CONFIDENTLY CLASSIFY WALL LOSS DUE TO CORROSION OR EROSION IN THREE DIFFERENT CATEGORIES CAT 1 SEVERE GREATER THAN 50 PERCENT WALL LOSS CAT 2 MEDIUM WALL LOSS BETWEEN 25 PERCENT AND 50 PERCENT AND CAT 3 MINOR LESS THAN 25 PERCENT. FIGURES 2 3 4 AND 5 SHOW A COMPLETE SET OF GUL SYSTEM. THE SET INCLUDES RING, STEM AND A TOUGH BOOK. FIGURE 6 SHOW A GUL DATA SHEET THAT IS USED FOR ANALYSIS.
Cooperative Agreement
Contractor
IRISNDT INC.
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
08/11/2016
Obligated Amount
$39.7k
NNS16AA20B - THE WORK TO BE PERFORMED UNDER CONTRACT SHALL CONSIST OF FURNISHING ALL LABOR, EQUIPMENT, MATERIALS, AND SUPPLIES NECESSARY TO 1 PROVIDE MANAGEMENT OF THE TASKS OF THIS LOUISIANA BOARD OF REGENTS CONTRACT, AND 2 SUCH REQUIREMENTS THAT MAY BE SUBSEQUENTLY SET FORTH ON RESEARCH AND DEVELOPMENT TASK ORDERS. THE CONTRACTOR SHALL PROVIDE ENGINEERING AND SCIENTIFIC RESEARCH TO NASA AT THE JOHN C. STENNIS SPACE CENTER SSC OTHER NASA CENTERS, THE TENANT AGENCIES AT STENNIS SPACE CENTER, AND OTHER GOVERNMENT AGENCIES IN AREAS SUCH AS ACOUSTICS, IMAGE ANALYSIS, GEOGRAPHIC INFORMATION SYSTEMS, COMPUTATIONAL FLUID DYNAMICS, POLYMERS AND CERAMICS, ELECTRON MICROSCOPY, MICROELECTRONICS, MICRO ELECTRO MECHANICAL SYSTEMS MEMS, MAGNETO HYDRODYNAMICS, DIAGNOSTIC INSTRUMENTATION, ADVANCED SIGNAL PROCESSING, EMERGING TECHNOLOGIES IN COMMUNICATIONS, COMPUTATIONAL SCIENCES AND COMPUTER ARCHITECTURE, KNOWLEDGE SYSTEMS, FINITE ELEMENT ANALYSIS INCLUDING THERMAL STRESSES, FLUID SOLID INTERACTIONS, ADVANCED PROCESS CONTROL THEORY, WORKFORCE DEVELOPMENT, STEM EDUCATION, AND OTHER COMPUTATIONAL, SCIENTIFIC, AND ENGINEERING AREAS ASSOCIATED WITH THE TECHNICAL AND EDUCATIONAL MISSIONS OF NASA AND THE AGENCIES ELIGIBLE TO ENGAGE IN THIS CONTRACT MECHANISM. THE CONTRACT WILL BE ADMINISTERED BY THE LOUISIANA BOARD OF REGENTS LABOR WHICH WILL SERVE AS THE LIAISON TO NASA IN THE PERFORMANCE OF THIS CONTRACT. THE LABOR WILL BE RESPONSIBLE FOR RECEIVING STATEMENTS OF WORK SOW FROM THE NASA SSC OFFICE OF PROCUREMENT. TIMELY DISTRIBUTION OF THE SOW TO LABOR INSTITUTIONS OFFICES OF SPONSORED RESEARCH WITH INSTRUCTIONS ON THE PROCEDURE AND REQUIRED SCHEDULE FOR SUBMITTING PROPOSALS. PROVIDING DOCUMENTATION TO STENNIS SPACE CENTER SUPPORTING SOW DISTRIBUTION TO ALL LABOR INSTITUTIONS OFFICES OF SPONSORED RESEARCH. DOCUMENTATION SUPPORTING A NEGATIVE RESPONSE FROM NONPARTICIPATING LABOR INSTITUTIONS IS REQUIRED. PROVIDING ALL SUBMITTED PROPOSALS TO STENNIS SPACE CENTER IN A TIMELY MANNER FOR STENNIS SPACE CENTER TECHNICAL MONITOR REVIEW. PROVIDING ADMINISTRATIVE OVERSIGHT TO THE LABOR INSTITUTION SELECTED BY NASA STENNIS SPACE CENTER TO CONDUCT RESEARCH UNDER EACH TASK ORDER. PERFORMING GENERAL OVERSIGHT AND ADMINISTRATIVE FUNCTIONS. PROVIDING MONTHLY INVOICES TO STENNIS SPACE CENTER. ENSURING ACCOUNTABILITY AND NETWORKING AMONG LABOR INSTITUTIONS. PROVIDING STATUS REPORTS ON SCHEDULE AND COST. PROVIDE ANNUAL REPORTS ON THE ACTIVITIES ON THE LABOR AT STENNIS SPACE CENTER. PROVIDE A FINAL REPORT AND PROJECT CLOSE OUT. LISTED BELOW ARE THE CRITERIA THAT WILL BE USED TO EVALUATE THE LABOR PROPOSAL TO ADMINISTER THE CONTRACT IN LOUISIANA BACKGROUND ON THE LABOR WITH A SUMMARY OF RELEVANT CAPABILITIES OF ITS MEMBER INSTITUTIONS. MANAGEMENT PLAN FOR THE ADMINISTRATION OF THIS CONTRACT. COSTS OF CONTRACT ADMINISTRATION. PAST PERFORMANCE OF LABOR ON SIMILAR CONTRACTS. QUALIFICATIONS OF MANAGEMENT PERSONNEL
IDC - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
LOUISIANA BOARD OF REGENTS
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
03/17/2016
Obligated Amount
$701.4k
NNS15AA91A - THE PRIMARY OBJECTIVE OF THIS PROJECT WILL BE THE DEVELOPMENT OF A LINE OF 15,000 PSI RATED VALVES WHICH WILL MEET NASAS UNIQUE NEEDS. THE TECHNICAL REQUIREMENTS INCLUDE 15,000 PSI RATED VALVE WITH 4X BURST PRESSURE DEMONSTRATED ON SHELL, A FULL PORT 8 BALL VALVE, THE PROTOTYPE VALVE ASSEMBLY SHALL FIT WITHIN AN EXISTING OBSOLETE VALVE FOOTPRINT, THE PROTOTYPE VALVE ASSEMBLY SHALL BE CAPABLE OF OPERATION (OPEN/CLOSE) UNDER FULL DIFFERENTIAL PRESSURE AND FLOW UNDER EMERGENCY SITUATIONS, ASSEMBLY SHALL BE LEAK-TIGHT (INCLUDING VALVE STEM SEALS) WHEN USED WITH GASEOUS HYDROGEN (CLASS VI LEAKAGE) PRECISION FLUID CONTROLS PLANS TO COLLABORATE WITH NASA PERSONNEL TO INCORPORATE DESIGN IMPROVEMENTS WHICH NASA HAS IMPLEMENTED IN SIMILAR HIGH PRESSURE VALVES CURRENTLY INSTALLED AT STENNIS SPACE CENTER. TECHNICAL ISSUES INCLUDE LEAK TIGHT PERFORMANCE (WITHIN CLASS VI LEAKAGE DEFINITION) AND MATERIALS SELECTION FOR USE IN HIGH PRESSURE SYSTEMS. CHALLENGES INCLUDE MANUFACTURING THE VALVE COMPONENTS AND TESTING OF THE FINAL ASSEMBLY SUCH AS PROOF. THE PROJECT WILL FOCUS ON AN 8, 15,000 PSI TOP ENTRY BALL VALVE DEVELOPMENT. THE NEW DESIGN WILL INCORPORATE ELEMENTS FROM THE EXISTING DESIGN AND WILL ADD DESIGN IMPROVEMENTS BASED ON THE ACTUAL USAGE AND MODIFICATIONS MADE BY STENNIS PERSONNEL DURING THE COURSE OF THE EXISTING VALVE'S