The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $189,173 - Thursday the 17th of April 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  WE PROPOSE THE CONTINUATION OF OUR RESEARCH AND DEVELOPMENT OF A NITROUS OXIDE FUEL BLEND (NOFBXTM) SINGLE-STAGE-TO-ORBIT (SSTO) MONOPROPELLANT PROPULSION SYSTEM FOR FUTURE USE ON A MARS ASCENT VEHICLE (MAV) AS PART OF THE MARS SAMPLE RETURN (MSR) ARCHITECTURE. THIS LIQUID MONOPROPULSION SYSTEM ARCHITECTURE IS ALSO READILY SCALABLE TO ALTERNATIVE PLANETARY ASCENT VEHICLES (PAV'S) AND SAMPLE RETURN SYSTEMS. KEY AREAS OF OUR PROPOSED DEVELOPMENT AND DEMONSTRATION ARE IN THE NOZZLE MINIATURIZATION TO SUPPORT COMPACT VEHICLE PACKAGING INTO AN MSR VEHICLE AND USE OF A PASSIVE THRUST VECTOR CONTROL MECHANISM WITH THREE ENGINES TO AVOID THE NECESSITY OF A LOW TEMPERATURE GIMBAL MECHANISM.

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• $126,433 - Thursday the 17th of April 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  WE PROPOSE THE CONTINUATION OF OUR RESEARCH AND DEVELOPMENT OF A NITROUS OXIDE FUEL BLEND (NOFBXTM) SINGLE-STAGE-TO-ORBIT (SSTO) MONOPROPELLANT PROPULSION SYSTEM FOR FUTURE USE ON A MARS ASCENT VEHICLE (MAV) AS PART OF THE MARS SAMPLE RETURN (MSR) ARCHITECTURE. THIS LIQUID MONOPROPULSION SYSTEM ARCHITECTURE IS ALSO READILY SCALABLE TO ALTERNATIVE PLANETARY ASCENT VEHICLES (PAV'S) AND SAMPLE RETURN SYSTEMS. KEY AREAS OF OUR PROPOSED DEVELOPMENT AND DEMONSTRATION ARE IN THE NOZZLE MINIATURIZATION TO SUPPORT COMPACT VEHICLE PACKAGING INTO AN MSR VEHICLE AND USE OF A PASSIVE THRUST VECTOR CONTROL MECHANISM WITH THREE ENGINES TO AVOID THE NECESSITY OF A LOW TEMPERATURE GIMBAL MECHANISM.

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• $124,958 - Wednesday the 9th of January 2013
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  WE PROPOSE TO DEVELOP A MINIATURE, LOW RF NOISE IGNITION MODULE FOR NOFBX PROPULSION SYSTEMS. THIS IGNITION MODULE IS DESIGNED UTILIZING UNIQUE PROPERTIES OF THE NOFBX PROPELLANT TO ENABLE A POTENTIAL 2-3 ORDER MAGNITUDE REDUCTION IN SPARK IGNITION ENERGY, VOLTAGE, CURRENT, AND POWER UNDER A VERY SPECIAL SET OF CONDITION REALIZED ONLY IN AN NOFBX COMBUSTION CHAMBER.

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