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Award Data

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The Award database is continually updated throughout the year. As a result, data for FY24 is not expected to be complete until March, 2025.

Download all SBIR.gov award data either with award abstracts (290MB) or without award abstracts (65MB). A data dictionary and additional information is located on the Data Resource Page. Files are refreshed monthly.

The SBIR.gov award data files now contain the required fields to calculate award timeliness for individual awards or for an agency or branch. Additional information on calculating award timeliness is available on the Data Resource Page.

  1. A PRELIMINARY DESIGN AND ANALYSIS OF AN ADVANCED HEAT REJECTION SYSTEM FOR AN EXTREME ALTITUDE AVCD ENGINE INSTALLED IN A HAARP

    SBC: Dieseldyne Corpon            Topic: N/A

    THE PROPOSED STUDY WILL EVALUATE THE REQUIREMENTS FOR HEAT REJECTION FROM THE VARIOUS SYSTEMS OF AN ULTRA-HIGH ALTITUDEADVANCED VARIABLE CYCLE DIESEL INSTALLED IN A DERIVATIVE AIRFRAME SUITABLE FOR THE AMES ATMOSPHERIC SAMPLING MISSION. A COMBINATION OF CONVECTIVE AND RADIATION HEAT TRANSPORT SYSTEMS WILL BE EVALUATED AND THEN INCORPORATED INTO A DIESEL SIMULATOR CODE FOR PERFORMANCE EVALUATION. C ...

    SBIR Phase I 1990 National Aeronautics and Space Administration
  2. A SIMPLE AND VERSATILE METHOD FOR THE MEASUREMENT OF SURFACE TENSION

    SBC: H & N Instruments Inc            Topic: N/A

    SURFACE TENSION IS A FUNDAMENTAL PROPERTY OF ALL LIQUIDS. THE SURFACE TENSION OF LIQUIDS DURING PROCESSING AFFECTS THE PROPERTIES OF A VARIETY OF HIGH PERFORMANCE MATERIALS, I.E.: ALLOYS, CERAMICS, COMPOSITES, AND POLYCRYSTALLINE MATERIALS. SURFACE TENSION IS NOT ROUTINELY MEASURED FOR MOST EXPERIMENTAL NEW MATERIALS. THIS IS BECAUSE NO SIMPLE, ACCURATE, YET VERSATILE COMMERCIAL INSTRUMENT EXISTS. ...

    SBIR Phase II 1990 National Aeronautics and Space Administration
  3. RAPIDLY SOLIDIFIED NARROW TITANIUM ALUMINIDE STRIP

    SBC: Ribbon Technology Corpon            Topic: N/A

    NASA LEWIS RESEARCH CENTER HAS DEVELOPED AN ARC SPRAY PROCESS WHICH CAN FABRICATE LAMINATED TITANIUM ALUMINIDE COMPOSITES USING TITANIUM ALUMINIDE WIRE TO FORM THE MATRIX. THIS IS A SIGNIFICANT MATERIALS ADVANCE IN HIGH STRENGTH, HIGH TEMPERATURE PROPERTIES AT REDUCED WEIGHT. A MAJOR LIMITATION TO THE APPLICATION OF THIS PROCESS HAS BEENTHE BRITTLENESS OF CONVENTIONALLY FORMED TITANIUM ALUMINIDE W ...

    SBIR Phase I 1990 National Aeronautics and Space Administration
  4. PROCESS CONTROL FOR MELT OVERFLOW RAPID SOLIDIFICATION TECHNOLOGY

    SBC: Ribbon Technology Corpon            Topic: N/A

    A PROMISING NEW TECHNIQUE FOR DIRECT CASTING RAPIDLY SOLIDIFIED TITANIUM ALLOY RIBBONS FOR AIRFRAME HONEY COMB STRUCTURES WAS DEVELOPED BY RIBBON TECHNOLOGY CORPORATION (RIBTEC) WITH NASA SUPPORT. THE PLASMA MELT OVERFLOW PROCESS COMBINES TRANSFERRED PLASMA ARC SKULL MELTING TECHNIQUES AND MELT OVERFLOW RAPID SOLIDIFICATION TECHNOLOGY TO DIRECT CAST RIBBONS AND STRIP THAT ARE AMENABLE TO PROCESSIN ...

    SBIR Phase I 1990 National Aeronautics and Space Administration
  5. HIGH LIFT HEAT ACTUATED SOLID-VAPOR HEAT PUMP FOR SIMULTANEOUS REFRIGERATION AND WATER HEATING.

    SBC: Rocky Research            Topic: N/A

    THERE IS A NEED FOR REFRIGERATION AS WELL AS HOT WATER HEATING ON MANNED SPACECRAFT. IN ORDER TO OBTAIN ENERGY ANDMASS EFFICIENT EQUIPMENT, IT IS PROPOSED TO USE COORDINATIVECOMPLEX COMPOUNDS, A SPECIAL CLASS OF NON-TOXIC SOLID-VAPOR MEDIA, FOR A DUAL DUTY THERMODYNAMIC CYCLE WHICH PROVIDES SIMULTANEOUSLY REFRIGERATION AND HOT WATER HEATING. SUCH CYCLES CAN BE DRIVEN WITH RELATIVELY LOW TEMPERATUR ...

    SBIR Phase I 1990 National Aeronautics and Space Administration
  6. HIGH DENSITY CHEMICAL THERMAL STORAGE SYSTEM FOR LOW GRAVITY ENVIRONMENTS

    SBC: Rocky Research            Topic: N/A

    N/A

    SBIR Phase I 1990 National Aeronautics and Space Administration
  7. THE CHEMICAL KINETICS OF LOX/HYDROCARBON COMBUSTION

    SBC: Software & Engineering Associa            Topic: N/A

    ANALYTICAL METHODS AND COMPUTER SOFTWARE ARE TO BE DEVELOPED FOR CHARACTERIZING THE CHEMICAL KINETIC MECHANISMS THAT CONTROL LOX/HYDROCARBON COMBUSTION IN ROCKET ENGINES. CRITICAL AREAS OF TECHNOLOGY ARE TO BE IDENTIFIED. AN INNOVATIVE AND HIGHLY GENERAL METHOD WILL BEAPPLIED TO MODEL LOX/RP-1 COMBUSTION AS IT OCCURS IN GAS GENERATORS FOR PUMP FED ENGINES. THE METHOD WILL THEN BE EXTENDED TO MODEL ...

    SBIR Phase II 1990 National Aeronautics and Space Administration
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