The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $99,994 - Wednesday the 18th of January 2012
  Department Of Army
  W6QK ACC-RSA
  DARPA PHASE I

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• $75,000 - Wednesday the 19th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THIS SMALL BUSINESS INNOVATION RESEARCH (SBIR) PROJECT PROPOSES THE DEVELOPMENT OF A COMPUTATIONAL SOFTWARE PACKAGE TO PROVIDE NASA WITH ADVANCED MATERIALS DEVELOPMENT CAPABILITIES FOR EXISTING AND NEW ABLATIVE MATERIALS USED IN THE NEXT GENERATION THERMAL PROTECTION SYSTEMS (TPS) OF SPACE VEHICLES. THIS MATERIALS DEVELOPMENT SOFTWARE PACKAGE (MDSAM) CAN BE USED TO OPTIMIZE PROPERTIES (HIGH STRENGTH AND LOW THERMAL CONDUCTIVITY) FOR BOTH THE VIRGIN MATERIAL AS WELL AS THE CHAR THAT FORMS DURING THE OPERATING CONDITIONS. IT WILL PROVIDE ATOMISTIC-LEVEL INFORMATION ON CHAR EVOLUTION AND THE DEGRADATION OF THERMO-MECHANICAL PROPERTIES. THE PROPOSED MDSAM WILL CONSIST OF THE FOLLOWING TWO MODULES: (I) AN EXPERIMENTALLY VALIDATED, ATOMISTIC-LEVEL SIMULATION ENGINE CAPABLE OF PREDICTING THE ROLE OF INTERFACIAL STRUCTURE ON THE RESIN-TO-CARBON PROCESS AND (II) ATOMISTICALLY-INFORMED CONTINUUM-LEVEL THERMO-MECHANICAL PERFORMANCE ANALYZER FOR COMPOSITE ABLATIVE MATERIALS SUBJECTED TO TRANSIENT PYROLYTIC CONDITIONS. THE UNDERLYING METHODOLOGY AND THE SOFTWARE PACKAGE WILL BE TRANSITIONED TO NASA SCIENTISTS WORKING ON ABLATIVE MATERIALS DEVELOPMENT. IN ADDITION TO DEVELOPING A COMPUTATIONAL SOFTWARE PACKAGE, WE WILL ADDRESS OPEN, UNSOLVED PROBLEMS IN THE LITERATURE TO SUPPORT NASA'S ABLATIVE MATERIALS DEVELOPMENT REQUIREMENTS. IN THE COURSE OF DEVELOPING THIS METHODOLOGY, WE WILL PRODUCE SIGNIFICANT SCIENTIFIC RESULTS ON PYROLYSIS AND MATERIALS PROPERTIES THAT WILL BE IMPORTANT TO NASA.

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• $50,000 - Saturday the 29th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE OVERALL PROGRAM OBJECTIVE IS TO DEVELOP A HIGH-TEMPERATURE PASSIVE THERMAL MANAGEMENT SYSTEM FOR THE RADIOISOTOPE POWER CONVERSION SYSTEM THAT ENERGIZES THE REFRIGERATION SYSTEM APPLICABLE TO VENUS MISSIONS. THE INNOVATION CONSISTS OF A HIGH TEMPERATURE ALKALI METAL VARIABLE CONDUCTANCE HEAT PIPE (VCHP) INTEGRATED WITH A TWO-PHASE HEAT COLLECTION / TRANSPORT PACKAGE FROM THE GENERAL PURPOSE HEAT SOURCE (GPHS) STACK TO THE STIRLING CONVERTOR HEATER HEAD. THE THERMAL MANAGEMENT SYSTEM COLLECTS THE HEAT FROM THE GPHS MODULES, AND DELIVERS HEAT AS REQUIRED TO THE STIRLING SYSTEM. ANY EXCESS HEAT IS REMOVED BY THE VCHP. EXCESS HEAT MUST BE REMOVED WHEN THE STIRLING SYSTEM IS SHUT DOWN, OR IN THE EARLY STAGES OF A MISSION POWERED BY A SHORT-LIFE RADIOISOTOPE. IN PHASE I, IT WAS DEMONSTRATED EXPERIMENTALLY AND THEORETICALLY THAT THE VCHP ALLOWS THE STIRLING CONVERTOR TO: STOP DURING TRANSIT TO VENUS, PRE-COOL THE SYSTEM BEFORE RE-ENTRY, WORK ON VENUS AND EXECUTE BRIEF STOPPAGES ON VENUS. THE RESERVOIR IS EXPOSED TO THE ENVIRONMENT TEMPERATURE DURING THE MISSION AND THIS IS A KEY FOR THE HTTMS TO WORK PASSIVELY. THE OTHER COMPONENT OF THE SYSTEM, THE TWO-PHASE HEAT TRANSPORT PACKAGE (HTP), MINIMIZES THE TEMPERATURE DROP BETWEEN THE MULTI-GPHS STACK AND THE HEATER HEAD. IN PHASE II, A FULL SCALE HTTMS WILL BE DESIGNED AND A REPRESENTATIVE MULTI-SEGMENT OF THE FULL SCALE HTTMS WILL BE BUILD AND TESTED IN RELEVANT ENVIRONMENT. THIS MULTI-SEGMENT CONTAINS TWO OR THREE PARALLEL/REDUNDANT HEAT PATHS FROM THE SIMULATED GPHS STACK TO THE HEATER HEAD SIMULATOR, IN ADDITION TO THE BACKUP COOLING SYSTEM (VCHP). THE FULL-SCALE MULTI-SEGMENT HTTMS WILL BE INTEGRATED AND TESTED WITH THE CORRESPONDING FULL SCALE MULTI-SEGMENT OF THE INTERMEDIATE TEMPERATURE THERMAL MANAGEMENT SYSTEM (ITTMS) OF THE VENUS LANDER.

