Federal Contractor Profile
Advanced Cooling Technologies INC
$66M obligated·144 awards·4 agencies·15 NAICS
Federal Contracts
Showing contracts 101–150 of 176 total. Sorted by action date, most recent first. Excludes $0 modifications.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Sep 14, 2020 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX20P0134 | 541714 | SBIR PHASE 1 TOPIC A201-019 DEVELOPMENT OF A ROBUST AND RELIABLE IGNITION ASSISTANCE SYSTEM FOR MULTI-FUEL CAPABLE ENGINES | $111K |
| Sep 13, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM09C | 541712 | IGF::OT::IGF ADVANCED COOLING TECHNOLOGIES, INC. (ACT) PROPOSES TO DEVELOP A LOW-COST LOOP HEAT PIPE (LHP) EVAPORATOR USING A TECHNIQUE KNOWN AS DIRECT METAL LASER SINTERING (DMLS), OTHERWISE KNOWN AS 3D PRINTING, TO PRODUCE LOW-COST LHPS TO BE USED IN CUBESAT AND SMALLSAT APPLICATIONS. THE WICK STRUCTURE IN AN LHP ASSUMES THE ROLE OF A PUMP IN A STANDARD LOOP, PUMPING LIQUID FROM THE LOWER PRESSURE CONDENSER TO THE HIGHER PRESSURE EVAPORATOR BY CAPILLARY FORCES. THE OVERALL THERMAL PERFORMANCE OF THE SYSTEM IS THEREFORE HIGHLY DEPENDENT ON THE IN-SITU CHARACTERISTICS OF THE WICK STRUCTURE. CURRENT LHP WICK MANUFACTURING AND INSTALLATION PROCESSES ARE CUMBERSOME, LABOR INTENSIVE, AND SUFFER FROM A LOW YIELD RATE. IT IS ESTIMATED THAT THE COST TO PRODUCE AN LHP EVAPORATOR, INCLUDING THE ATTACHMENT OF THE BAYONET, SECONDARY WICK AND COMPENSATION CHAMBER, ACCOUNTS FOR APPROXIMATELY 75% OF THE TOTAL SYSTEM'S MANUFACTURING COST. BY 3D PRINTING AN EVAPORATOR ENVELOPE WITH AN INTEGRAL POROUS PRIMARY WICK STRUCTURE, THE OVERALL COMPLEXITY AND COST OF THE DESIGN CAN BE SIGNIFICANTLY REDUCED. | $375K |
| Sep 5, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0656 | 541715 | LOOP HEAT PIPE MANUFACTURING VIA DMLS FOR CUBESAT APPLICATIONS | $732K |
| Aug 31, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0271 | 541715 | 3D PRINTED LOOP HEAT PIPE | $125K |
| Aug 31, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0339 | 541715 | THERMAL MANAGEMENT SYSTEM FOR LUNAR ICE MINERS | $125K |
| Aug 31, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0520 | 541715 | DARK PHOTOVOLTAIC CELLS FOR SPACE POWER GENERATION | $121K |
| Aug 31, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0686 | 541715 | PASSIVE THERMAL CONTROL VALVES FOR LHPS&PUMPED SYSTEMS | $125K |
| Jul 6, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0178 | 541715 | AUTONOMOUS MELTING PROBE FOR ICY PLANETS EXPLORATION | $747K |
| Jul 2, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0203 | 541715 | VARIABLE CONDUCTANCE COLD PLATE FOR SPATIAL AND TEMPORAL TEMPERATURE UNIFORMITY | $750K |
| Jun 19, 2020 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833520C0579 | 541715 | RESEARCH AND DEVELOPMENT | $500K |
