The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $89,800 - Monday the 14th of May 2012
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  PRODUCTION OF TOOLING

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• $75,000 - Monday the 3rd of June 2013
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  ADVANCED LIQUID ROCKET PROPULSION SYSTEMS MUST ACHIEVE LONGER BURN TIMES WITHOUT PERFORMANCE DEGRADATION TO ALLOW THE LOWEST COST PER KILOGRAM ACCESS TO SPACE. ABLATIVE THRUST CHAMBERS HAVE AN EXTENSIVE HERITAGE AND ARE THE LOW COST APPROACH TO FABRICATING ROCKET THRUST CHAMBERS. HOWEVER, COMPOSITE ABLATIVE CHAMBERS ARE HEAVY AND SUFFER FROM EROSION THAT TYPICALLY LIMITS PERFORMANCE OF THE ENGINE IN TERMS OF BURN TIME AND EFFICIENCY/PERFORMANCE OF THE COMBUSTION. IN THE LAST DECADE, THERE HAS BEEN SIGNIFICANT INTEREST IN UTILIZING FIBER-REINFORCED CERAMIC COMPOSITES SUCH AS CARBON FIBER-REINFORCED SILICON CARBIDE (C/SIC) COMPOSITES. SUCH COMPOSITES HAVE DEMONSTRATED A LOW EROSION RATE IN BI-PROPELLANT LIQUID ROCKET THRUST CHAMBERS AT TEMPERATURES APPROACHING 4000F. HOWEVER INSERTION OF THESE MATERIALS HAVE BEEN LIMITED BY COMPLEXITIES ASSOCIATED WITH REQUIRED SYSTEM REDESIGN TO ACCOMMODATE A RADIATIVELY-COOLED CHAMBER AND UNPROVEN ATTACHMENT METHODS. BY INCORPORATING A CERAMIC COMPOSITE LINER WITHIN AN ABLATIVE THRUST CHAMBER IN CRITICAL AREAS THAT ARE SUBJECTED TO THE HIGHEST TEMPERATURES, A LOW EROSION, HIGH PERFORMANCE CHAMBER IS OBTAINED THAT ELIMINATES COSTS AND COMPLEXITIES THAT HAVE LIMITED THE INSERTION OF CERAMIC COMPOSITE THRUST CHAMBERS. THE PHASE II WILL BUILD ON THE SUCCESSFUL STATIC HOT FIRE TEST OF SUCH A THRUST CHAMBER THAT DEMONSTRATED MINIMAL EROSION TO DEMONSTRATE WEIGHT SAVINGS AND A REDUCTION IN FILM COOLING WITH RESPECT TO A COMPARABLE ABLATIVE ENGINE.

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• $72,050 - Wednesday the 1st of August 2012
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  HI-NICALON TYPE-S SIC/MI-SIC COMPOSITE PANELS END USER:DONGMING ZHU 3-5422 BLDG:106 RM:214

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• $50,000 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  DURABLE HIGH TEMPERATURE MATERIALS ARE REQUIRED FOR REUSABLE HYPERSONIC STRUCTURAL THERMAL PROTECTION SYSTEMS. IN PARTICULAR, TEMPERATURES EXCEEDING 2700 F, AND APPROACHING 3000 F, ARE TARGETED FOR CAPABLE STRUCTURAL MATERIALS THAT CAN SURVIVE STRESSES ON THE ORDER OF 10 KSI (70 MPA) FOR AT LEAST 100 HOURS IN AN OXIDIZING ENVIRONMENT. SUCH MATERIALS HAVE BEEN IDENTIFIED AS AN ENABLING MATERIAL FOR FUTURE HYPERSONIC VEHICLES AS THIS APPLICATION IS STRUCTURAL, A STRONG DEGREE OF DAMAGE TOLERANCE IS DESIRED, AND THUS CERAMIC MATRIX COMPOSITES ARE THE PRIMARY CHOICE DUE TO THE DESIRE FOR REDUCED WEIGHT, HIGH TEMPERATURE STRENGTH AND OXIDATION RESISTANCE. SILICON CARBIDE FIBER-REINFORCED SILICON CARBIDE MATRIX (SIC/SIC) COMPOSITES ARE BELIEVED TO BE THE MOST SUITABLE SOLUTION DUE TO MEETING THE REQUIREMENTS WITH THE LIMITATIONS OF CREEP AT THE HIGHEST TEMPERATURES/LOADS, AND OXIDATIVE ATTACK AT STRESSES THAT EXCEED THE MATERIALS PROPORTIONAL LIMIT. THE PROPOSED EFFORT WILL DEFINE THE TEMPERATURE-STRESS LIMIT OF SIC/SIC COMPOSITES, AND EXAMINE METHODS TO FURTHER EXTEND THIS LIMIT.

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• $326,179 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  SILICON CARBON AND GRAPHITE PRODUCTS - IT IS THE GOAL OF NASA S ENVIRONMENTALLY RESPONSIBLE AVIATION PROGRAM (ERA) TO CONTINUE WORK ON THE HIGH PRESSURE TURBINE VANE APPLICATION WITH SIC/SIC COMPOSITES PRODUCED BY THE COMBINED METHODS OF CVI AND SMI. THESE PARTICULAR PROCESSING METHODS YIELD COMPOSITES WITH THE REQUIRED FIBER VOLUME, CREEP RESISTANCE AND HIGH TEMPERATURE STRENGTH NEEDED FOR A HIGH PRESSURE TURBINE VANE APPLICATION.

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• $18,050 - Friday the 13th of April 2012
  National Aeronautics And Space Administration
  GLENN RESEARCH CENTER
  HI NICALON TYPE S COMPOSITE PANELS

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