OPERATION. PRECISION FLUID CONTROLS (PFC) WILL WORK WITH THE SPRING ENERGIZED SEAL MANUFACTURERS TO INTEGRATE NEW DESIGN IMPROVEMENTS WHICH HAVE DEVELOPED OVER THE LAST SEVERAL YEARS. DURING OUR DESIGN OF FLIGHT HARDWARE, PFC HAS ENCOUNTERED MANY APPLICATIONS WHICH REQUIRE THESE SPECIALTY SEALS AND HAVE WORKED IN CONCERT WITH THE SEAL MANUFACTURERS TO DEVELOP INNOVATIVE DESIGNS TO SOLVE INTRICATE SEALING REQUIREMENTS. PFC WILL INVESTIGATE THE USE OF ALTERNATE MATERIALS TO BE USED FOR SURFACES WITH HIGH FRICTION SUCH AS TOUGHMET AS WELL AS COATINGS. WE WILL ALSO DETERMINE IF ROLLING BEARING ELEMENTS MAY PLAY A ROLE IN THE FUTURE DESIGN. ANOTHER CONCEPT WE WILL EXPLORE IS USING A MECHANICALLY RETRACTABLE SEAT WHICH WE HAVE USED SUCCESSFULLY IN LARGER MAIN ENGINE VALVES FOR LAUNCH VEHICLES. THE BODY WILL BE 316 SST WITH AN A286 VALVE STEM AND BALL. THE CURRENT SEAT IS METAL AND WE WILL EXPLORE ADDITIONAL OPTIONS FOR SEAT MATERIAL. THE VALVE WILL INCORPORATE BELLEVILLE SPRINGS MADE FROM LNCONEL 718. THE MATERIAL FOR THE THRUST WASHER IS CURRENTLY TORIAN, ALTERNATIVE MATERIALS WILL BE ANALYZED. SEALS MADE FROM PCTFE WILL BE ANALYZED AND MAY BE SWITCHED TO A POLYAMIDE. PFC WILL PERFORM THE INITIAL FUNCTIONAL TESTING, ADDITIONAL TESTING WILL BE PERFORMED AT STENNIS SPACE CENTER.
Grant for Research
Contractor
PRECISION FLUID CONTROLS INC
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
09/30/2015
Obligated Amount
$250k
NNS15AA88A - MULTICAMERA HIGH DYNAMIC RANGE HIGH-SPEED VIDEO OF ROCKET ENGINE TESTS AND LAUNCHES.DURING THIS EFFORT WE PROPOSE TO BORESIGHT THREE TO FOUR GFE HIGH DEFINITION (HD) RGB (COLOR) CAMERAS. WITH THE ADVENT OF SENSORS WITH MORE INTRINSIC DYNAMIC RANGE, THIS ARRANGEMENT COULD PROVIDE HIGHER QUALITY AND LONGER IMAGE ACQUISITIONS, AS COMPARED TO THE STS-134 AND STS-135 IMAGERY, IN COLOR AND WITH FEWER CAMERAS. WE WILL DESIGN AND CONSTRUCT A CUSTOM CAMERA MOUNT AND DEVELOP A CUSTOM SOFTWARE WORKFLOW TO FUSE RAW BAYER ARRAY IMAGERY INTO COLOR HDR IMAGERY. WE WILL DEMONSTRATE THIS TECHNOLOGY IN A LABORATORY ENVIRONMENT USING A QUARTZ TUNGSTEN HALOGEN LAMP TO SIMULATE A BRIGHT ROCKET PLUME WITH A DARK BACKGROUND. THE TECHNOLOGY DEMONSTRATOR WILL USE ~125 HZ, 10 BIT VIDEO SAMPLING TO DEMONSTRATE THE WORKFLOW AND VIDEO PROCESSING TECHNIQUES. MULTICAMERA CAMERA SYNCHRONIZATION AND SOFTWARE BASED IMAGE STABILIZATION WILL BE EVALUATED. THE MULTICAMERA DATA STREAMS WILL BE TRANSMITTED AND STORED ON A WINDOWS OPERATING SYSTEM COMPUTER WITH SOLID STATE DRIVES. USING A 10 GIGE INTERFACE FROM THE CAMERA AND AN OPTICAL FIBER WE EXPECT TO BE ABLE TO PLACE THE STORAGE DEVICE IN A DESKTOP COMPUTER AT A DISTANCE OF 25 M OR GREATER FROM THE CAMERAS. MILESTONE 1: MULTICAMERA HDR IMAGING SYSTEM DESIGN AND CONSTRUCTION GFE EMERGENT HS-2000C CAMERAS WILL BE USED TO GENERATE THE INTRINSIC LOW DYNAMIC RANGE IMAGING IN THIS DESIGN. THIS CAMERA IS A 2048 X 1088 PIXEL CMOS ARRAY THAT HAS THE SOFTWARE AND ELECTRONICS INTERFACE TO SUPPORT AUTOMATION. AS PART OF THIS FIRST TASK I2R WILL REVIEW AND REFINE THE LONG RANGE IMAGING REQUIREMENTS. DESIGN PARAMETERS INCLUDING SCENE DYNAMIC RANGE, IMAGING FRAME RATE, DATA STORAGE, DISTANCE TO TARGET AND EXPECTED ENVIRONMENTAL OPERATING CONDITIONS SUCH AS ACCELERATION FORCES AND TEMPERATURE WILL BE EVALUATED AND DEFINED. ONCE THE IMAGING REQUIREMENTS ARE DEFINED THE HDR IMAGING SYSTEM WILL BE DESIGNED. MILESTONE 2: CAMERA INTEGRATION AND TESTING ALL ASPECTS REQUIRED TO INTEGRATE THE GFE EMERGENT HS-2000C CAMERAS INTO THE IMAGING PLATFORM WILL BE CONDUCTED DURING THIS TASK. CAMERA INTEGRATION WILL INCLUDE PROVIDING APPROPRIATE MECHANICAL AND ELECTRICAL INTERFACES TO OPERATE THE CAMERA, PROVIDING APPROPRIATE THERMAL COOLING, CHECKING ALL COMPUTER AND SOFTWARE INTERFACES, AND VERIFYING CAMERA FIELD OF VIEW AND EXPECTED GROUND SAMPLE DISTANCE. AS PART OF THIS TASK THE CAMERA WILL BE FUNCTIONALLY TESTED WITHIN THE IMAGING PLATFORM. ANY ISSUES THAT ARISE AS A RESULT WILL BE ADDRESSED. MILESTONE 3: CAMERA CALIBRATION AND SOFTWARE DEVELOPMENT DURING THIS TASK I2R WILL DEVELOP A COLOR HDR ALGORITHM SPECIFIC TO THE HARDWARE DESIGN AND EXPECTED IMAGING REQUIREMENTS. THE HDR ALGORITHM WILL BE AN EXTENSION TO THE ONE DEVELOPED IN A PREVIOUS NASA DUAL USE PROJECT. THE ALGORITHM WILL UTILIZE UP TO FOUR DIFFERENT CAMERA EXPOSURE SETTINGS. THE CODE WILL BE DEVELOPED USING MATLAB, A HIGHLY CAPABLE SCRIPTING LANGUAGE WITH EXTENSIVE LIBRARIES AND DEBUGGING TOOLS. SEVERAL MATLAB TOOLBOXES WILL LIKELY BE EMPLOYED. TO INCREASE THE USABILITY OF THE MATLAB SOFTWARE, A MATLAB EXECUTABLE WILL BE GENERATED. THIS WILL ENABLE NASA AND OTHER COMMERCIAL CUSTOMERS TO EXECUTE THE SOFTWARE ON COMPUTERS THAT DO NOT HAVE MATLAB LICENSES. AS PART OF THIS TASK I2R WILL PERFORM A RADIOMETRIC AND GEOMETRIC CALIBRATION OF THE EMERGENT HS-2000C HIGH SPEED VIDEO CAMERAS. THE RADIOMETRIC CALIBRATION WILL INCLUDE A STATIC AND DYNAMIC DARK FRAME ASSESSMENT, FLAT FIELDING, A DEMOSAICKING ASSESSMENT AND A WHITE BALANCE. CAMERA FOCUS WILL BE EVALUATED AND FRAME TO FRAME CO-REGISTRATION WILL BE ASSESSED. EXTENSIVE I2R MATLAB-BASED IMAGE DE-NOISING ALGORITHMS WILL BE TAILORED AND REFINED FOR THIS HDR APPLICATION TO IMPROVE IMAGE QUALITY. MILESTONE 4: TEST AND EVALUATION THE COLOR HDR IMAGING SYSTEM WILL BE TESTED AND EVALUATED IN A LABORATORY SETTING USING A BRIGHT SOURCE SURROUNDED BY DARK STRUCTURE/BACKGROUND. THE HDR IMAGING SYSTEM WILL BE PLACED