| Mar 24, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0055 | 541715 | ELECTRIC AIRCRAFT PROGRAM | $249K |
| Mar 2, 2020 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833519C0346 | 541715 | IGF::OT::IGF | $100K |
| Dec 19, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0023 | 541715 | SMALLSAT SWARM SPARSE APERTURE SAR FOR RECON AND SURVEILLANCE (SSSASAFRAS) | $750K |
| Oct 25, 2019 | Department of DefenseNAVAL AIR WARFARE CENTER | N6893619C0015 | 541715 | SBIR 2 N171-022 | $375K |
| Sep 23, 2019 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833519C0735 | 541715 | PROGRESS REPORT | $140K |
| Sep 18, 2019 | Department of DefenseNAVAL AIR WARFARE CENTER | N6893619P0662 | 333415 | CENTER SHAFT BASE AND TABLE WING ASSEMBLY | $115K |
| Sep 13, 2019 | Department of CommerceDEPT OF COMMERCE NIST | 1333ND19PNB680786 | 334516 | POTASSIUM FILLED ISOTHERMAL FURNACE LINERS FOR NIST PML | $81K |
| Sep 11, 2019 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833519C0775 | 541715 | RESEARCH AND DEVELOPMENT | $140K |
| Aug 30, 2019 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833519C0513 | 541715 | RESEARCH AND DEVELOPMENT | $750K |
| Jul 23, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0349 | 541715 | IN RESPONSE TO THE 2019 NASA SBIR SOLICITATION TOPIC Z2.01, SPACECRAFT THERMAL MANAGEMENT , ADVANCED COOLING TECHNOLOGIES, INC. PROPOSES THE DEVELOPMENT OF A VARIABLE CONDUCTANCE COLD PLATE TO PROVIDE SPATIAL AND TEMPORAL ISOTHERMALITY | $125K |
| Jul 23, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0363 | 541715 | AUTONOMOUS MELTING PROBE FOR ICY PLANETS EXPLORATION | $125K |
| Jul 8, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0209 | 541715 | THE PROPOSED PROGRAM WILL DEVELOP A NOVEL VAPOR-PRESSURE-DRIVEN VARIABLE-VIEW-FACTOR RADIATOR THAT IS DEPLOYABLE, OPERATES WITH VARIABLE GEOMETRY (I.E., FORM FACTOR) AND OFFERS HIGH TURNDOWN RATIO. THE DEVICE UTILIZES TWO-PHASE HEAT TRANSFER AND NOVEL GEOMETRIC FEATURES THAT ADAPTIVELY (AND REVERSIBLY) ADJUST THE VIEW FACTOR IN RESPONSE TO INTERNAL PRESSURE IN THE RADIATOR. THE RADIATOR FOLDS INTO A CLOSED SHAPE TO MINIMIZE THE VIEW FACTOR WHEN COLD, AND OPENS UP TO MAXIMIZE THE VIEW FACTOR WHEN HEATED. PROTOTYPES DEMONSTRATED IN PHASE I PROVE THE FEASIBILITY AND HIGHLIGHT THE ADVANTAGES OF A TWO-PHASE RADIATOR OVER SHAPE MEMORY ALLOY TECHNOLOGIES. STRUCTURAL AND THERMAL SIMULATION STUDIES CONFIRMED THE VIABILITY OF THE CONCEPT. AT LOW TEMPERATURES, THE VIEW FACTOR OF EMISSIVE SURFACES OF THE RADIATOR TO THE HEAT SINK IS NEAR ZERO, SO THE ONLY HEAT LOST IS THAT WHICH IS EMITTED FROM THE INSULATED OUTER SURFACES OF THE RADIATOR. THE FLEXIBLE SECTION OF THE RADIATOR IS AN ELASTIC ENVELOPE ENCLOSING A SATURATED WORKING FLUID. WHEN THE TEMPERATURE OF THE RADIATOR INCREASES, THE CORRESPONDING INCREASE IN VAPOR PRESSURE GENERATES A NET FORCE ON THE INTERIOR WALLS