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• $374,993 - Wednesday the 27th of June 2012
  Office Of Policy Budget And Administration
  NBC ACQUISITION SERVICES DIVISION
  ADVANCED COOLING TECHNOLOGY (10.1 PH II) IMPLEMENT OPTION

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• $374,955 - Tuesday the 30th of October 2012
  Department Of Air Force
  FA8650 USAF AFMC AFRL/RQK
  COMPLETION OF FUNDING

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• $31,500 - Friday the 12th of September 2014
  National Aeronautics And Space Administration
  GODDARD SPACE FLIGHT CENTER
  ALUMINUM/ETHANE CONSTANT CONDUCTANCE HEAT PIPE (1 EACH) ALUMINUM/AMMONIA CONSTANT CONDUCTANCE HEAT PIPES (3 EACH) NRE (PROGRAM MANAGEMENT, TOOLING AND TEST) (1 EACH)

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• $221,000 - Friday the 21st of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  FUTURE LUNAR LANDERS AND ROVERS WILL REQUIRE VARIABLE THERMAL LINKS THAT CAN REJECT HEAT DURING DAYTIME, AND PASSIVELY SHUT-OFF DURING LUNAR NIGHT. DURING THE LONG LUNAR DAY, THE THERMAL MANAGEMENT SYSTEM MUST REMOVE THE WASTE HEAT FROM THE ELECTRONICS AND BATTERIES KEEP THEM WITHIN THE ACCEPTABLE TEMPERATURE LIMIT. SINCE THE HEATER POWER AVAILABILITY IS RESTRICTED, A VARIABLE THERMAL LINK IS THEREFORE REQUIRED TO LIMIT THE AMOUNT OF HEAT THAT IS REMOVED FROM THE ELECTRONICS AND RADIATED TO SPACE DURING THE LONG LUNAR NIGHT. CONVENTIONAL LOOP HEAT PIPES (LHPS) CAN PROVIDE THE REQUIRED VARIABLE THERMAL CONDUCTANCE, BUT THEY CONSUME ELECTRICAL POWER TO SHUT DOWN THE HEAT TRANSFER. OUR INNOVATION ADDS A THERMAL CONTROL VALVE (TCV) TO THE LHP, ALLOWING IT TO PASSIVELY SHUT OFF WITHOUT CONSUMING ANY ELECTRICAL POWER. THIS IS IMPORTANT SINCE THERE IS A SEVERE PENALTY FOR ELECTRICAL POWER CONSUMPTION: SUPPLYING 1 W IN A PHOTOVOLTAIC SYSTEM REQUIRES ROUGHLY 5 KG OF EXTRA EQUIPMENT. THE TCV USED IN THE LHP HAS BEEN PREVIOUSLY SELECTED FOR THERMAL CONTROL IN THE PUMPED LOOP ON THE MARS SCIENCE LABORATORY. THE PHASE I PROJECT WAS SUCCESSFUL IN DEMONSTRATING THE FEASIBILITY OF INTEGRATING THE TCV IN A LHP. THE PHASE II PROJECT WILL FABRICATE AND TEST A LHP WITH A TCV AT REPRESENTATIVE CONDITIONS, BRINGING THE TECHNOLOGY TO TRL 6. THE TESTING WILL INCLUDE FULL CHARACTERIZATION OF THE TCV UNDER VARIOUS LHP OPERATION MODES. ANALYSIS AND TESTING OF DIFFERENT LHP CONDENSER LAYOUTS WILL ALSO BE PERFORMED, AS WELL AS FREEZE/THAW ANALYSIS.