Cooperative Agreement
Contractor
INNOVATIVE IMAGING & RESEARCH CORP
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
09/23/2015
Obligated Amount
$32.5k
NNS15AA01C - SYNERGY-ACHIEVING CONSOLIDATED OPERATIONS AND MAINTENANCE (SACOM)
IDC - 561210 Facilities Support Services
Contractor
Syncom Space Services, LLC (SYNCOM SPACE SERVICES LLC)
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
07/02/2015
Obligated Amount
$1.5B
NNS14AA17B - THE CONTRACTOR SHALL PROVIDE ENGINEERING AND SCIENTIFIC RESEARCH TO NASA, OTHER GOVERNMENT AGENCIES AND VARIOUS TENANTS AT THE JOHN C. STENNIS SPACE CENTER. THE AREAS OF WORK INCLUDE ROCKET PROPULSION TESTING RESEARCH AND DEVELOPMENT, PROJECT FORMULATION, NEW BUSINESS DEVELOPMENT, REMOTE SENSING APPLICATIONS, ECOSYSTEM INTEGRATION AND ANALYSIS, COASTAL COMMUNITY RESILIENCY AND SUSTAINABLE DEVELOPMENT, WATER QUALITY, CLIMATE CHANGE AND VARIABILITY EFFECTS ON REGIONAL ECOSYSTEMS, ACOUSTICS, IMAGE ANALYSIS, GEOGRAPHIC INFORMATION SYSTEMS, COMPUTATIONAL FLUID DYNAMICS, POLYMERS/CERAMICS, ELECTRON MICROSCOPY, MICRO-ELECTROMECHANICAL SYSTEMS, MAGNETO HYDRODYNAMICS, DIAGNOSTICS INSTRUMENTATION, AND OTHER ASSOCIATED SCIENTIFIC, COMPUTATIONAL AND ENGINEERING AREAS. SPECIFIC EXAMPLES OF PAST RESEARCH IN SEVERAL OF THESE AREAS IS SHOWN IS SECTION 5 BELOW. THE MISSISSIPPI RESEARCH CONSORTIUM (MRC) IS A COLLABORATION OF FOUR MISSISSIPPI UNIVERSITIES DEDICATED TO PROVIDING RESEARCH AND TECHNOLOGY DEVELOPMENT TO VARIOUS STATE AND FEDERAL AGENCIES. THE MRC CONSISTS OF JACKSON STATE UNIVERSITY (JSU), MISSISSIPPI STATE UNIVERSITY (MSU), UNIVERSITY OF SOUTHERN MISSISSIPPI (USM) AND UNIVERSITY OF MISSISSIPPI (UM). SECTION 2 ADMINISTERING INSTITUTION: THE CONTRACT WILL BE ADMINISTERED BY A SINGLE MRC INSTITUTION THAT WILL SERVE AS THE MRC LIAISON TO NASA IN THE PERFORMANCE OF THIS CONTRACT. THE ADMINISTERING INSTITUTION WILL BE RESPONSIBLE FOR: A. RECEIVING STATEMENTS OF WORK FROM THE NASA OFFICE OF PROCUREMENT. B.DISTRIBUTE THE SOW WITHIN THREE WORK DAYS TO EACH MRC INSTITUTION OFFICE OF SPONSORED RESEARCH WITH INSTRUCTIONS ON THE PROCEDURE AND REQUIRED SCHEDULE FOR SUBMITTING PROPOSALS. C. COLLECTING AND REVIEWING THE PROPOSALS TO VERIFY THE TECHNICAL REQUIREMENTS ARE MET, INCLUDING BUDGET AND SCHEDULE. D.PROVIDING ALL SUBMITTED PROPOSALS TO NASA, ALONG WITH MRC RECOMMENDATION OF THE PROPOSAL THAT BEST MEETS THE REQUIREMENTS OF THE INDIVIDUAL SOW AND PROVIDES BEST VALUE TO THE GOVERNMENT.E.PROVIDE THE TOTAL COST OF THE PROPOSAL TO GOVERNMENT.F.ENTERING INTO A CONTRACT WITH THE MRC INSTITUTION SELECTED BY NASA WHEN A FIXED COST RESEARCH PROPOSAL IS FUNDED BY NASA. G.PERFORMING GENERAL OVERSIGHT AND ADMINISTRATIVE FUNCTIONS.H.PROVIDING MONTHLY INVOICES. I.PROVIDING STATUS REPORTS ON PROJECT SCHEDULES TO THE MRC INSTITUTIONS, THE NASA CONTRACTING OFFICER (CO) AND THE NASA CONTRACTING OFFICER REPRESENTATIVES (COR) J.REQUIRE EACH PRINCIPAL INVESTIGATOR (PI) TO PROVIDE A TECHNICAL REPORT AT THE CONCLUSION OF THE RESEARCH BEFORE FINAL PAYMENT IS MADE TO THE PI OR THE PI INSTITUTION K.PROVIDE NASA CO AND COR ONE COPY OF ALL FINAL REPORTS WITHIN 90 DAYS OF THE COMPLETION OF EACH PROJECT. L.INCLUDE THE FINAL REPORT IN THE SSC S TECHNICAL DOCUMENTATION SYSTEM PRIOR
IDC - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
UNIVERSITY OF SOUTHERN MISSISSIPPI
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
11/27/2013
Obligated Amount
$5.7M
NNS14AA12P - : 1.0 BACKGROUND: RESEARCHERS AT STENNIS SPACE CENTER ARE INVESTIGATING THE USE OF CRYOGENS AS AN ACOUSTIC SUPPRESSION FLUID IN ROCKET TEST ENVIRONMENTS IN LIEU OF TRADITIONAL FLUIDS. 2.0 SCOPE: PROVIDE COMBUSTOR NOZZLE, SCALE ASPIRATOR AND ACOUSTIC SUPPRESSION DATA PER THE ATTACHED SPECIFICATION (CRYOGENIC ACOUSTIC SUPPRESSION FABRICATION AND TESTING SPECIFICATION). DELIVERABLES: 1 EA. COMBUSTOR NOZZLE PER ATTACHED SPECIFICATION. COMBUSTION SIDE OF NOZZLE SHALL BE CLEANED TO LEVEL 400A PER NASA-RPT-STD-8070-001. 1 EA. SCALE ASPIRATOR PER ATTACHED SPECIFICATION. 