OF THE ENVELOPE WHICH CAUSES THE ELASTIC WALLS TO BEND SO THAT THE STRUCTURE OPENS AND THE VIEW FACTOR INCREASES. THE INCREASE IN VIEW FACTOR REDUCES THERMAL RESISTANCE OF HEAT REJECTION WHICH ENABLES INHERENTLY PASSIVE THERMAL CONTROL. ADDITIONALLY, THE ENTIRE STRUCTURE OF THE RADIATOR CONSISTS OF CAVITIES FILLED WITH SATURATED FLUID ACTING LIKE HEAT PIPES, SO THE RADIATING SURFACE WILL BE NEARLY ISOTHERMAL, ACHIEVING A RADIATOR PANEL EFFICIENCY NEAR ONE. IN PHASE I, MODELING AND PROTOTYPING INDICATES THAT THE BASELINE GEOMETRY PROPOSED CAN ACHIEVE A THERMAL TURNDOWN RATIO OF 37:1. | $749K |
| Jul 2, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019C5050 | 541715 | SBIR II, PROCESS MODELING FRAMEWORK FOR LINEAR FRICTION WELD | $750K |
| May 13, 2019 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833519C0346 | 541715 | IGF::OT::IGF | $140K |
| Feb 20, 2019 | Department of DefenseNAVAL AIR WARFARE CENTER | N6893619P0175 | 332710 | NAWCWD CENTER SHAFT BASE AND TABLE WING | $92K |
| Dec 12, 2018 | Department of DefenseW4PZ USA MED RSCH ACQUIS ACT | W81XWH19C0036 | 541715 | DHA SBIR PHASE I - H182-003-0034 PROPOSAL TITLED "LIMB COOLING DEVICE TO PRESERVE ISCHEMIC EXTREMITY FOR PROLONGED FIELD CARE" MEDICAL R&D SERVICE CONTRACT. | $150K |
| Oct 29, 2018 | Department of DefenseNAVAL AIR WARFARE CENTER | N6893619C0015 | 541715 | SBIR 2 N171-022 | $375K |
| Sep 20, 2018 | Department of DefenseDEFENSE MICROELECTRONICS ACTIVITY | HQ072718C0008 | 541713 | STTR PHASE II, DMEA 16B-0001, THICKNESS MEASUREMENT TECHNOLOGY FOR THIN FILMS ON SAPPHIRE SUBSTRATE. | $1000K |
| Sep 8, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2723 | 541715 | PHASE III (NON-SBIR FUNDS): $ 100,000 TASK 1: DESIGN REQUIREMENTS TASK 4: DEVELOPMENT OF ALUMINUM AMMONIA HOT RESERVOIR VCHP FOR LUNAR LANDER 50% OF TASK 6: REPORTING | $100K |
| Sep 7, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CM03C | 541712 | IGF::OT::IGF THE THERMAL TRANSPORT REQUIREMENTS FOR FUTURE SPACECRAFT MISSIONS CONTINUE TO INCREASE, APPROACHING SEVERAL KILOWATTS. AT THE SAME TIME THE HEAT ACQUISITION AREAS HAVE TRENDED DOWNWARD, THEREBY INCREASING THE INCIDENT HEAT FLUX. CURRENT INCIDENT HEAT FLUX FOR LASER DIODE APPLICATIONS IS ON THE ORDER OF 5-10W/CM2, ALTHOUGH THIS IS EXPECTED TO INCREASE TOWARDS 50W/CM2. THIS IS A SEVERE LIMITATION FOR AXIAL GROOVE ALUMINUM/AMMONIA CONSTANT CONDUCTANCE HEAT PIPES (CCHPS). THE MAXIMUM HEAT FLUX IN A CCHP IS SET BY THE BOILING LIMIT, WHICH TYPICALLY START AT 5 W/CM2 FOR AXIAL GROVE WICKS, AND 20-30 W/CM2 FOR POWDER METAL WICKS. THE INNOVATION IS TO DEVELOP CCHPS WITH A HYBRID WICK, WHICH HAS A SINTERED EVAPORATOR WICK, AND A CONVENTIONAL GROOVED ADIABATIC AND CONDENSER WICK. THESE HYBRID WICKS CAN OPERATE AT HIGHER HEAT FLUXES, ALLOWING THE USE OF HIGHER POWER LASER DIODES. THEY ALSO ALLOW THE USE OF