The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $750,000 - Saturday the 1st of December 2012
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - RADIATION-COOLED, BIPROPELLANT THRUST CHAMBERS ARE BEING CONSIDERED FOR THE ASCENT/DESCENT ENGINES AND REACTION CONTROL SYSTEMS FOR NASA MISSIONS SUCH AS MARS SAMPLE RETURN AND ORION MPCV. CURRENTLY, IRIDIUM-LINED RHENIUM COMBUSTION CHAMBERS ARE THE STATE-OF-THE-ART FOR IN-SPACE ENGINES. NASA'S ADVANCED MATERIALS BIPROPELLANT ROCKET (AMBR) ENGINE, A 150-LBF IRIDIUM-RHENIUM CHAMBER PRODUCED BY PLASMA PROCESSES AND AEROJET, RECENTLY SET A HYDRAZINE SPECIFIC IMPULSE RECORD OF 333.5 SECONDS. TO WITHSTAND THE HIGH LOADS DURING TERRESTRIAL LAUNCH, RHENIUM CHAMBERS WITH IMPROVED MECHANICAL PROPERTIES ARE NEEDED. RECENT EL-FORMTM RESULTS HAVE SHOWN CONSIDERABLE PROMISE FOR IMPROVING THE MECHANICAL PROPERTIES OF RHENIUM BY PRODUCING A MULTI-LAYERED DEPOSIT COMPRISED OF A TAILORED MICROSTRUCTURE, I.E., ENGINEERED RE. DURING PHASE I, AN AMBR SIZE CHAMBER WAS PRODUCED TO DEMONSTRATE FORMATION OF THE ENGINEERED RE MATERIAL IN BOTH THE THROAT AND BARREL REGIONS. TENSILE TESTS SHOWED THE ENGINEERED RE MATERIAL HAD A YIELD STRENGTH GREATER THAN 40KSI AT ROOM TEMPERATURE. IN ADDITION, ENGINEERED RE DEPOSITS WERE PRODUCED ON MULTIPLE MANDRELS AT ONE TIME, I.E., MULTI-COMPONENT PROCESS DEMONSTRATION. DURING PHASE II, THE ENGINEERED RE PROCESSING TECHNIQUES WILL BE OPTIMIZED. DETAILED CHARACTERIZATION AND MECHANICAL PROPERTIES TEST WILL BE PERFORMED. OPTIMIZATION OF THE MULTI-COMPONENT FABRICATION TECHNIQUE WILL RESULT IN A 30% OR HIGHER REDUCTION IN CHAMBER FABRICATION COSTS. THE MOST PROMISING TECHNIQUES WILL BE SELECTED AND USED TO PRODUCE AN ENGINEERED RE AMBR SIZE COMBUSTION CHAMBER FOR TESTING AT AEROJET.

  ---

• $744,427 - Friday the 4th of March 2016
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - NON-TOXIC MONOPROPELLANTS HAVE BEEN DEVELOPED THAT PROVIDE BETTER PERFORMANCE THAN TOXIC HYDRAZINE. FORMULATIONS BASED ON HYDROXYLAMMONIUM NITRATE (HAN) HAVE SUPERIOR PERFORMANCE AS COMPARED TO HYDRAZINE WITH ISP (261 SECONDS, 12% GREATER), HIGHER DENSITY AND VOLUMETRIC IMPULSE (60% GREATER DENSITY-IMPULSE), LOWER MELTING POINT, AND MUCH LOWER TOXICITY (NO SELF CONTAINED BREATHING APPARATUS REQUIRED). HAN BASED MONOPROPELLANTS REQUIRE HIGHER CHAMBER TEMPERATURES (2083K VS 883K) TO COMBUST. CURRENT HYDRAZINE BASED COMBUSTION CHAMBER TECHNOLOGY (INCONEL OR NIOBIUM C103 AND SILICIDE COATING) AND CATALYST (SHELL 405) ARE INADEQUATE. HOWEVER, CURRENT STATE OF THE ART IRIDIUM LINED RHENIUM CHAMBERS AND INNOVATIVE NEW FOAM CATALYST WERE DEMONSTRATED IN PULSE AND 10 SECOND FIRINGS IN THE PHASE I. THE GOAL OF THE SBIR PROJECT IS DEVELOP AND TEST A FLIGHT WEIGHT THRUSTER FOR AN ENVIRONMENTALLY "GREEN" MONOPROPELLANT.

  ---

• $49,998 - Tuesday the 17th of April 2012
  Missile Defense Agency
  MISSILE DEFENSE AGENCY (MDA)
  PH I RESEARCH&DEVELOPMENT OPTION

  ---

• $45,001 - Tuesday the 15th of May 2012
  Department Of Navy
  OFFICE OF NAVAL RESEARCH
  RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)

  ---

• $149,860 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE DELETERIOUS EFFECTS OF LUNAR DUST, TYPICALLY LESS THAN 50 A M IN DIAMETER, HAVE TO BE ADDRESSED PRIOR TO ESTABLISHING A HUMAN BASE AND LONG DURATION HUMAN PRESENCE ON THE SURFACE OF THE MOON. THESE EFFECTS INCLUDE ABRASION OF SEALS, GASKETS, MOTORS, ACTUATORS, GIMBALS, BEARINGS, BLOCKING OF OPTICAL WINDOWS, AND COATING OF THERMAL CONTROL SURFACES AND SOLAR PANELS WITH LUNAR DUST. NEGATIVE PHYSIOLOGICAL EFFECTS DUE TO DUST INHALATION BY ASTRONAUTS MUST BE MITIGATED. ISSUES RELATED TO LUNAR DUST HAVE BEEN IDENTIFIED SINCE THE APOLLO MISSIONS; HOWEVER, NO CREDIBLE MITIGATION TECHNIQUES HAVE BEEN IMPLEMENTED TO DATE. THE ESSENCE OF THIS PROPOSED ACTIVITY IS TO DEVELOP A MULTI-USE COATING SYSTEM - A HIGHLY WEAR RESISTANT COATING SURFACE FOR USE IN THE SPACE ENVIRONMENT THAT CAN ALSO PERFORM AS PART OF AN ELECTRICALLY CONDUCTIVE CIRCUIT UPON DEMAND TO MINIMIZE WEAR SURFACE ABRASION AND, WHEN ELECTRICALLY ACTIVATED, REPEL FINE LUNAR DUST PARTICLES FROM WEAR SURFACES, SEALING SURFACES, AND COMPLEX GEOMETRIES.

  ---

• $120,475 - Friday the 17th of June 2016
  Department Of Navy
  OFFICE OF NAVAL RESEARCH
  RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)

  ---

• $12,000 - Friday the 11th of January 2013
  National Aeronautics And Space Administration
  MARSHALL SPACE FLIGHT CENTER
  IGF::OT::IGF NICRAIY-ZIRCONIA COATING OF FOUR (4) NOZZLE SKIRTS OWNED BY MSFC IN SUPPORT OF ER32.

  ---

• $1,000,000 - Monday the 20th of April 2015
  Missile Defense Agency
  MISSILE DEFENSE AGENCY (MDA)
  SBIR/STTR PHASE II RESEARCH&DEV.IGF::OT::IGF

  ---