1 PK. ACOUSTIC SUPPRESSION DATA PER ATTACHED SPECIFICATION. DELIVERY SCHEDULE SHALL BE AS FOLLOWS: 40 WEEKS ARO: ALL ITEMS LISTED ABOVE SHIP TO: STENNIS SPACE CENTER BUILDING 2204 SSC, MISSISSIPPI 39529 NASA POINT OF CONTACT NICHOLAS J. NUGENT SSC/NASA CODE EA32 BUILDING 3225, ROOM B-28 STENNIS SPACE CENTER, MISSISSIPPI 39529 PHONE: (228) 688-1282 EMAIL: NICHOLAS.J.NUGENT@NASA.GOV CRYOGENIC ACOUSTIC SUPPRESSION FABRICATION AND TESTING CRYOGENIC ACOUSTIC SUPPRESSION FABRICATION AND TESTING SPECIFICATION NOVEMBER 12, 2013 REVISION 1 REVISION NO. 1 1 OF 7 CRYOGENIC ACOUSTIC SUPPRESSION FABRICATION AND TESTING PROJECT TABLE OF CONTENTS GENERAL REQUIREMENTS APPENDICES APPENDIX A - NASA-RPT-STD-8070-0001 SURFACE CLEANLINESS STANDARD FOR FLUID SYSTEMS FOR ROCKET ENGINE TEST FACILITIES OF THE NASA ROCKET PROPULSION TEST PROGRAM -- END OF TABLE OF CONTENTS REVISION NO. 1 2 OF 7 CRYOGENIC ACOUSTIC SUPPRESSION FABRICATION AND TESTING GENERAL REQUIREMENTS 1.1 SUMMARY THE WORK TO BE PERFORMED UNDER THIS PROJECT CONSISTS OF THE DESIGN, FABRICATION, INSPECTION, CLEANING, TESTING, AND DELIVERY TO JOHN C. STENNIS SPACE CENTER, STENNIS, MISSISSIPPI A COMBUSTOR NOZZLE, SCALE ASPIRATOR AND EXPERIMENTAL ACOUSTIC TEST DATA. 1.2 REFERENCES NASA&SSC STANDARDS AND SPECIFICATIONS (SSC) NASA-RPT-STD-8070-0001 SURFACE CLEANLINESS STANDARD FOR FLUID SYSTEMS FOR ROCKET ENGINE TEST FACILITIES OF THE NASA ROCKET PROPULSION TEST PROGRAM 1.3 SUBMITTALS THE FOLLOWING SHALL BE SUBMITTED TO THE CONTRACTING OFFICE AND THE CONTRACTING OFFICERS REPRESENTATIVE (COR) IN SUFFICIENT DETAIL TO SHOW FULL COMPLIANCE WITH THE SPECIFICATION: DESIGN CALCULATIONS THE CONTRACTOR SHALL FURNISH DESIGN CALCULATIONS IN A FORMAT AGREED UPON BETWEEN THE COR AND THE CONTRACTOR. THESE ARE DUE NO LATER THAN ONE WEEK PRIOR TO DESIGN REVIEWS. FINAL DESIGN CALCULATIONS ARE DUE NO LATER THAN TWO WEEKS PRIOR TO CONTRACT CONCLUSION. DESIGN CALCULATIONS SHALL INCLUDE: COMBUSTOR NOZZLE DESIGN THERMAL AND STRUCTURAL ASPIRATOR DESIGN SCALING ASPIRATOR PLUMBING ACOUSTIC SUPPRESSION NOZZLE SIZING (MASS AND MOMENTUM) DRAWINGS FABRICATION DRAWINGS SHALL BE SUBMITTED OF ALL DESIGNED HARDWARE BY THE CONTRACTOR. IF DRAWINGS ARE MADE FROM SOLID MODELS, THE MODELS SHALL BE SUBMITTED AS WELL. DRAWINGS ARE DUE
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
Purdue University (PURDUE UNIVERSITY)
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
11/14/2013
Obligated Amount
$105k
NNX13CS02P - THE OBJECTIVE OF THIS PHASE I SBIR PROGRAM IS TO DEVELOP POLYMER DERIVED RARE EARTH SILICATE NANOCOMPOSITE ENVIRONMENTAL BARRIER COATINGS (EBC) FOR PROVIDING NEXT-GENERATION CORROSION RESISTANCE AND THERMAL INSULATION TO AEROJET'S NUCLEAR THERMAL PROPULSION (NTP) SYSTEMS. THE NTP ENVIRONMENTAL BARRIER COATINGS WILL BE DEVELOPED FROM NANOSONIC'S INNOVATE INORGANIC POLYMERIC NANOCOMPOSITE RESINS THAT CROSSLINK TO DIMENSIONALLY STABLE GELS UNDER AMBIENT CONDITIONS AND GRACEFULLY TRANSITION TO HIGH TEMPERATURE CORROSION AND THERMALLY INSULATIVE RESISTANT COATINGS AT ELEVATED TEMPERATURES. THROUGH A SYNERGISM OF NANOPARTICLE RARE EARTH SILICATE LOAD TRANSFER PATHWAYS, NANOSONIC'S PROPOSED EBC TOPCOAT TECHNOLOGY WILL READILY ABSORB AND DISSIPATE HIGH VELOCITY IMPACT THREATS WHILE PROVIDING EXCEPTIONAL THERMAL SHOCK RESISTANCE NECESSARY FOR ENHANCED SURVIVABILITY OF NICKEL-CHROMIUM BASED ALLOYS WITHIN CURRENT AND FUTURE NTP ROCKET ENGINE ROCKET THRUST CHAMBERS AND NOZZLES. WORKING WITH TEAM MEMBERS AEROJET AND THE UNIVERSITY OF WASHINGTON, NANOSONIC WILL MOLECULARLY ENGINEER A FAMILY OF RARE EARTH SILICATE POLYMERIC PRECURSORS THAT ARE SPECIFICALLY OPTIMIZED FOR ROCKET ENGINES WITHIN AEROJET'S NTP SPACE TECHNOLOGY PROGRAM. FOR THE PROPOSED EFFORT, NANOSONIC, THE UNIVERSITY OF WASHINGTON AND AEROJET HAVE CREATED AN SBIR RESEARCH TEAM TO RAPIDLY IDENTIFY, OPTIMIZE AND TRANSITION NEXT-GENERATION POLYMER DERIVED RARE EARTH SILICATE COATINGS SPECIFICALLY OPTIMIZED TO EXTEND THE OPERATIONAL UTILITY OF NTP ROCKET THRUST CHAMBERS AND NOZZLES. WITHIN THIS TEAMING PARTNERSHIP, NANOSONIC WILL CONTINUOUSLY SYNTHESIZE AND OPTIMIZE RARE EARTH POLYMERIC PRECURSOR COATINGS WHEREAS THE UNIVERSITY OF WASHINGTON WILL TEST COATED NICKELCHROMIUM BASED ALLOYS WITHIN FLOW CONDITIONS SIMULATING NTP ROCKET EXHAUST. ANSYS THERMAL MODELING WILL BE EMPLOYED TO INTERPRET AND JOINTLY OPTIMIZE PROMISING RARE EARTH SILICATE COATINGS WITH AEROJET.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
NanoSonic Inc (NANOSONIC INC.)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
05/17/2013
Obligated Amount
$125k
NNX13CS03P - THE DEVELOPMENT OF ROCKET-BASED AND TURBINE-BASED COMBINED CYCLE ENGINES ARE A HIGH PRIORITY FOR TRANSPORTATION INTO SPACE. IN ORDER TO TEST COMPONENTS AND SYSTEMS, AND CERTIFY LIFE CYCLES FOR THESE ENGINES, NON-INTRUSIVE FLOW DIAGNOSTICS ARE REQUIRED. IN PARTICULAR, HIGH-SPEED MEASUREMENTS OF PRESSURE, VELOCITY, AND TEMPERATURE PROFILES ACROSS BOTH INLET AND OUTLET DUCTS OF THESE ENGINES WOULD PROVIDE A BETTER UNDERSTANDING OF ENGINE PERFORMANCE. SOUTHWEST SCIENCES, INC. PROPOSES TO DEVELOP A HIGH-SPEED, NON-INTRUSIVE MONITOR TO MEASURE SUCH FLOWS. THIS FIBER OPTIC SENSOR IS BASED ON A NOVEL APPROACH DERIVED FROM WAVELENGTH MODULATION SPECTROSCOPY, IN WHICH HIGH BANDWIDTH MEASUREMENTS CAN BE ACQUIRED AND PROCESSED WITH SIMPLE ELECTRONICS. PHASE I WILL FOCUS ON VALIDATING THE PROPOSED TECHNIQUE AND IN PHASE II, A FULLY OPERATIONAL PROTOTYPE WILL BE CONSTRUCTED, TESTED AND DELIVERED TO NASA.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
