Award search
Awards for “PHYSICAL SCIENCES INC.”
25 awards on this page · sorted by amount · page 39
| Award ID | Recipient | Awarding agency | Amount | Start | End | NAICS | Description |
|---|---|---|---|---|---|---|---|
| HQ000610C7417 | PHYSICAL SCIENCES INC. | Department of Defense | $99.96K | 2010-07-05 | 2011-01-05 | 541712 | PH I RESEARCH & DEVELOPMENT |
| FA955009C0080 | PHYSICAL SCIENCES INC. | Department of Defense | $99.96K | 2008-11-15 | 2009-08-14 | 541712 | STTR (PHASE I) - DYNAMIC ROUGHNESS APPLIED TO BOUNDARY LAYER CONTROL |
| W911SR19C0008 | PHYSICAL SCIENCES INC. | Department of Defense | $99.96K | 2018-12-14 | 2019-05-20 | 541714 | SBIR PHASE I BASE PERIOD. PHYSICAL SCIENCES INC. |
| FA865011M2203 | PHYSICAL SCIENCES INC. | Department of Defense | $99.96K | 2012-04-27 | 2012-04-27 | 541711 | STTR PHASE I |
| NNX09CF62P | MAXION TECHNOLOGIES, INC. | National Aeronautics and Space Administration | $99.95K | 2009-01-22 | 2010-01-21 | 541712 | TUNABLE, NARROW LINE WIDTH MID-INFRARED LASER SOURCE MAXION TECHNOLOGIES, INC. (MAXION) AND PROFESSOR MARIO DAGENAIS AND HIS GROUP AT THE UNIVERSITY OF MARYLAND (UMD) JOINTLY PROPOSE TO DEVELOP A COMPACT, EFFICIENT, SINGLE MODE, NARROW LINEWIDTH TUNABLE LASER SOURCE IN THE 3.2 TO 3.6 MICRON WAVELENGTH REGION. THIS EFFORT, IF SUCCESSFUL, WILL ASSIST NASA IN ITS TRACE GAS DETECTION OBJECTIVES BY SUPPLYING NASA WITH THE MOST CRITICAL (AND DIFFICULT TO OBTAIN) LASER SOURCE REQUIRED. DURING THE PHASE 1 PORTION OF THIS EFFORT, MAXION AND UMD PROPOSE TO: A) DEVELOP/DEMONSTRATE A LOW-LOSS IC LASER DESIGN, B) DEVELOP ULTRA-LOW MODAL REFLECTIVITY ANTI-REFLECTION (AR) OUTPUT FACETS ON INTERBAND CASCADE LASER (ICL) GAIN CHIPS, AND C) VALIDATE THE AR COATING QUALITY BY DEMONSTRATING CONTINUOUS TUNING OF AN ECL USING THE HIGH TEMPERATURE, STATE-OF-THE-ART AR-COATED GAIN CHIP DEVELOPED DURING THIS PROGRAM. THE LOW-LOSS ICL DESIGN IS IMPORTANT TO IMPROVE THE MAXIMUM CW OPERATING TEMPERATURE OF IC LASERS, CURRENTLY LIMITED TO NEAR-ROOM-TEMPERATURE VALUES. THE ULTRA-LOW REFLECTIVITY COATING WILL PERMIT THE MAXIMUM POSSIBLE WAVELENGTH TUNING RANGE TO BE ACHIEVED. THIS IS IMPORTANT AS IT WILL REALIZE TUNABILITY THROUGHOUT THE WIDEST POSSIBLE RANGE (THE GOAL BEING 3.2-TO-3.6 MICRONS) USING A SINGLE SEMICONDUCTOR LASER CHIP. THE NEW LOW-LOSS IC DESIGN AND THE ULTRA-LOW REFLECTIVITY OUTPUT FACET REPRESENT, TOGETHER, THE TWO CENTRAL ROADBLOCKS MAXION SEES TO ACHIEVING A COMPACT, TUNABLE LASER SOURCE IN THE MID-INFRARED WAVELENGTH REGION. CONSEQUENTLY, THE PHASE I EFFORT WILL REPRESENT A FEASIBILITY STUDY TO SEE IF OUR APPROACHES TO OVERCOMING THESE TWO ROADBLOCKS CAN BE SUCCESSFUL. |
| W911SR13C0064 | PHYSICAL SCIENCES INC. | Department of Defense | $99.95K | 2013-09-10 | 2014-02-28 | 541712 | SBIR PHASE I PHYSICAL SCIENCES INC. |
