The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $594,443 - Wednesday the 19th of December 2012
  National Aeronautics And Space Administration
  KENNEDY SPACE CENTER
  P-POD: POLY PICOSATELLITE ORBITAL DEPLOYERS FIVE YEAR IDIQ MODIFICATION 11 INCORPORATES TA9-010

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• $5,759 - Wednesday the 5th of September 2012
  Veterans Affairs Department
  NATIONAL CEMETERY ADMINISTRATION
  CATCH CANS/STANDS TO BE USED AS A COMPENENT OF THE IRRIGATION AUDIT KITS.

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• $517,141 - Wednesday the 19th of December 2012
  National Aeronautics And Space Administration
  KENNEDY SPACE CENTER
  P-POD: POLY PICOSATELLITE ORBITAL DEPLOYERS FIVE YEAR IDIQ MODIFICATION 14 INCORPORATE TASK ASSIGNMENT 9-012.

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• $378,288 - Wednesday the 19th of December 2012
  National Aeronautics And Space Administration
  KENNEDY SPACE CENTER
  P-POD: POLY PICOSATELLITE ORBITAL DEPLOYERS FIVE YEAR IDIQ MODIFICATION 16 INCORPORATES DELIVERY ORDER DO-002 (CRS- 2), DO-003 (CRS- 3), DO-005 (NROL-39), AND DO-006 (ORS3); EXTENDS THE PERIOD OF PERFORMANCE OF TA9-012; INCORPORATES TASK ASSIGNMENTS TA9-013&TA9-015; UPDATE KSC CLAUSE 52.242-90; AN ADMINISTRATIVE CORRECTION TO DO-006; AND ZERO-OB STP/NRO FUNDING.

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• $300,390 - Wednesday the 19th of December 2012
  National Aeronautics And Space Administration
  KENNEDY SPACE CENTER
  CONTRACTOR SHALL SUPPORT POLY PICOSATELLITE ORBITAL DEPLOYERS (PPOD) FIVE YEAR IDIQ CONTRACT PER SCHEDULE ENCLOSED. MODIFICATION 12 INCORPORATES TA9-011 AND DO 9-004 REV 4