SOUTHWEST SCIENCES INC (SOUTHWEST SCIENCES, INC.)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
05/16/2013
Obligated Amount
$125k
NNX13CS01P - SIERRA LOBO SHALL CONDUCT TESTING OF THE HELIUM RECOVERY SYSTEM AT THE SIERRA LOBO TECHNOLOGY DEVELOPMENT AND ENGINEERING CENTER IN MILAN, OHIO. TESTING SHALL INCLUDE SAMPLING OF THE PRODUCT STREAM TO DETERMINE HELIUM PURITY THROUGH THIRD-PARTY ANALYSIS OF THE SAMPLE.SIERRA LOBO SHALL DEVELOP A MODIFICATION TO THE HELIUM RECOVERY SYSTEM SOFTWARE TO PROVIDE A NEW CAPABILITY TO CALCULATE THE HYDROGEN CONTENT OF THE INCOMING HYDROGEN/HELIUM FLOW BASED ON SYSTEM MEASUREMENTS.SIERRA LOBO SHALL TEST THE NEW CAPABILITY OF THE HELIUM RECOVERY SYSTEM TO CALCULATE THE HYDROGEN CONTENT OF THE INCOMING HYDROGEN/HELIUM FLOW MIXTURE.SIERRA LOBO SHALL DESIGN A NEW HELIUM RECOVERY SYSTEM LOW-PRESSURE VENT ACCESSORY FOR THE HELIUM RECOVERY SYSTEM. THE LOW-PRESSURE VENT ACCESSORY SHALL CONSIST OF A 30 PSID COMPRESSOR, RESERVOIR, AND MANIFOLD. THE LOW-PRESSURE VENT ACCESSORY PROVIDES THE CAPABILITY TO OPERATE THE HELIUM RECOVERY SYSTEM CONNECTED DIRECTLY TO A HYDROGEN VENT SYSTEM, ENABLING A NEW CONCEPT OF OPERATIONS FOR PURGING HYDROGEN VENT SYSTEMS WITH THE ABSOLUTE MINIMUM AMOUNT OF HELIUM.SIERRA LOBO SHALL PROVIDE IN ACCORDANCE WITH SIERRA LOBO ISO/AS9100/CMMI QUALITY PROCESSES, OVERALL ADMINISTRATIVE AND PROGRAM MANAGEMENT OF THE PROJECT AND SHALL INCLUDE CONTRACT ADMINISTRATION, FINANCIAL PLANNING, AND ACCOUNTING, PREPARATION AND UPDATE PROJECT SCHEDULES, UPDATE WORK PLANS, MAINTAIN QUALITY ASSURANCE, AND PREPARE CUSTOMER DELIVERABLES.SIERRA LOBO SHALL CONDUCT SYSTEMS ENGINEERING TASKS AS REQUIRED IN ACCORDANCE WITH SIERRA LOBO ISO/AS9100/CMMI QUALITY PROCESSES THAT MAY INCLUDE; REQUIREMENTS MANAGEMENT, DEVELOPMENT OF CONTROLLED DOCUMENTATION FOR DESIGN, FABRICATION, AND TEST, DEVELOPMENT OF HAZARDS ANALYSES, AND PREPARE FOR AND CONDUCT PRELIMINARY DESIGN REVIEWS, CRITICAL DESIGN REVIEWS, AND TEST READINESS REVIEWS.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
Sierra Lobo (SIERRA LOBO, INC.)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
04/05/2013
Obligated Amount
$75k
NNS12AB17A - PLANETARY AND EARTH IMAGINING REQUIRES RADIOMETRICALLY CALIBRATED AND STABLE IMAGING SENSORS. RADIOMETRIC CALIBRATION CORRECTS SENSOR ARTIFACTS, IS USED TO CONVERT A SENSOR S OUTPUT TO ENGINEERING UNITS AND IS CRITICAL TO VARIOUS NASA RESEARCH AND MONITORING TEST ARTICLES AND MULTIPLE SENSORS AT DIFFERENT TIMES AND GEOMETRIES. AT THE NASA STENNIS SPACE CENTER (SSC) IMAGING CAMERAS HAVE BEEN USED IN SITU TO MONITOR PROPULSION TEST STAND ACTIVITIES AND RADIOMETRIC CALIBRATION CAN HELP ANALYZE THE LIGHT PRODUCED BY A TEST ARTICLE DURING FIRING. THIS DATA CAN BE USED TO INFER TEMPERATURE AND COMPOSITION AND CAN BE USED TO DETECT DEFECTS OR IF PRUDENT STOP A TEST. SIMILARLY THERE ARE ALSO NEEDS TO RADIOMETRICALLY CALIBRATE MANY NON-NASA INSTRUMENTS USED BY INDUSTRY AND ACADEMIA. SENSOR RADIOMETRIC CALIBRATION AND STABILITY IS TYPICALLY ACCOMPLISHED BY INITIALLY CALIBRATING AN IMAGING SENSOR IN A LABORATORY BEFORE IT IS FIELDED OR INTEGRATED ONTO A SPACECRAFT AND LAUNCHED. NATIONAL INSTITUTE OF STANDARDS AND TECHNOLOGY (NIST) TRACEABLE INTEGRATING SPHERE BASED RADIOMETRIC CALIBRATION SOURCES HAVE BEEN THE LABORATORY WORK HORSE TECHNOLOGY FOR SEVERAL DECADES. AN INTEGRATING SPHERE SOURCE IS A SPHERICAL SHELL COATED WITH HIGHLY REFLECTING DIFFUSE MATERIAL THAT IS ILLUMINATED EITHER INTERNALLY OR EXTERNALLY. THESE SPHERES HAVE PORTS THAT ALLOW LIGHT TO ENTER OR EXIT. SOMETIMES THE INTEGRATING SPHERES SOURCE WILL HAVE A DETECTOR OR SPECTROMETER TO MONITOR ITS OUTPUT. WITH A FEW EXCEPTIONS VENDORS SELL DESIGNS AND TECHNOLOGY SIMILAR TO THOSE THAT WERE INTRODUCED INTO THE MARKET A DECADE OR MORE AGO EVEN THOUGH ADVANCES IN DIGITAL IMAGERS AND SPECTROSCOPIC SYSTEMS WOULD BENEFIT FROM SEVERAL IMPROVEMENTS THE PUSH FOR HIGHER SPATIAL RESOLUTION IMAGERY IS INCREASING THE REQUIRED PORT DIAMETER AND CONSEQUENTLY THE SIZE NEEDED FOR CALIBRATION SOURCES WHICH IS CAUSING SCALING ISSUES WITH TRADITIONAL DESIGNS. THE TYPES OF CALIBRATION SOURCE IMPROVEMENTS NEEDED INCLUDE: *LARGER EXIT PORT DIAMETERS TO FACILITATE THE CALIBRATION OF LARGE IMAGING SYSTEMS*PROGRAMMABLE OPERATION TO ALLOW INTEGRATED SENSOR-SPHERE CONTROL TO IMPROVE WORK FLOW*BETTER SHORT TERM STABILITY TO IMPROVE THE SIGNAL TO NOISE RATIO (SNR) OF MEASUREMENTS TO REDUCE THE NUMBER OF MEASUREMENTS REQUIRED AND ENABLE SENSOR TEMPORAL SNR MEASUREMENTS TO BE ACQUIRED.* IMPROVED LONG-TERM STABILITY TO MEASURE SENSOR DRIFT AND REDUCE CALIBRATION SOURCE MAINTENANCE*BETTER SPATIAL UNIFORMITY TO IMPROVE FLAT FIELDING AND REDUCE NUMBER OF MEASUREMENTS REQUIRED* INCREASED UV-VISIBLE OUTPUT THAT IS MORE CHARACTERISTIC OF NATURAL ILLUMINATION*VARIABLE ILLUMINATION OVER SEVERAL DECADES OF RADIANCE TO CALIBRATE SENSORS OVER THE LARGE DYNAMIC RANGE NOW AVAILABLE WITH MODERN SENSORS* REDUCED POWER DISSIPATION TO.
