The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $99,996 - Wednesday the 18th of January 2012
  Missile Defense Agency
  MISSILE DEFENSE AGENCY (MDA)
  PH I RESEARCH&DEVELOPMENT

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• $99,995 - Wednesday the 18th of January 2012
  Missile Defense Agency
  MISSILE DEFENSE AGENCY (MDA)
  PH I RESEARCH&DEVELOPMENT

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• $99,989 - Monday the 24th of October 2011
  Department Of Army
  W6QK ACC-RSA
  ARMY SBIR PHASE I ENTITLED "COUPLED PYROLYSIS, RADIANT HEAT TRANSFER, AND FLUID DYNAMICS MODELING"

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• $79,989 - Friday the 4th of May 2012
  Department Of Navy
  NAVAIR WARFARE CTR AIRCRAFT DIV LKE
  SBIR PHASE I TOPIC N121-028

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• $75,000 - Saturday the 1st of December 2012
  National Aeronautics And Space Administration
  STENNIS SPACE CENTER
  IGF::OT::IGF OTHER FUNCTIONS: COUPLING RADIATION TRANSFER EQUATION WITH CRUNCH CFD

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• $749,981 - Monday the 9th of March 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF 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.

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• $749,973 - Thursday the 27th of October 2016
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - THE PROPOSED SBIR PHASE II PROGRAM WILL LEAD TO THE VALIDATION OF A STATE-OF-THE-ART LARGE EDDY SIMULATION (LES) MODEL, COUPLED WITH A FFOWCS-WILLIAMS-HAWKINGS (FW-H) FARFIELD ACOUSTIC SOLVER, FOR SUPPORTING THE DEVELOPMENT OF ADVANCED ENGINE CONCEPTS, INCLUDING INNOVATIVE FLOW CONTROL STRATEGIES FOR ATTENUATION OF THEIR JET NOISE EMISSIONS. DURING PHASE I, THE LES/FW-H MODEL WAS VALIDATED AGAINST MATCHED SETS OF FLOWFIELD AND COMPANION ACOUSTIC DATA ACQUIRED AT NASA/GRC FOR ROUND NOZZLES. THE FLOWFIELD VALIDATION INCLUDED DETAILED COMPARISONS AGAINST IMAGERY, MEAN FLOW MEASUREMENTS AND TURBULENCE STATISTICS. DURING PHASE II, THE END-TO-END LES/FW-H NOISE PREDICTION MODEL WILL BE DEMONSTRATED AND VALIDATED BY APPLYING IT TO HIGH ASPECT-RATIO RECTANGULAR NOZZLE DESIGNS, PROPOSED FOR TESTING AT NASA GRC UNDER THE FUNDAMENTAL AERONAUTICS PROGRAM. THE MODEL WILL ALSO BE VALIDATED AGAINST ACOUSTIC AND FLOWFIELD DATA FROM A REALISTIC JET-PYLON EXPERIMENT, THEREBY SIGNIFICANTLY ADVANCING THE STATE-OF-THE-ART FOR LES. THIS CRITICAL VALIDATION WILL PROVIDE THE FOUNDATION FOR PROCEEDING TO APPLICATION OF THIS INNOVATIVE METHODOLOGY IN SUPPORTING THE DESIGN AND OPTIMIZATION OF CONTROL CONCEPTS, E.G. CHEVRONS, BEVELS, ETC., AS WELL AS ULTIMATELY PERFORMING PREDICTIONS OF NOISE EMISSIONS FROM FULL-SCALE, REALISTIC NOZZLES WITH COMPLEX EXHAUST FLOWPATHS, AIRFRAME/PROPULSIVE JET INTERACTIONS, ETC.

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• $69,983 - Wednesday the 19th of October 2011
  Department Of Navy
  NAVAIR WARFARE CTR AIRCRAFT DIV LKE
  EXERCISE OPTION

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• $64,990 - Thursday the 22nd of March 2012
  Department Of Navy
  NAVAIR WARFARE CTR AIRCRAFT DIV LKE
  RESEARCH&DEVELOPMENT

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• $50,000 - Monday the 10th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE UNCERTAINTY QUANTIFICATION METHODS DEVELOPED UNDER THIS PROGRAM ARE DESIGNED FOR USE WITH CURRENT STATE-OF-THE-ART FLOW SOLVERS DEVELOPED BY AND IN USE AT NASA. THE PHASE I PROGRAM DEMONSTRATED THE CRISP CFDREG ERROR QUANTIFICATION AND REDUCTION CODE WITH SIMULATIONS CONDUCTED USING THE NASA UNSTRUCTURED SOLVERS FUN3D AND USM3D. PHASE I PROVIDED EVIDENCE SUPPORTING THE SUSPECTED NEED FOR AN ERROR PREDICTION CODE THAT MATCHES THE FINITE VOLUME SCHEME OF THE NAVIER-STOKES SOLVER ITSELF. PHASE II WILL CONTINUE THIS WORK BY EXPANDING OUR ERROR TRANSPORT EQUATION (ETE) SOLVER TO TREAT BOTH CLASSES OF UNSTRUCTURED GRID FINITE VOLUME SCHEMES. SUPPORT FOR THE CGNS STANDARD WILL BE IMPLEMENTED AND PERMIT USE OF THE PHASE II PRODUCT BY A BROADER SPECTRUM OF POTENTIAL USERS. SPECIFIC ISSUES THAT AFFECT NUMERICAL ACCURACY OF THE ERROR PREDICTIONS AND HOW THEY PROPAGATE INTO INTEGRATED QUANTITIES SUCH AS LIFT AND DRAG COEFFICIENTS WILL BE ADDRESSED. REDUCTION OF ERROR FOR LARGE SCALE MESHES IS A MATTER OF EQUAL IMPORTANCE, AND IMPROVEMENTS ARE PLANNED THAT WILL PROVIDE FOR ANISOTROPIC GRID REFINEMENT WITHIN THE EXISTING CRISP CFDREG MESH ADAPTATION CODE. FINALLY, ERROR QUANTIFICATION APPROACHES FOR TRANSIENT APPLICATIONS WILL BE EXPLORED TO EXPAND THESE DEVELOPMENTS TO PROBLEMS THAT INVOLVE INHERENT UNSTEADINESS AND/OR MOVING BOUNDARIES.

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