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• $250,026 - Friday the 15th of January 2016
  National Aeronautics And Space Administration
  LANGLEY RESEARCH CENTER
  STATEMENT OF WORK FOR DEVELOPMENT OF THE INTEGRATED MODELING AND VERIFICATION OF HYBRID WING-BODY, LOW NOISE ESTOL AIRCRAFT RESEARCH OPPORTUNITIES IN AERONAUTICS - 2006(ROA-2006), NRA-NNH06ZEA001N-SSFW2 1.0 INTRODUCTION/BACKGROUND THIS EFFORT IS DIVIDED INTO TWO PHASES. PHASE I IS A 1-YEAR BASE PERIOD, AND PHASE II IS A 2-YEAR OPTION PERIOD. THE PURPOSE OF THIS EFFORT IS TO DEVELOP AND VALIDATE PREDICTIVE CAPABILITIES FOR THE DESIGN AND PERFORMANCE OF CRUISE EFFICIENT, SHORT TAKE-OFF AND LANDING (CESTOL)SUBSONIC AIRCRAFT, AND TO VALIDATE PREDICTIVE CAPABILITIES FOR AN ESTIMATE OF CESTOL AIRCRAFT NOISE DURING TAKEOFF AND LANDING. FOR PHASE I (I.E., YEAR 1 BASE PERIOD), THESE METHODOLOGIES WILL BE THEN BE USED TO ACHIEVE THE FINAL OBJECTIVE OF YEAR 1, WHICH IS TO SELECT AND FURTHER REFINE ONE CESTOL CONCEPT AND THEN TO COMPLETE A PRELIMINARY DESIGN OF A LARGE SCALE WIND TUNNEL MODEL AND TEST. FOR PHASE II (I.E., YEARS 2 AND 3 OPTION PERIOD), THE WIND TUNNEL DESIGN AND CONSTRUCTION IS TO BE COMPLETED IN YEAR 2, AND A LARGE SCALE WIND TUNNEL TEST IS TO BE COMPLETED IN YEAR 3. THE FINAL OBJECTIVE OF PHASE II IS THE DEVELOPMENT VERIFICATION OF PREDICTIVE CODES FOR THESE ADVANCED POWERED-LIFT CONCEPTS AND THE GENERATION OF AN OPEN COLLECTION OF WIND TUNNEL DATA THAT CAN BE USED BY MODELERS TO IMPROVE THE CAPABILITY OF MODELING THESE COMPLEX FLOWS. IT IS INTENDED THAT THE PHASE I AND PHASE II (IF OPTION IS EXERCISED) EFFORT WILL ADDRESS THE FOLLOWING TOPICS: LOW-SPEED AERODYNAMIC CHARACTERISTICS UP TO AND BEYOND MAXIMUM LIFT VIA A COMBINATION OF COMPUTATIONAL AND EXPERIMENTAL EFFORTS IN ORDER TO OBTAIN A MORE COMPLETE PICTURE OF THE FLOW PHYSICS. ACOUSTIC CHARACTERISTICS OF A LOW-NOISE HYBRID WING-BODY SYSTEM VIA EXPERIMENTAL EFFORTS AND NOISE SIGNATURE MODELING TO ANALYZE NOT JUST THE NOISE GENERATED BY THE VEHICLE, BUT ALSO TO ANALYZE THE NOISE FOOTPRINT AROUND THE AIRPORT DURING TAKEOFF AND LANDING. 2.0 SCOPE OF WORK PHASE I WILL CONDUCT A PRELIMINARY DESIGN STUDY TO DETERMINE THE HYBRID WING-BODY DESIGN TO BE ANALYZED IN PHASE II, INCLUDING POWERED LIFT AERODYNAMIC STUDIES, BOTH COMPUTATIONAL AND EXPERIMENTAL, TO BETTER UNDERSTAND OF THE FLOW PHYSICS ASSOCIATED WITH USING THE PROPULSION SYSTEM TO IMPROVE THE AIRCRAFT LIFTING CAPABILITY. PHASE II WILL EXPAND THE UNDERSTANDING OF THE PHYSICS OF THE FLOW FIELD ASSOCIATED WITH POWERED LIFT CONFIGURATIONS. THE DESIGN DETERMINED FROM PHASE I WILL BE THE FOCUS OF BOTH THE EXPERIMENTAL AND COMPUTATIONAL EFFORTS. THE PROPULSION MODELING WILL BE FOCUSED ON METHODS OF IMPROVING THE AERODYNAMIC PREDICTIVE CAPABILITIES. THE LARGE SCALE WIND TUNNEL MODEL EFFORT IN YEAR 2 WILL FOCUS ON FINALIZING THE WIND TUNNEL MODEL, ASSEMBLING THE TEST PLAN, AND SCHEDULING THE EXPERIMENT IN THE CHOSEN FACILITY. YEAR 3 FOR THE LARGE SCALE WIND TUNNEL MODEL EFFORT WILL FOCUS ON PERFORMING THE EXPERIMENTS, ANALYZING THE RESULTS, AND PREPARING THE RESULTS FOR RELEASE. PHASE II WILL CONCLUDE WITH THE RELEASE OF THE ENTIRE DATA (INCLUDING WIND TUNNEL GEOMETRIES, RESULTING DATA, COMPUTATIONAL GEOMETRY MODELS AND CFD CONFIGURATION FILES) TO NASA AND THE GENERAL RESEARCH COMMUNITY, IF POSSIBLE. THE CONTRACTOR SHALL NOT CONSIDER ANY DATA GENERATED FROM THIS EFFORT AS PROPRIETARY AND WILL RELEASE ALL OF THE DATA THAT IT IS LEGALLY ALLOWED TO RELEASE TO THE GENERAL RESEARCH COMMUNITY. NASA WILL ENSURE THAT AS MUCH OF THESE RESULTS AS POSSIBLE ARE ABLE TO BE RELEASED TO THE GENERAL RESEARCH COMMUNITY WITHOUT LEGAL RESTRICTION.

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• $25,000 - Monday the 24th of September 2012
  Department Of Air Force
  FA9401 AFNWC PZI
  BASE TEST-POD TASK