Cooperative Agreement
Contractor
INNOVATIVE IMAGING & RESEARCH CORP
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
08/23/2012
Obligated Amount
$75k
NNX12CB10C - OTHER FUNCTION - AN ORIFICE ELEMENT IS COMMONLY USED IN LIQUID ROCKET ENGINE TEST FACILITIES TO PROVIDE A LARGE REDUCTION IN PRESSURE OVER A VERY SMALL DISTANCE IN THE PIPING SYSTEM. ORIFICE ELEMENTS ARE USED IN PROPELLANT LINES, FEED SYSTEMS, PLUME SUPPRESSION SYSTEMS AND STEAM EJECTOR TRAINS. WHILE THE ORIFICE AS A DEVICE IS LARGELY EFFECTIVE IN STEPPING DOWN PRESSURE, IT IS ALSO SUSCEPTIBLE TO A WAKE-VORTEX TYPE INSTABILITY AND CAVITATION INSTABILITY THAT PROPAGATE DOWNSTREAM AND INTERACT WITH OTHER ELEMENTS OF THE TEST FACILITY RESULTING IN STRUCTURAL VIBRATION. IN THIS PROPOSAL A NEW PROPRIETARY INSTABILITY MITIGATION DEVICE HAS BEEN DEVELOPED THAT STEPS DOWN THE PRESSURE, STRAIGHTENS THE FLOW AND SUPPRESSES ALL INSTABILITY MODES. THE DEVICE IS SCALABLE AND CAN BE USED FOR DIFFERENT MASS FLOW RATES AND VARYING LEVELS OF DE-PRESSURIZATION CONDITIONS. IT IS RELATIVELY INEXPENSIVE TO MANUFACTURE, EASY TO FABRICATE AND INSTALL, AND CAN BE TAILORED TO MEET THE PERFORMANCE REQUIREMENTS OF A GIVEN FACILITY. IN PHASE I, THE DEVICE HAS BEEN SUCCESSFULLY DEMONSTRATED IN A SUB-SCALE CRYOGENIC TEST FACILITY. IN PHASE II THE PERFORMANCE OF THE DEVICE WILL BE CALIBRATED FOR FULL-SCALE OPERATION IN A CRYOGENIC TEST FACILITY AND A WATER TEST FACILITY.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
COMBUSTION RESEARCH AND FLOW TECHNOLOGY INC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
06/06/2012
Obligated Amount
$750k
NNX12CA85C - OTHER FUNCTION - THE INNOVATION AIMS TO DEVELOP THE TOOLS FOR MULTIPLE GEOBROWSERS TO COMMUNICATE OVER THE INTERNET TO CREATE A REAL COLLABORATIVE EXPERIENCE OVER COMPUTER DESKTOP VIRTUAL GLOBES WHEN DEALING WITH ANY TYPE OF GEOSPATIAL INFORMATION. THESE FUNCTIONS ARE ESPECIALLY IMPORTANT WHEN DEALING WITH DECISION MAKERS, WHO FREQUENTLY ARE NON-GIS EXPERTS THAT REQUIRE VISUALIZING THEIR OWN ASSETS ON A MAP, LIKE THEIR FIREFIGHTER ENGINE POSITIONS, COMBINED WITH EXTERNAL EXPERTISE AND OTHER RELEVANT DATASETS, LIKE NASA MODIS WILDFIRE HOTSPOTS, CREATING ACTIONABLE GEOSPATIAL INFORMATION TO MAKE BETTER INFORMED AND TIMELIER DECISIONS. THE ULTIMATE OBJECTIVE WOULD BE A FULLY INTEROPERABLE MULTI-PLATFORM COLLABORATIVE DECISION ENVIRONMENT THAT DELIVERS ACCURATE INFORMATION ON EMERGING SITUATIONS WHILE COLLABORATING WITH DISTRIBUTED PARTNERS, ADVISORS, SPECIALISTS AND AUTHORITIES IN VARIOUS JURISDICTIONS, REGARDLESS OF THE VIRTUAL GLOBE, HARDWARE OR OPERATING SYSTEMS USED.
Definitive Contract - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
STORMCENTER COMMUNICATIONS, INC.
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
04/27/2012
Obligated Amount
$893.4k
NNX12CG37P - AMERICAN GNC CORPORATION (AGNC) AND LOUISIANA TECH UNIVERSITY (LATECH) ARE PROPOSING A BREAKTHROUGH TECHNOLOGY CONSISTING OF AN INNOVATIVE SYSTEM FOR FACILITATING THE MONITORING AND MANAGEMENT OF NASA TEST FACILITIES (SUCH AS ROCKET ENGINE TEST STANDS) AND WIDELY DISTRIBUTED SUPPORT SYSTEMS (WDSS). THIS TECHNOLOGY, TERMED THE INTELLIGENT DISTRIBUTED AND UBIQUITOUS HEALTH MANAGEMENT SYSTEM (IDU-HMS) CONSISTS OF: (A) A FAULT AWARE WIRELESS SENSOR NETWORK (WSN) FOR MONITORING VALVES, VACUUM LINES, AND PRESSURIZED SUBSYSTEMS; (B) LOCAL WIRELESS DATA COLLECTION AND DIAGNOSTIC UNITS; (C) A MAIN WEB SERVICE BASED HEALTH AND DATA UNIT; AND (D) PORTABLE WEB CLIENTS. NEW AND POWERFUL ALGORITHMS BASED ON THE ARTIFICIAL INTELLIGENCE PARADIGM ARE LEVERAGED FOR CONDUCTING AUTOMATED ANOMALY DETECTION AND DIAGNOSTICS. ANOTHER KEY INNOVATION IS THE UBIQUITOUS INFORMATION CAPABILITY ENABLED BY MOBILE COMMUNICATION TECHNOLOGIES AS WELL AS SECURE INTERNET AND WIRELESS LOCAL AREA NETWORK (WLAN) CONNECTIONS. THE ARCHITECTURE IS BASED ON A STANDARDIZED FRAMEWORK FOR MAXIMUM MODULARITY SUCH THAT IT CAN BE INTEGRATED INTO CURRENT SUPPORT, CBM+ TYPE, AND CONTROL SYSTEMS AT NASA STENNIS SPACE CENTER (SSC).