VARIABLE CONDUCTANCE HEAT PIPES (VCHPS) IN LUNAR AND MARTIAN LANDERS AND ROVERS, WHICH MUST OPERATE AT TILTS UP TO 45 . CONVENTIONAL ALUMINUM/AMMONIA HEAT PIPES CAN ONLY OPERATE WITH A 0.1 INCH TILT, SO THEY ARE UNSUITABLE. LOOP HEAT PIPES CAN ALSO OPERATE WITH TILTING, BUT THEY ARE TWO ORDERS OF MAGNITUDE MORE EXPENSIVE. A HYBRID GROOVED AND SINTERED WICK CCHP WILL ALLOW OPERATING AT HIGHER HEAT FLUXES AS COMPARED TO AXIAL GROOVE DESIGN AND CAN ALSO OPERATE AGAINST GRAVITY ON THE PLANETARY SURFACE, OPERATE IN SPACE, CARRYING POWER OVER LONG DISTANCES, ACT AS A THERMOSYPHON ON THE PLANETARY SURFACE FOR LUNAR AND MARTIAN LANDERS AND ROVERS, AND DEMONSTRATE A HIGHER TRANSPORT CAPABILITY THAN AN ALL-SINTERED WICK. | $200K |
| Aug 8, 2018 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833518C0118 | 541715 | IGF::OT::IGF | $100K |
| Jul 20, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2187 | 541715 | NASA S SPACE TECHNOLOGY MISSION DIRECTORATE (STMD) IS INVESTIGATING TECHNOLOGIES FOR THERMAL CONTROL SYSTEMS (TCS) IN HUMAN SPACEFLIGHT VEHICLES, SUCH AS VARIABLE GEOMETRY SPACECRAFT RADIATOR. THE TCS IN CREWED VEHICLES MUST MAINTAIN A RELATIVELY CONSTANT ENVIRONMENT TEMPERATURE FOR A WIDE RANGE OF EXTERNAL THERMAL ENVIRONMENTS (LOW EARTH ORBIT, TRANS-PLANETARY COAST, AND PLANETARY SURFACE OPERATIONS). THE SINK TEMPERATURE MAY VARY FROM APPROXIMATELY 70 K TO 230 K. RECENT RESEARCHES INVESTIGATED AND PRESENTED POTENTIAL OF HEAT REJECTION CAPABILITY FROM THE MORPHING COMPOSITE / SHAPE MEMORY ALLOYS (SMA) RADIATOR. THE SMA RADIATOR EMPLOYS SUCH TEMPERATURE DEPENDENT SMA MATERIALS TO PASSIVELY MORPH THE RADIATOR SHAPE AND THUS ADJUST THE RATE OF HEAT REJECTION TO A WIDE RANGE OF VEHICLE REQUIREMENTS. NONETHELESS, UTILIZING SMA MATERIALS FACES MANY DISADVANTAGES, INCLUDING LOW ACTUATION FREQUENCY, SENSITIVITY OF MATERIAL PROPERTIES IN FABRICATION, RESIDUAL STRESS S DEVELOPED IN THIN FILMS, AND NONLINEARITY OF ACTUATION FORCE. ADVANCED COOLING TECHNOLOGIES, INC. (ACT) PROPOSES TO DEVELOP A NOVEL VAPOR-PRESSURE-DRIVEN VARIABLE VIEW FACTOR RADIATOR AS A THERMAL CONTROL SYSTEM COMPONENT FOR SPACECRAFT. SIMILAR TO SMA RADIATOR MECHANISM, THE RADIATOR FOLDS INTO A TEAR DROP SHAPE TO MINIMIZE THE VIEW FACTOR WHEN COLD, AND OPENS UP TO MAXIMIZE THE VIEW FACTOR WHEN HEATED. HOWEVER, THE PROPOSED DEVICE INSTEAD UTILIZES VAPOR PRESSURE INSIDE A HOLLOW CURVED PANEL TO CHANGE THE SHAPE OF THE RADIATOR. IN PHASE I, A PROOF-OF-CONCEPT TWO-PHASE VAPOR PRESSURE DRIVEN MORPHING RADIATOR PROTOTYPE WILL BE FABRICATED AND TESTED. TEST RESULTS WILL BE USED TO VALIDATE A THERMOSTRUCTURAL MODEL, WHICH WILL BE EMPLOYED TO DESIGN THE FULL-SCALE PROTOTYPE | $125K |
| Jul 18, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865018P5057 | 541715 | NOVEL PROCESS MODELING FRAMEWORK FOR LINEAR FRICTION WELDING | $150K |