| HQ014718C7431 | PHYSICAL SCIENCES INC. | Department of Defense | $99.95K | 2018-06-25 | 2019-06-24 | 541715 | SBIR/STTR PHASE I RESEARCH&DEVELOPMENT FOR LOW SWAP NUCLEAR MAGNECTIC RESONANCE GYROSCOPE |
| NNX08CA92P | PHYSICAL SCIENCES INC. | National Aeronautics and Space Administration | $99.95K | 2008-07-21 | 2008-07-21 | 541712 | A NEW PULSED ELECTRIC THRUSTER NAMED PULSED ELECTROGASDYNAMIC THRUSTER, FOR ATTITUDE CONTROL AND ORBIT MANEUVER IS PROPOSED. IN THIS THRUSTER PROPELLANT GAS IS INTRODUCED INTO THE THRUST NOZZLE THROUGH A FAST ACTING GAS VALVE. WHEN THE PROPELLANT GAS PARTIALLY FILLS THE THRUSTER NOZZLE IN 100~200 MICROSECOND A SHORT HIGH VOLTAGE PULSE IS APPLIED TO BREAK DOWN AND HEAT THE PROPELLANT GAS. THE TYPICAL DURATION OF THE PULSED DISCHARGE IS 10 MICROSECOND. THE HEATED PROPELLANT GAS EXPANDS THROUGH THE NOZZLE GENERATING A HIGH IMPULSE (-MN-S PER PULSE) AT A HIGH SPECIFIC THRUST (120 MICRO N-S/JOULE). THE SPECIFIC IMPULSE (ISP) WILL BE IN THE RANGE OF 1000~1400 SEC. THIS PROCESS CAN BE REPEATED AT A FREQUENCY WHICH SATISFIES THE SPACECRAFT THRUST REQUIREMENT. THE THRUST GENERATING MECHANISM OF THE PROPOSED THRUSTER IS GASDYNAMIC EXPANSION NOT MAGNETOHYDRODYNAMIC INTERACTION. THE PROPOSED THRUSTER IS DIFFERENT FROM THE CONVENTIONAL PULSED ELECTROTHERMAL THRUSTER IN THAT THE JOULE HEATING OF THE PROPELLANT TAKES PLACE AS THE PROPELLANT GAS EXPANDS THROUGH THE DIVERGENT NOZZLE THEREBY ELIMINATING THE HEAT AND MOMENTUM LOSSES AT THE NOZZLE THROAT. OUR OBJECTIVES ARE: (I) ESTABLISH PROOF OF CONCEPT; (II) DEVELOP AN ENGINEERING MODEL; AND (III) DEVELOP A PROTO-FLIGHT MODEL OF THE PROPOSED THRUSTER SYSTEM. |
| W911SR12C0004 | PHYSICAL SCIENCES INC. | Department of Defense | $99.95K | 2011-12-12 | 2012-06-12 | 541711 | INFRARED SIGNATURES - PH. I STTR |
| HQ014713C7409 | PHYSICAL SCIENCES INC. | Department of Defense | $99.95K | 2013-03-13 | 2013-09-14 | 541712 | PH I RESEARCH&DEVELOPMENT TITLED: INNOVATIVE FAST RUNNING POST INTERCEPT EO/IR SCENE GENERATOR IGF::OT::IGF |
| N0001408M0334 | PHYSICAL SCIENCES INC. | Department of Defense | $99.95K | 2008-06-24 | 2008-12-24 | 541712 | RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY) |
| W911NF08C0090 | PHYSICAL SCIENCES INC. | Department of Defense | $99.95K | 2008-07-18 | 2009-01-14 | 541712 | SCIENTIFIC RESEARCH SERVICES |
| INDN10PC20011 | PHYSICAL SCIENCES INC. | Department of the Interior | $99.94K | 2009-11-01 | 2010-05-15 | 541712 | SBIR 9.2 PHASE 1 ROBUST DISCRIMINATION OF HUMAN VS. ANIMAL FOOTSTEPS USING SEISMIC SIGNALS (7279-560) |
| HQ000608C7854 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2008-02-13 | 2008-08-12 | 541712 | CONTRACT SUMMARY REPORT. |
| FA865012M2250 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2012-03-21 | 2012-12-24 | 541711 | STTR 1: MOF BASED CATALYST FOR ELECTROCHEMICAL REDUCTION |