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• $194,000 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  ADVANCED MULTIDISCIPLINARY PHYSICS-BASED DESIGN AND ANALYSIS CAPABILITIES ARE REQUIRED TO PURSUE THE REVOLUTIONARY VEHICLE AND TECHNOLOGY CONCEPTS NEEDED TO MEET THE SUBSTANTIAL CHALLENGES FACING THE AEROSPACE COMMUNITY. AN AIRCRAFT'S SHAPE IS THE NATURAL STARTING POINT FOR PHYSICS-BASED MULTIDISCIPLINARY ANALYSIS AND OPTIMIZATION. ITS OUTER MOLD LINES AND STRUCTURAL LAYOUT ARE THE INTERFACE BETWEEN AERODYNAMICS, STRUCTURES, MASS PROPERTIES, AND ALL THE PHYSICS THAT IMPACT A VEHICLE'S PERFORMANCE. PARAMETRIC GEOMETRY TOOLS SUCH AS NASA'S VEHICLE SKETCH PAD (VSP) DESCRIBE AN AIRCRAFT S GEOMETRY BY USING THE TERMS MOST FAMILIAR TO DESIGNERS; THE PARAMETRIC APPROACH IS IDEALLY SUITED TO THE RAPID EXPLORATION PROCESS CHARACTERISTIC OF CONCEPTUAL DESIGN. PHOENIX INTEGRATION'S MODELCENTER IS A PREMIER MULTIDISCIPLINARY INTEGRATION TOOL WHICH FINDS POPULAR USE IN INDUSTRY AND NASA. THE DECISION MAKERS INVOLVED IN THE DESIGN OF THE NEXT GENERATIONS OF AIR VEHICLES NEED THE ABILITY TO SELECT AND VARY THE LEVEL OF ANALYSIS FIDELITY TO SUIT THE DECISION BEING MADE. UNFORTUNATELY, ANALYSIS FIDELITY IS OFTEN DICTATED BY THE AVAILABLE TOOLS. THIS LIMITATION FREQUENTLY STEMS FROM THE UNDERLYING GEOMETRY REPRESENTATION. IN THIS RESEARCH, WE PROPOSE TO EXTEND AND ENHANCE VSP SO THAT IT WILL BE CAPABLE OF INTEGRATING LOW, MID, AND HIGH-FIDELITY ANALYSES INTO THE DESIGN PROCESS IN A TRULY VARIABLE FIDELITY MANNER, ALL BASED ON A COMMON GEOMETRIC MODEL. VSP WILL BE SIGNIFICANTLY MODIFIED AND RE-DESIGNED TO BECOME MORE MODULAR AND EXTENDABLE, BETTER FACILITATING INTEGRATION WITH ANALYSIS TOOLS AND INTEGRATION ENVIRONMENTS SUCH AS PHOENIX INTEGRATION'S MODELCENTER. MODELCENTER WILL BECOME MORE INTELLIGENT ABOUT GEOMETRY AND THE SENSITIVITIES INHERENT TO DESIGN PROCESSES. VSP WILL BECOME MORE INTELLIGENT ABOUT GEOMETRY AND THE ROLE IT PLAYS IN PHYSICS-BASED ANALYSIS, HELPING TO COUPLE ANALYSES BY MAPPING SOLUTIONS BETWEEN MODELS. VSP WILL BECOME MORE FLEXIBLE, ALLOWING CUSTOM DEFINITION OF NEW PARAMETRIC COMPONENTS. VSP WILL BECOME BETTER CONNECTED TO HIGH-FIDELITY ANALYSIS, BUT ALSO BETTER CONNECTED TO LOW AND MID-FIDELITY ANALYSES. THIS WILL ENABLE VARIABLE FIDELITY DESIGN BASED ON A COMMON GEOMETRY MODEL. THESE COMBINED ADVANCES WILL RESULT IN A GEOMETRY ENGINE AND AN INTEGRATION FRAMEWORK WHICH ARE SIGNIFICANTLY MORE INTELLIGENT, MORE EXTENSIBLE, AND MORE CAPABLE THAT WHAT IS AVAILABLE TODAY. THESE TOOLS WILL ENABLE MULTI-FIDELITY AND MULTI-PHYSICS ANALYSIS EARLY IN THE DESIGN PROCESS WHEN FUNDAMENTAL DECISIONS ARE MADE. THIS IMPROVED DESIGN MODELING CAPABILITY WILL LEAD TO BETTER UNDERSTANDING OF THE ADVANCED TECHNOLOGIES AND CONCEPTS REQUIRED TO MEET THE CHALLENGES FACING THE AEROSPACE INDUSTRY.

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• $16,000 - Wednesday the 21st of December 2011
  Department Of Air Force
  FA9401 AFNWC PZI
  RECONFIGURABLE NANOSAT TECHNOLOGY TES

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• $132,544 - Wednesday the 19th of December 2012
  National Aeronautics And Space Administration
  KENNEDY SPACE CENTER
  MODIFICATION 17 INCORPORATES TA9-010 REV. 1 'APIC FY12'; TA9-014 'P-POD AND CUBESAT NANO LAUNCHER SUPPORT'; AND DO-005 REV 2.

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