| Jul 16, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2155 | 541715 | IN CONTRAST TO THE STANDARD COLD RESERVOIR VARIABLE CONDUCTANCE HEAT PIPE (VCHP) WHERE FOR TIGHT THERMAL CONTROL AN ELECTRICAL HEATER IS USED FOR THE RESERVOIR (WICKED), ADVANCED COOLING TECHNOLOGIES, INC (ACT) DEVELOPED A HOT RESERVOIR VCHP WITH THE RESERVOIR THERMALLY COUPLED TO THE EVAPORATOR. THIS NOVEL FEATURE WILL PROVIDE A TIGHT TEMPERATURE CONTROL CAPABILITY WITHOUT THE NEED FOR CONTROL POWER. BASED ON THE RECENT ISS TESTING RESULT, IT WAS CONCLUDED THAT WORKING FLUID MANAGEMENT WITHIN THE RESERVOIR AND THE NCG TUBE (TYPICALLY NON-WICKED) OF VCHPS IS THE KEY TO ADVANCE THE RELIABILITY OF A HOT RESERVOIR VCHP, WHICH WILL SECURE A SUCCESSFUL LONG-TERM MISSION OF PLANETARY LANDERS. UNDER THIS STTR TOPIC, ACT WILL COLLABORATE WITH CASE WESTERN RESERVE UNIVERSITY (CWRU) TO IMPLEMENT SEVERAL NOVEL FLUID MANAGEMENT FEATURES TO ENHANCE SYSTEM RELIABILITY OF HOT RESERVOIR VCHP. ACT WILL DEVELOP SEVERAL ADVANCED FLUID MANAGEMENT FEATURES AND TEST THEIR PERFORMANCE ON A HOT RESERVOIR VCHP PROTOTYPE. IN PARALLEL, CWRU WILL PERFORM A FUNDAMENTAL STUDY AND MATHEMATICAL MODEL DEVELOPMENT TO SIMULATE AND UNDERSTAND THE COMPLEXITY OF THE TRANSPORT PHENOMENA PROBLEM WITHIN THE TWO-PHASE WORKING FLUID AND NON-CONDENSABLE GAS MIXTURE IN THE RESERVOIR AND THE NCG TUBE. THE OBJECTIVE OF THE CWRU S EFFORT IS TO BRING DEEP UNDERSTANDING OF THE THERMAL-FLUID AND THERMODYNAMIC ENVIRONMENT IN THE VCHP RESERVOIR AND NCG TUBE AND IDENTIFY AN EFFECTIVE PURGING MECHANISM (I.E. VAPOR REMOVAL FROM A HOT RESERVOIR), WHICH IS CRUCIAL IN DESIGNING A RELIABLE HOT RESERVOIR VCHP FOR FUTURE PLANETARY LANDER THERMAL MANAGEMENT | $125K |
| Jul 16, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2186 | 541715 | A RELIABLE THERMAL MANAGEMENT SYSTEM THAT WILL ENABLE AT LEAST 24-HOURS SURVIVAL OF VENUS LANDERS IN THE EXTREME ENVIRONMENT (460 C, 92 BAR) IS HIGHLY DESIRABLE FOR NASA FUTURE VENUS IN-SITU EXPLORATION MISSIONS. IN RESPONSE TO THE NASA SBIR SOLICITATION, ADVANCED COOLING TECHNOLOGIES, INC. (ACT) PROPOSES TO DEVELOP A CONSUMABLE-BASED COOLING SYSTEM FOR VENUS LANDERS WASTE HEAT REJECTION. THE PROPOSED SYSTEM CONSISTS OF TWO PRESSURIZED VESSELS: A PRIMARY VESSEL CHARGED WITH A CONSUMABLE FLUID IN A SATURATION STATE (AMMONIA) AND A SECONDARY VESSEL FILLED WITH COMPRESSED GAS. THE MAIN ROLE OF THE COMPRESSED GAS IS TO HELP AMMONIA VAPOR VENTING INTO A HIGHER-PRESSURE ENVIRONMENT THAN THE VAPOR PRESSURE THAT CORRESPONDS TO THE COOLED ELECTRONICS TEMPERATURE. THROUGH VENTING A MIXTURE OF CONSUMABLE VAPOR AND COMPRESSED GAS TO THE VENUS AMBIENT, A SIGNIFICANT AMOUNT OF EVAPORATIVE COOLING (PRIMARY) AND JOULE-THOMPSON COOLING (SECONDARY) CAN BE ACHIEVED, WHICH NOT ONLY WILL KEEP THE ELECTRONICS TEMPERATURE COOL BUT ALSO PROVIDE HEAT GUARDING BY COLLECTING AND