| W31P4Q18C0025 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2017-12-12 | 2018-09-12 | 541715 | IGF::OT::IGF ARMY SMALL BUSINESS INNOVATION RESEARCH PROGRAM (SBIR) PHASE I CONTRACT ACTION FOR STATEMENT OF WORK ENTITLED, "UTILIZING GROUND-BASED SIMULATION..." RA-T015-18 |
| W911SR07P0031 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2007-06-07 | 2008-04-08 | 541712 | BASIC EFFORT - SBIR PHASE I |
| W9113M11C0047 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2011-05-26 | 2011-11-25 | 541712 | ARMY SBIR PHASE 1(400 DPPH) |
| W15QKN12C0082 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2012-08-23 | 2013-05-19 | 541712 | PHASE I SBIR, PROPOSAL ENTITLED, "INNOVATIVE SYSTEMS FOR LARGE SCALE, LOW COST PRODUCTION OF HIGH QUALITY SILICON NANOPARTICLES." |
| W911SR10C0065 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2010-09-16 | 2011-03-15 | 541711 | PHASE I STTR ENTITLED" FULLY INTEGRATED SYSTEM FOR PATHOGEN CONCENTRATION AND DETECTION IN WATER SUPPLIES" |
| FA865010M1792 | PHYSICAL SCIENCES INC. | Department of Defense | $99.94K | 2010-03-09 | 2010-12-10 | 541712 | AIR-DELIVERABLE TUNNEL DETECTION SENSOR SUITE |
| HQ014715C7310 | PHYSICAL SCIENCES INC. | Department of Defense | $99.93K | 2015-04-28 | 2015-12-20 | 541712 | ::IGF::OT::IGF STTR PHASE I RESEARCH&DEVELOPMENT |
| W912HZ13P0023 | PHYSICAL SCIENCES INC. | Department of Defense | $99.93K | 2013-02-06 | 2013-09-26 | 541712 | U434ICA STTR PHASE I PROJECT |
| W911NF08C0078 | PHYSICAL SCIENCES INC. | Department of Defense | $99.93K | 2008-08-08 | 2009-02-04 | 541712 | SCIENTIFIC RESEARCH SERVICES |
| NNX09CC20P | PHYSICAL SCIENCES INC. | National Aeronautics and Space Administration | $99.93K | 2009-01-22 | 2009-07-22 | 541712 | NEXT GENERATION, UAV-CLASS OZONE PHOTOMETER PHYSICAL SCIENCES INC. PROPOSES TO DEVELOP A COMPACT, RUGGED, RAPID-RESPONSE, AUTONOMOUS SENSOR FOR IN-SITU MONITORING OF AMBIENT O3 FROM UAVS. OUR INNOVATION IS TO COMBINE NEWLY AVAILABLE UV LIGHT EMITTING DIODES (LEDS) WITH MINIATURIZED, LOW POWER, HIGH SENSITIVITY SIGNAL DETECTION ELECTRONICS TO CREATE A NEXT GENERATION, UAV-CLASS, PHOTOMETER FOR O3. THE ADVENT OF UV LEDS ENABLES THE DEVELOPMENT OF A VERY COMPACT AND HIGHLY SENSITIVE MONITOR FOR AMBIENT O3. AN LED-BASED SENSOR HAS MANY ADVANTAGES OVER CURRENTLY AVAILABLE TECHNOLOGIES AND IS HIGHLY SUITABLE FOR DEPLOYMENT IN UAVS. THE PHASE I PROGRAM WILL DEMONSTRATE THE FEASIBILITY OF A BREADBOARD SENSOR AND CREATE A DETAILED CONCEPTUAL PLAN FOR A FIELDABLE PROTOTYPE. THE TRL AT THE END OF PHASE I WILL BE LEVEL 4. THE PHASE II PROGRAM WILL FABRICATE A PROTOTYPE THAT CAN BE FIELD DEMONSTRATED ON AN AIRCRAFT. THE TRL AT THE END OF PHASE II WILL BE LEVEL 6. SUCCESSFUL COMPLETION OF PHASES I AND II WILL RESULT IN A RIGOROUSLY VALIDATED PROTOTYPE SENSOR THAT CAN MONITOR AMBIENT O3 WITH HIGH SPEED AND PRECISION. THE SENSOR ARCHITECTURE CAN BE EASILY MODIFIED TO MEASURE OTHER SPECIES. USING NEW MID-IR LEDS, THE PHOTOMETER CAN MONITOR TRACE GASES SUCH AS CO2 AND CO. |