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• $200,000 - Saturday the 29th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE OVERALL PROGRAM OBJECTIVE IS TO DEVELOP A HIGH-TEMPERATURE PASSIVE THERMAL MANAGEMENT SYSTEM FOR THE RADIOISOTOPE POWER CONVERSION SYSTEM THAT ENERGIZES THE REFRIGERATION SYSTEM APPLICABLE TO VENUS MISSIONS. THE INNOVATION CONSISTS OF A HIGH TEMPERATURE ALKALI METAL VARIABLE CONDUCTANCE HEAT PIPE (VCHP) INTEGRATED WITH A TWO-PHASE HEAT COLLECTION / TRANSPORT PACKAGE FROM THE GENERAL PURPOSE HEAT SOURCE (GPHS) STACK TO THE STIRLING CONVERTOR HEATER HEAD. THE THERMAL MANAGEMENT SYSTEM COLLECTS THE HEAT FROM THE GPHS MODULES, AND DELIVERS HEAT AS REQUIRED TO THE STIRLING SYSTEM. ANY EXCESS HEAT IS REMOVED BY THE VCHP. EXCESS HEAT MUST BE REMOVED WHEN THE STIRLING SYSTEM IS SHUT DOWN, OR IN THE EARLY STAGES OF A MISSION POWERED BY A SHORT-LIFE RADIOISOTOPE. IN PHASE I, IT WAS DEMONSTRATED EXPERIMENTALLY AND THEORETICALLY THAT THE VCHP ALLOWS THE STIRLING CONVERTOR TO: STOP DURING TRANSIT TO VENUS, PRE-COOL THE SYSTEM BEFORE RE-ENTRY, WORK ON VENUS AND EXECUTE BRIEF STOPPAGES ON VENUS. THE RESERVOIR IS EXPOSED TO THE ENVIRONMENT TEMPERATURE DURING THE MISSION AND THIS IS A KEY FOR THE HTTMS TO WORK PASSIVELY. THE OTHER COMPONENT OF THE SYSTEM, THE TWO-PHASE HEAT TRANSPORT PACKAGE (HTP), MINIMIZES THE TEMPERATURE DROP BETWEEN THE MULTI-GPHS STACK AND THE HEATER HEAD. IN PHASE II, A FULL SCALE HTTMS WILL BE DESIGNED AND A REPRESENTATIVE MULTI-SEGMENT OF THE FULL SCALE HTTMS WILL BE BUILD AND TESTED IN RELEVANT ENVIRONMENT. THIS MULTI-SEGMENT CONTAINS TWO OR THREE PARALLEL/REDUNDANT HEAT PATHS FROM THE SIMULATED GPHS STACK TO THE HEATER HEAD SIMULATOR, IN ADDITION TO THE BACKUP COOLING SYSTEM (VCHP). THE FULL-SCALE MULTI-SEGMENT HTTMS WILL BE INTEGRATED AND TESTED WITH THE CORRESPONDING FULL SCALE MULTI-SEGMENT OF THE INTERMEDIATE TEMPERATURE THERMAL MANAGEMENT SYSTEM (ITTMS) OF THE VENUS LANDER.

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• $149,995 - Wednesday the 18th of July 2012
  Department Of Air Force
  FA8650 USAF AFMC AFRL/RQK
  ADAPTIVE VCS CONDENSER WITH INTEGRATED VCHPS FOR AIRCRAFT THERMAL MANAGEMENT

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• $149,933 - Thursday the 30th of August 2012
  Department Of Army
  W6QK ACC-APG ADELPHI
  SBIR PHASE 1, TOPIC # OSD11-EP1

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