REMOVING THE INCOMING HEAT LEAKS FROM VENUS ENVIRONMENT. IN PHASE I, A PROOF-OF-CONCEPT CONSUMABLE BASED PROTOTYPE WILL BE FABRICATED AND TESTED. TEST RESULTS WILL BE USED TO VALIDATE A MATHEMATICAL MODEL. AFTER VALIDATION, THE MODEL WILL BE EMPLOYED TO DESIGN THE FULL-SCALE PROTOTYPE AND OPTIMIZE MASS AND THERMAL PERFORMANCE. A PRELIMINARY MODELING RESULT SHOWS A THERMAL MANAGEMENT SYSTEM TOTAL MASS (FLUIDS AND STRUCTURE) OF 75KG. | $125K |
| Jul 2, 2018 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833516C0114 | 541712 | IGF::OT::IGF RESEARCH AND DEVELOPMENT | $250K |
| Apr 27, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017C2032 | 541712 | IGF::OT::IGF DURABLE PRE-COOLING HEAT EXCHANGERS FOR HIGH MACH FLIGHT - SBIR PHASE 2 | $187K |
| Mar 20, 2018 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833515C0032 | 541712 | STTR PHASE II RESEARCH AND DEVELOPMENT | $300K |
| Mar 19, 2018 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833518C0287 | 541715 | RESEARCH AND DEVELOPMENT IGF::OT::IGF | $125K |
| Feb 5, 2018 | Department of DefenseNAVAL AIR WARFARE CENTER | N6893617C0043 | 541712 | IGF::OT::IGF; SBIR 1 N171-022 NOVEL HIGH DENSITY FUELS DEVELOPMENT. | $100K |
| Nov 16, 2017 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833518C0118 | 541715 | IGF::OT::IGF | $125K |
| Sep 29, 2017 | Department of DefenseNSWC CARDEROCK | N0016717P0441 | 541712 | IGF::OT::IGF PHASE I BAA- ACT INC CONCEPT | $150K |
| Sep 25, 2017 | Department of DefenseDEFENSE MICROELECTRONICS ACTIVITY | HQ072717P0026 | 541712 | IGF::OT::IGF STTR PHASE I RESEARCH STUDY, DMEA 16B-0001, THICKNESS MEASUREMENT TECHNOLOGY FOR THIN FILMS ON SAPPHIRE SUBSTRATE | $71K |
| Sep 5, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017C2032 | 541712 | IGF::OT::IGF DURABLE PRE-COOLING HEAT EXCHANGERS FOR HIGH MACH FLIGHT - SBIR PHASE 2 | $563K |
| Aug 18, 2017 | Department of DefenseDEFENSE MICROELECTRONICS ACTIVITY | HQ072717P0026 | 541712 | IGF::OT::IGF STTR PHASE I RESEARCH STUDY, DMEA 16B-0001, THICKNESS MEASUREMENT TECHNOLOGY FOR THIN FILMS ON SAPPHIRE SUBSTRATE | $79K |
| Jun 21, 2017 | Department of DefenseHQUSSOCOM | H9222217P0060 | 541712 | IGF::OT::IGF SBIR 17.1 PHASE I, FEASIBILITY STUDY, TOPIC USSOCOM 002 MOISTURE WICKING PATHWAY TREATMENT FOR TEXTILES | $150K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CS05P | 541712 | IGF::OT::IGF IN RESPONSE TO THE NASA STTR SOLICITATION TOPIC T3.01, "ENERGY HARVESTING, TRANSFORMATION AND MULTIFUNCTIONAL POWER DISSEMINATION", ADVANCED COOLING TECHNOLOGIES, INC. (ACT) AND CARNEGIE MELLON UNIVERSITY (CMU) PROPOSE TO DEVELOP A THERMO-RADIATIVE CELL TO HARVEST ENERGY FROM WASTE HEAT, FOR EXAMPLE, FROM RADIATORS. CURRENTLY NASA'S TOP TECHNICAL CHALLENGE IS THE NEED TO "INCREASE AVAILABLE POWER". ADDITIONALLY, NASA HAS A GRAND CHALLENGE AS "AFFORDABLE AND ABUNDANT