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
AMERICAN GNC CORPORATION
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
02/13/2012
Obligated Amount
$125k
NNX12CF59P - THE DESIGN, DEVELOPMENT AND STAGING OF TESTS TO CERTIFY LIQUID ROCKET ENGINES USUALLY REQUIRE HIGH-FIDELITY STRUCTURAL, FLUID AND THERMAL SUPPORT ANALYSIS. THESE ANALYSES ARE CRUCIAL TO A SUCCESSFUL ENGINE TEST PROGRAM SINCE PRESSURIZATION REQUIREMENTS, HEAT LOADS, COOLING REQUIREMENTS AND STRUCTURAL STRESSES ARE EVALUATED. FURTHERMORE, THESE ANALYSES ARE UTILIZED TO DETECT ANOMALIES, UNSTEADY PRESSURE PULSATIONS, STRUCTURAL VIBRATIONS, RESONANT MODES AND UNEXPECTED PLUME IMPINGEMENT ZONES THAT MAY BE HAZARDOUS TO THE TEST STAND STRUCTURE AND/OR THE TEST ARTICLE. SUCH HIGH-FIDELITY ANALYSES HAVE TRADITIONALLY BEEN PERFORMED ON PC-CLUSTER TYPE COMPUTATIONAL PLATFORMS SPANNING OVER DAYS/WEEKS GIVEN THE COMPLEXITY OF THE FLOWPATH AND FLOW REGIMES TYPICALLY INVOLVED IN THE TESTING OF LIQUID ROCKET ENGINES. IN THIS PROPOSAL WE EXPLOIT THE DATA PARALLELISM OF THE COMPUTATIONAL ALGORITHMS INVOLVED TO SIGNIFICANTLY ENHANCE PERFORMANCE ON LOW-COST HIGH-SPEED GPU ENABLED HARDWARE. SUCH A TRANSITION TO GPU-BASED HARDWARE WILL RESULT IN A PARADIGM SHIFT FOR COMPUTE-INTENSIVE PROPULSION SYSTEM APPLICATIONS FROM EXPENSIVE CPU DOMINATED PC-CLUSTER ARCHITECTURES TO ECONOMICAL WORKSTATION STYLED HYBRID GPU-CPU SYSTEMS, WHILE RESULTING IN DRAMATIC DECREASES IN TURNAROUND TIMES.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
COMBUSTION RESEARCH AND FLOW TECHNOLOGY INC
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
02/10/2012
Obligated Amount
$125k
NNX12CG38P - NASA AND MANY OTHERS OFTEN RELY ON DELIVERY OF CRYOGENIC HYDROGEN TO MEET THEIR FACILITY NEEDS. NASA'S STENNIS SPACE CENTER IS ONE OF THE LARGEST USERS OF HYDROGEN, WITH THE LH2 USED AS A FUEL FOR CRYOGENIC ROCKET ENGINE TESTING. OTHER NASA CENTERS INCLUDING KENNEDY SPACE CENTER, WHICH UTILIZES HYDROGEN TO SUPPORT SPACE SHUTTLE LAUNCHES, AND MANY INDUSTRIAL LOCATIONS ALSO USE SIGNIFICANT AMOUNTS OF HYDROGEN. UNFORTUNATELY EXTREMELY LARGE AMOUNTS OF HYDROGEN ARE LOST DURING TRANSFERS AND TEST OPERATIONS DUE TO BOIL-OFF RESULTING FROM HEAT TRANSFERRED INTO THE EQUIPMENT, OR BY OTHER MEANS. ADDITIONALLY, THROUGH TEST OPERATIONS, HYDROGEN AND HELIUM BECOME MIXED AND REQUIRE SEPARATION TO REGAIN THEIR VALUE. THIS GASEOUS HYDROGEN IS TYPICALLY FLARED AS A SAFETY MEASURE WITH LITTLE TO NO ECONOMIC VALUE OR ENERGY EFFICIENCY REALIZED FROM THE PROCESS. NO ECONOMICAL MEANS EXISTS TO SAFELY CAPTURE, PROCESS AND STORE, AND SIMULTANEOUSLY EXTRACT VALUABLE ENERGY, THE LARGE AMOUNTS OF GASEOUS HYDROGEN RELEASED DURING NASA TEST OPERATIONS, OR IN INDUSTRIAL APPLICATIONS WHERE CRYOGENIC HYDROGEN IS USED. THE TECHNOLOGIES DEVELOPED TO CAPTURE AND CLEAN THE HYDROGEN MUST BE COST EFFECTIVE AND ABLE TO PERFORM THE RECYCLING PROCESS IN AN IN-SITU ROCKET ENGINE TEST AREA ENVIRONMENT, AND MUST COMPLY WITH ALL SAFETY AND QUALITY STANDARDS FOR THIS ENVIRONMENT. BECAUSE CRYOGENIC HYDROGEN IS VERY PURE, ITS RECYCLE AND RECOVERY AS A COMPRESSED GAS CAN RESULT IN A VALUABLE COMMODITY AND CAN PROVIDE THE BASIS OF A POWER GENERATION SYSTEM THAT CONSERVES FACILITY ENERGY. THIS STTR PROJECT DEVELOPS A HYDROGEN-BASED ENERGY CONSERVATION SYSTEM (HECS) THAT BRINGS IN GASEOUS HYDROGEN RELEASED FROM CRYOGENIC STORAGE OR TRANSFER OR MIXED HYDROGEN, HELIUM STREAM FROM TEST OPERATIONS, PURIFIES THE HYDROGEN AND ALTERNATELY ELECTROCHEMICALLY COMPRESSES IT TO COMMERCIAL STORAGE PRESSURES (UP TO 6,000 PSI) AND REUSES THE HYDROGEN IN A REACTION WITH AIR TO EFFICIENTLY PRODUCE ELECTRICITY.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
SKYRE, INC. (SUSTAINABLE INNOVATIONS)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
02/09/2012
Obligated Amount
$124.9k
NNS11AB03P - COMBUSTION RESEARCH&FLOW TECHNOLOGY, INC. (CRAFT TECH) SBIR PHASE III PROJECT STATEMENT OF WORK TITLE: SPEED UP OF THERMAL/HEAT TRANSFER ANALYSIS USING A GPU ENABLED COMPUTING ENVIRONMENT PURPOSE: TO AGGRESSIVELY SPEED-UP THE TIME FOR ANALYSES OF HEAT TRANSFER AND THERMAL EFFECTS THROUGH THE UTILIZATION OF GPU (GRAPHICAL PROCESSOR UNITS) ENABLED COMPUTING. INTRODUCTION: THE DESIGN AND ANALYSIS DIVISION AT NASA SSC IS RESPONSIBLE FOR CONDUCTING RELIABLE AND MEANINGFUL ENGINEERING SIMULATIONS IN SUPPORT OF POTENTIAL AND ACTIVE ROCKET TEST PROGRAMS. GENERAL ANALYSIS OR DATA PROCESSING TASKS HAVE BEEN CONDUCTED USING IN-HOUSE OR COMMERCIAL ENGINEERING SOFTWARE ON STANDARD WORKSTATIONS. WHEN THE NEED ARISES FOR HIGHER-FIDELITY MODELING, SUCH AS 3D TRANSIENT COMPUTATIONAL FLUID/THERMAL/STRUCTURAL ANALYSES, SUPERCOMPUTING FACILITIES ARE USED TO TAKE ADVANTAGE OF MULTIPROCESSING AND THEREBY ENABLE RAPID TURN-AROUND TIMES. HOWEVER, THESE