The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $99,995 - Monday the 24th of October 2011
  Department Of Army
  W6QK ACC-RSA
  ARMY SMALL BUSINESS INAVATIVE RESEARCH (SBIR) PHASE I AWARD.

  ---

• $999,946 - Monday the 20th of April 2015
  Missile Defense Agency
  MISSILE DEFENSE AGENCY (MDA)
  STTR PHASE II RESEARCH AND DEVELOPMENT IGF::OT::IGF

  ---

• $50,000 - Monday the 7th of April 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  HISTORY HAS REPEATEDLY SHOWN THAT COMBUSTION INSTABILITY IS THE GREATEST TECHNICAL RISK FACED IN ANY CHEMICAL PROPULSION DEVELOPMENT PROGRAM. THE UCDS PROCESS ADDRESSES THIS ISSUE BY USING A RIGOROUS PHYSICS-BASED ANALYTICAL FRAMEWORK TO DECOMPOSE THE COMPLEX FLOW FIELD INSIDE A CHEMICAL PROPULSION DEVICE, SUCH AS A LIQUID OR SOLID ROCKET, IN A WAY THAT ALLOWS RAPID SIMULATION OF THE DYNAMIC BEHAVIOR. USING UCDS IT IS POSSIBLE TO GENERATE HIGH FIDELITY PREDICTIONS OF THE TIME EVOLUTION, AMPLITUDE AND WAVEFORM OF A PRESSURE OSCILLATION, ALONG WITH ANY CHANGES TO THE MEAN PROPERTIES DUE TO NON-LINEAR EFFECTS. FURTHERMORE, IT HAS BEEN SHOWN THAT THE MODAL ALPHA (LINEAR GROWTH RATE) IS A KEY PHYSICAL PARAMETER THAT DEFINES THE DYNAMIC BEHAVIOR OF A ROCKET AND PROVIDES A RELIABLE MEASURE OF COMBUSTION STABILITY MARGIN. BY MONITORING HOW THE ARRAY OF MODAL ALPHAS CHANGE WITH DESIGN OR OPERATIONAL FEATURES, THE EFFECTS ON ENGINE COMBUSTION STABILITY CAN BE PREDICTED. THIS INSIGHT PROVIDES THE MEANS TO ELIMINATE INSTABILITY WITHOUT RESORTING TO EXPENSIVE CUT-AND-TRY ITERATIVE DEVELOPMENTAL TESTING. GTL PROPOSES TO USE THIS DESIGN GUIDELINE AND THE UCDSTM PROCESS TO CREATE A CLEAN-SHEET DESIGN FOR A NEW LIQUID ROCKET THAT IS INHERENTLY STABLE AND COMPARE IT TO AN EXISTING ENGINE.

  ---

• $49,972 - Friday the 20th of July 2012
  Department Of Army
  W6QK ACC-RSA
  EXERCISE OPTION FOR "SMBF TECHNOLOGY"

  ---

• $499,312 - Monday the 25th of June 2012
  Department Of Army
  W6QK ACC-APG
  PERFORMANCE OF WORK IN ACCORDANCE WITH

  ---

• $362,000 - Monday the 14th of November 2011
  Department Of Air Force
  FA9300 AFTC PZR
  INCREMENTAL FUNDING SBIR II

