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 - Thursday the 22nd of October 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - LARGE AMPLITUDE, UNSTEADY HEATING LOADS AND STEEP FLOW GRADIENTS PRODUCED IN REGIONS OF SHOCK-WAVE/TURBULENT BOUNDARY-LAYER INTERACTION (SWTBLI) POSE A SERIOUS AND CHALLENGING PROBLEM FOR DESIGNERS OF HYPERSONIC VEHICLES. CHARACTERIZING SWTBLI FLOW FEATURES, SUCH AS THE SIZE OF FLOW SEPARATION, IS IMPORTANT FOR DESIGN EVALUATION AND CFD VALIDATION. TAO SYSTEMS AND CUBRC PROPOSE TO DEVELOP A WIDE-BANDWIDTH, THIN-FILM HEAT TRANSFER SENSOR SYSTEM THAT QUANTIFIES THE HIGH FREQUENCY SWTBLI AT DUPLICATED FLIGHT CONDITIONS. THIS EFFORT COMBINES TAO SYSTEMS' HIGH FREQUENCY-RESPONSE/HIGH-SENSITIVITY ELECTRONICS AND SIGNAL PROCESSING TECHNIQUES WITH THE UNIQUE EXPERTISE OF CUBRC IN HIGH-SPEED, HIGH-ENTHALPY FLOWS TO OBTAIN SPATIOTEMPORAL INFORMATION FOR THE DEVELOPMENT OF PHYSICS-BASED TURBULENCE MODELS.

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• $750,000 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  IGF::OT::IGF OTHER FUNCTION - NEW AIRCRAFT DESIGNS DEPEND ON AN INTEGRATED ACTIVE APPROACH TO FLIGHT CONTROL, FLUTTER SUPPRESSION AND STRUCTURAL MODE ATTENUATION TO MEET DESIRED HANDLING QUALITY PERFORMANCE AND GUST LOAD ALLEVIATION. TAO SYSTEMS WILL TEAM WITH PROFESSOR GARY BALAS AT THE UNIVERSITY OF MINNESOTA TO (1) DEVELOP A ROBUST CONTROLLER THAT DEMONSTRATES IMPROVED AEROSTRUCTURAL PERFORMANCE OVER CURRENT STATE-OF-THE-ART TECHNIQUES BY UTILIZING A NOVEL AERODYNAMIC LOAD SENSOR, AND (2) PROVIDE A ROBUST LINEAR PARAMETER VARYING CONTROLLER THAT (A) REQUIRES NO AD HOC METHODS OF GAIN-SCHEDULING, (B) PROVIDES ROBUSTNESS GUARANTEES THAT MORE TRADITIONAL METHODS DO NOT OFFER, AND (C) ALLOWS FOR EXPLICIT RATE BOUNDS ENABLING LESS CONSERVATIVE, HIGHER PERFORMING CONTROLLER DESIGNS. THE BENEFITS INCLUDE IMPROVEMENT OF AERODYNAMIC AND STRUCTURAL EFFICIENCY USING ROBUST AEROSERVOELASTIC CONTROL METHODS OVER A RANGE OF FLIGHT SPEEDS, IN THE PRESENCE OF SIGNIFICANT TURBULENCE.

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• $266,914 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  ARMSTRONG FLIGHT RESEARCH CENTER
  IGF::OT::IGF OTHER FUNCTION: DISTRIBUTED AERODYNAMIC SENSING AND PROCESSING (DASP) TOOLBOX FOR THE NASA F/A-18A, TN853 AIRPLANE TAO OF SYSTEMS INTEGRATION INC. DEMONSTRATED THE FEASIBILITY, DEVELOPMENT, AND MATURATION TECHNOLOGIES FOR ADVANCED FLIGHT RESEARCH EXPERIMENTATION UNDER STTR PHASE II PURCHASE ORDER NUMBER NNX11CIO9P. THIS EFFORT IS TO DESIGN, BUILD AND VALIDATE A DISTRIBUTED AERODYNAMIC SENSING AND PROCESSING (DASP) TOOLBOX USING AERODYNAMIC `OBSERVABLE FOR FLIGHT RESEARCH AND DEVELOPMENT APPLICATIONS. THE SYSTEM WILL BE DESIGNED SPECIFICALLY FOR THE F/A-18 TN853 BASED ON PREVIOUS TEST PROGRAMS.

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• $125,000 - Friday the 6th of September 2013
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  FLIGHT CONTROL, STRUCTURAL RELIABILITY, AND EFFICIENCY DEPEND CRITICALLY ON THE ABILITY TO ASSESS THE TIME-ACCURATE UNSTEADY AERODYNAMIC LOADS AND MOMENTS FOR EACH LIFTING SURFACE UNDER NOMINAL AND ADVERSE FLOW CONDITIONS. TAO SYSTEMS AND CALIFORNIA INSTITUTE OF TECHNOLOGY PROPOSE TO DEVELOP A FLOW CONTROL SYSTEM THAT UTILIZES ADVANCED SENSORS AND A VORTICITY STATE ESTIMATOR (VSE) TO REACH FLOW STATES UNATTAINABLE WITHOUT CONTINUOUS CONTROL FEEDBACK. THE FLOW CONTROL SCHEME ENABLES MANIPULATION OF THE VORTICITY STATE TO ACHIEVE PERFORMANCE OBJECTIVES, SUCH AS SHORT TAKE-OFF/LANDING THROUGH CONTROLLED AERODYNAMIC LIFT AT ANGLES OF ATTACK NEAR STALL.

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• $100,000 - Saturday the 1st of December 2012
  National Aeronautics And Space Administration
  ARMSTRONG FLIGHT RESEARCH CENTER
  IGF::OT::IGF OTHER FUNCTIONS: WIND TUNNEL EXPERIMENTS SUPPORTING VORTICITY STATE ESTIMATION (VSE) IN SIMULATED GUSTING FLOW DEVELOPMENT OF MORE EFFICIENT SOFTWARE TOOLS FOR PREDICTING AND UNDERSTANDING THE RESPONSE OF AN AIRFRAME UNDER THE SIMULTANEOUS INFLUENCES OF STRUCTURAL DYNAMICS, THERMAL DYNAMICS, STEADY AND UNSTEADY AERODYNAMICS, AND THE CONTROL SYSTEM UNDER SBIR PHASE I PURCHASE ORDER NUMBER NNX11CD64. THIS EFFORT IS TO DESIGN, BUILD, AND INSTRUMENT A TWO-DIMENSIONAL WING MODEL FOR THE FEJER UNSTEADY FLOW WIND TUNNEL.

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