INFRASTRUCTURES ARE LIMITED IN AVAILABILITY AND CAN BE IMPRACTICAL TO USE FOR DAY-TO-DAY DESIGN AND ANALYSIS TASKS. HOWEVER, WITH THE ADVENT OF GRAPHICAL PROCESSING UNIT (GPU) COMPUTING TECHNOLOGY, MODELING TASKS THAT WERE RESTRICTED TO HIGH-END COMPUTATIONAL FACILITIES ARE NOW TANGIBLE ON LOWER COST HIGH-END WORKSTATIONS. GPU COMPUTING HAS THE POTENTIAL OF REDUCING MODELING TIME BY ONE TO TWO ORDERS OF MAGNITUDE COMPARED TO CURRENT CPU WORKSTATIONS. FOR NASA SSC, ONE OF THE MOST POTENTIAL ADVANTAGES OF GPU COMPUTING IS PERHAPS THE OPPORTUNITY TO PERFORM REAL-TIME COMPUTING, VISUALIZATION OR DATA PROCESSING DURING ROCKET ENGINE TESTING THEREBY PROVIDING FEEDBACK DIRECTLY TO THE TEST OPERATIONS PERSONNEL AND CUSTOMERS. IN A SBIR PHASE II CONTRACT (NNX08CA36C), CRAFT TECH USED THEIR NUMERICAL SIMULATION SOFTWARE (CRUNCH CFD CODE) TO DEVELOP A MODEL THAT CAN PREDICT PERFORMANCE OF KEY SYSTEMS IN HIGH ALTITUDE TEST FACILITIES FOR ROCKET AND SATELLITE PROPULSION ENGINES, INCLUDING COLLOIDAL/ION THRUSTERS AND NUCLEAR PROPULSION ENGINES, PROVIDE DESIGN SUPPORT BY SUPPLEMENTING CURRENT EMPIRICAL RULES, AND DIAGNOSE SYSTEM ANOMALIES AS WELL AS EVALUATE TRANSIENT PERFORMANCE. IN A SUBSEQUENTLY FUNDED PHASE III PROJECT, THEY INCLUDED THERMAL/HEAT TRANSFER ANALYSIS CAPABILITY TO THIS MODEL OF THE NEW SSC A3 TEST STAND. SCOPE: THE OBJECTIVE OF THIS TASK WILL BE TO AGGRESSIVELY SPEED-UP THE TIME FOR ANALYSES OF HEAT TRANSFER AND THERMAL EFFECTS THROUGH THE UTILIZATION OF GPU (GRAPHICAL PROCESSOR UNITS) ENABLED COMPUTING. THIS EFFORT WILL SIGNIFICANTLY ENHANCE THE CURRENT ANALYSIS FRAMEWORK BY FACILITATING ANALYSES OF COMPLEX HEAT TRANSFER PROBLEMS ON DESKTOP WORKSTATIONS WITH RAPID TURNAROUND THAT CAN SUPPORT A TESTING ENVIRONMENT. TRADITIONALLY SUCH ANALYSES ARE CARRIED OUT ON MULTIPLE PROCESSORS OR PC CLUSTERS THAT REQUIRE SIGNIFICANT COSTS FOR ESTABLISHING AND MAINTAINING A COMPUTING ENVIRONMENT. IN THIS PROGRAM, THE ALGORITHMS WILL BE INNOVATIVELY RE-ENGINEERED FOR DESKTOP COMPUTERS WITH GPU ENABLED ARCHITECTURES LEADING TO SUBSTANTIAL REDUCTION IN THE COST OF CARRYING OUT ANALYSES AND SPEEDUP IN TURNAROUND TIME. THE WORK UNDER THIS TASK MUST BE PERFORMED BEFORE SEPTEMBER 30, 2012 WITH THE FINAL COMPLETED DELIVERABLE DUE WITHIN 30 DAYS OF TASK COMPLETION. HOWEVER, DUE TO THE NATURE OF THE FUNDING SOURCE AND HQ EXPECTATIONS COMPLETION OF THIS ACTIVITY WITHIN SIX MONTHS OF RECEIPT OF THE AWARD IS GREATLY DESIRED. DELIVERABLES: PROGRESS REPORTS WILL BE SUBMITTED AS APPROPRIATE. THE FINAL DELIVERABLE WILL PROVIDE THE FOLLOWING: WORKING GPU THERMAL/HEAT TRANSFER ANALYSIS ALGORITHMS OPERATING INSTRUCTIONS FOR THE GPU ALGORITHMS FINAL REPORT TO INCLUDE PROBLEMS AND ISSUES IN THE CONVERSION TO THE GPU ENABLED ARCHITECTURE. SHIP TO: ALL REQUIREMENTS HEREIN SHALL BE DELIVERED TO THE FOLLOWING ADDRESS FOB
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
COMBUSTION RESEARCH AND FLOW TECHNOLOGY INC
Contracting Agency/Office
National Aeronautics and Space Administration»Stennis Space Center
Effective date
09/23/2011
Obligated Amount
$50k
NNX11CI44P - IMMENSE QUANTITIES OF EXPENSIVE LIQUEFIED HELIUM ARE REQUIRED AT STENNIS AND KENNEDY SPACE CENTERS FOR PRE-COOLING ROCKET ENGINE PROPELLANT SYSTEMS PRIOR TO FILLING WITH LIQUID HYDROGEN, FOR PRESSURIZING TANKS AND FOR SAFELY PURGING RESIDUAL HYDROGEN. PRESENTLY, THE HELIUM USED IN THESE PROCESSES IS DISCARDED, ALONG WITH SUBSTANTIAL QUANTITIES OF HYDROGEN. TDA RESEARCH PROPOSES TO DESIGN AND BUILD A COMPACT, PORTABLE AND COST EFFECTIVE MEMBRANE SYSTEM FOR RECOVERING, PURIFYING AND STORING BOTH HELIUM AND HYDROGEN. RECOVERED HELIUM CONTAINING LESS THAN A FEW PERCENT RESIDUAL HYDROGEN CAN BE RE-USED AS A PURGE GAS. THE ULTRAPURE HYDROGEN RECOVERED CONCURRENTLY MAY BE BURNED AS FUEL OR USED TO GENERATE CLEAN ELECTRICITY IN FUEL CELLS. THE PERFORMANCE OF THESE HIGH SELECTIVITY MEMBRANES HAS BEEN DEMONSTRATED AND IS READY FOR IMPLEMENTATION TO SOLVE THIS PROBLEM. IN PHASE I WE WILL FABRICATE MEMBRANES AND ASSESS THEIR PERFORMANCE BY PROCESSING A SIMULATED PURGE GAS STREAM AND DETERMINING THE PURITIES OF THE HELIUM AND HYDROGEN. WE WILL ALSO CARRY OUT A DETAILED ENGINEERING FEASIBILITY AND COST ANALYSIS TO DETERMINE THE TECHNICAL VIABILITY OF SCALING UP THE PROCESS IN PHASE II. TDA'S SYSTEM WILL HELP NASA CONSERVE VALUABLE HYDROGEN AND THE UNITED STATE'S RAPIDLY DWINDLING AND EXPENSIVE NON-RENEWABLE HELIUM RESOURCE.
Purchase Order - 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
Contractor
TDA Research, Inc. (TDA RESEARCH, INC.)
Contracting Agency/Office
National Aeronautics and Space Administration»Mission Support Directorate»NASA Shared Services Center
Effective date
02/18/2011
Obligated Amount
$99.9k

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