POWER" FOR NASA MISSION ACTIVITIES. THE THERMORADIATIVE CELL TECHNOLOGY USES SEMICONDUCTOR P-N JUNCTIONS, SIMILAR TO THE PHOTOVOLTAIC CELL BUT WITH SMALLER BAND GAP SEMICONDUCTOR, TO CONVERT HEAT TO ELECTRICITY. THIS TECHNOLOGY MAKES USE OF THE EXTREMELY COLD DARK UNIVERSE (~3K) AS THE NATURAL HEAT SINK AND LOW-GRADE WASTE HEAT (~50-100℃) AS THE HEAT SOURCE. THE IMBALANCE OF THE THERMAL RADIATION EMITTED AND ABSORBED BY THE CELL WILL CAUSE THE IMBALANCE OF THE CHARGE CARRIER MOTION IN THE P-N JUNCTION, I.E., GENERATING ELECTRICAL POWER. THE OVERALL TECHNICAL OBJECTIVE OF PHASE I AND PHASE II PROJECTS IS TO DEVELOP A THERMO-RADIATIVE CELL SYSTEM THAT CAN GENERATE PRACTICALLY USABLE POWER AS SUPPLEMENTARY POWER FOR THE ELECTRONICS ON SPACE VEHICLES, PLATFORMS OR HABITATS. DURING PHASE I, ACT WILL FABRICATE A CRYOGENIC SYSTEM TO INVESTIGATE THE PERFORMANCE THE THERMO-RADIATIVE CELL MADE OF COMMERCIAL AVAILABLE INSB, HGCDZNTE, PBSE, OR INAS WAFERS. THE CRYOGENIC SYSTEM WILL USE LIQUID NITROGEN TO CREATE A STABLE LOW TEMPERATURE ENVIRONMENT. PERFORMANCE INVESTIGATION INCLUDES THE POWER DENSITY AND ENERGY EFFICIENCY AT DIFFERENT HEAT SOURCE TEMPERATURES FOR THE NON-OPTIMIZED CELL MATERIAL COMPONENT AND STRUCTURE IN PHASE I. | $125K |
| May 5, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM09C | 541712 | IGF::OT::IGF ADVANCED COOLING TECHNOLOGIES, INC. (ACT) PROPOSES TO DEVELOP A LOW-COST LOOP HEAT PIPE (LHP) EVAPORATOR USING A TECHNIQUE KNOWN AS DIRECT METAL LASER SINTERING (DMLS), OTHERWISE KNOWN AS 3D PRINTING, TO PRODUCE LOW-COST LHPS TO BE USED IN CUBESAT AND SMALLSAT APPLICATIONS. THE WICK STRUCTURE IN AN LHP ASSUMES THE ROLE OF A PUMP IN A STANDARD LOOP, PUMPING LIQUID FROM THE LOWER PRESSURE CONDENSER TO THE HIGHER PRESSURE EVAPORATOR BY CAPILLARY FORCES. THE OVERALL THERMAL PERFORMANCE OF THE SYSTEM IS THEREFORE HIGHLY DEPENDENT ON THE IN-SITU CHARACTERISTICS OF THE WICK STRUCTURE. CURRENT LHP WICK MANUFACTURING AND INSTALLATION PROCESSES ARE CUMBERSOME, LABOR INTENSIVE, AND SUFFER FROM A LOW YIELD RATE. IT IS ESTIMATED THAT THE COST TO PRODUCE AN LHP EVAPORATOR, INCLUDING THE ATTACHMENT OF THE BAYONET, SECONDARY WICK AND COMPENSATION CHAMBER, ACCOUNTS FOR APPROXIMATELY 75% OF THE TOTAL SYSTEM'S MANUFACTURING COST. BY 3D PRINTING AN EVAPORATOR ENVELOPE WITH AN INTEGRAL POROUS PRIMARY WICK STRUCTURE, THE OVERALL COMPLEXITY AND COST OF THE DESIGN CAN BE SIGNIFICANTLY REDUCED. | $750K |
| Apr 28, 2017 | Department of DefenseOFFICE OF NAVAL RESEARCH | N0001414C0118 | 541712 | LONG RANGE BROAD AGENCY ANNOUNCEMENT (BAA) FOR NAVY AND MARINE CORPS SCIENCE AND TECHNOLOGY | $224K |
| Apr 27, 2017 | Department of DefenseNAVAL AIR WARFARE CENTER | N6893617C0043 | 541712 | IGF::OT::IGF; SBIR 1 N171-022 NOVEL HIGH DENSITY FUELS DEVELOPMENT. | $125K |
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