  ---

• $200,000 - Monday the 7th of April 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  HISTORY HAS REPEATEDLY SHOWN THAT COMBUSTION INSTABILITY IS THE GREATEST TECHNICAL RISK FACED IN ANY CHEMICAL PROPULSION DEVELOPMENT PROGRAM. THE UCDS PROCESS ADDRESSES THIS ISSUE BY USING A RIGOROUS PHYSICS-BASED ANALYTICAL FRAMEWORK TO DECOMPOSE THE COMPLEX FLOW FIELD INSIDE A CHEMICAL PROPULSION DEVICE, SUCH AS A LIQUID OR SOLID ROCKET, IN A WAY THAT ALLOWS RAPID SIMULATION OF THE DYNAMIC BEHAVIOR. USING UCDS IT IS POSSIBLE TO GENERATE HIGH FIDELITY PREDICTIONS OF THE TIME EVOLUTION, AMPLITUDE AND WAVEFORM OF A PRESSURE OSCILLATION, ALONG WITH ANY CHANGES TO THE MEAN PROPERTIES DUE TO NON-LINEAR EFFECTS. FURTHERMORE, IT HAS BEEN SHOWN THAT THE MODAL ALPHA (LINEAR GROWTH RATE) IS A KEY PHYSICAL PARAMETER THAT DEFINES THE DYNAMIC BEHAVIOR OF A ROCKET AND PROVIDES A RELIABLE MEASURE OF COMBUSTION STABILITY MARGIN. BY MONITORING HOW THE ARRAY OF MODAL ALPHAS CHANGE WITH DESIGN OR OPERATIONAL FEATURES, THE EFFECTS ON ENGINE COMBUSTION STABILITY CAN BE PREDICTED. THIS INSIGHT PROVIDES THE MEANS TO ELIMINATE INSTABILITY WITHOUT RESORTING TO EXPENSIVE CUT-AND-TRY ITERATIVE DEVELOPMENTAL TESTING. GTL PROPOSES TO USE THIS DESIGN GUIDELINE AND THE UCDSTM PROCESS TO CREATE A CLEAN-SHEET DESIGN FOR A NEW LIQUID ROCKET THAT IS INHERENTLY STABLE AND COMPARE IT TO AN EXISTING ENGINE.

  ---

• $124,861 - Monday the 10th of June 2013
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE UCDS PROCESS IS THE RESULT OF 50 YEARS OF RESEARCH INTO COMBUSTION INSTABILITY BY THE WORLDS LEADING SCIENTISTS AND ENGINEERS. THE BREAKTHROUGHS THAT CREATED UCDS HAVE PROVIDED A SOLID ANALYTICAL FOUNDATION UPON WHICH TOOLS CAN BE DEVELOPED AND APPLIED. ONE OF THESE IS THE UCDS NONLINEAR TOOL, WHICH GTL HAS BEEN APPLYING WITH MUCH SUCCESS IN THE INVESTIGATIONS OF THE DYNAMICS OF SOLID ROCKETS, LIQUID ROCKETS AND TURBOJETS. IN THE PROPOSED EFFORT, GTL SHALL ENHANCE THIS TOOL IN PREPARATION FOR ITS APPLICATION TO SCRAMJETS AND RAMJETS BY INCORPORATING MEAN FLOW EFFECTS IN THE ACOUSTIC MODELS USED IN THE NONLINEAR ALGORITHMS. SINCE THE NONLINEAR DATA ANALYSIS TOOL (NDAT) SHARES THE SAME NONLINEAR ALGORITHM WITH THE UCDS NONLINEAR TOOL, THIS ENHANCEMENT SHALL ALSO IMPROVE THE ABILITY OF NDAT TO TRANSFORM NONLINEAR TEST DATA INTO LINEAR PARAMETERS. TAKING THIS TO THE NEXT STEP, GTL SHALL INCREASE THE FUNCTIONALITY OF NDAT BY IMPLEMENTING CHANGES TO THE ALGORITHM THAT ALLOW IT TO UTILIZE THE DATA FROM MULTIPLE PRESSURE TRANSDUCERS IN THE DATA ANALYSIS RATHER THAN RESTRICTING THE TOOL TO THE CURRENT SINGLE DATA CHANNEL. THIS WILL BE ACCOMPLISHED BY DEVELOPING ALGORITHM ROUTINES THAT USE THE RELATIVE LOCATION OF THE PRESSURE TRANSDUCERS AND THE INTERVENING ACOUSTIC ENVIRONMENT TO ACCOUNT FOR THE TEMPORAL AND PHASE RELATIONSHIPS BETWEEN THE DATA STREAMS. WHEN IMPLEMENTED, THESE CHANGES WILL ALLOW NDAT TO AUTOMATICALLY IDENTIFY THE ORIENTATION OF THE OSCILLATING MODES AND REDUCE THE NONLINEAR PRESSURE OSCILLATION DATA INTO A CLEAR AND CONCISE SET OF LINEAR PARAMETERS. THE LAST PART OF THE PHASE I EFFORT WILL BE TO EXAMINE THE ROLE OF NONLINEAR ENERGY DISSIPATION IN SCRAMJETS IN PREPARATION FOR FURTHER REFINEMENT IN THE PHASE II EFFORT.

  ---