Federal Contractor Profile
Busek CO., INC.
$67M obligated·104 awards·2 agencies·4 NAICS
Federal Contracts
Showing award actions 51–100 of 123 funded award actions, most recent first.
- Contracts with positive obligations
- 104
- Funded award actions shown
- 123
- Obligations shown
- $67M
- Awarding agencies
- 2
This table shows award actions with a positive obligation. Zero-dollar and negative-dollar actions, such as administrative changes and deobligations, are not displayed. Multiple award actions may belong to the same contract.
Award data as of June 24, 2026. Source: USAspending federal award records.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Apr 1, 2020 | Department of DefenseFA8808 MIL SATELLITE COM SYS PKT LA | FA880820C0041 | 336415 | HALL EFFECT THRUSTER CAPABILITY STUDY | $4.7M |
| Mar 5, 2020 | Department of DefenseFA8649 USAF SBIR STTR CNTRCTNG AFRL | FA864920P0485 | 541715 | HIGH DENSITY PLASMA THRUSTER | $150K |
| Feb 28, 2020 | Department of DefenseFA9300 AFTC PZR | FA930020C0008 | 541715 | SPACE PROPULSION IN NEUTRALIZING SATELLITE THREATS - BEAM DIVERGENCE DEMONSTRATION | $1.0M |
| Jan 30, 2020 | Department of DefenseFA9300 AFTC PZR | FA930020C0004 | 541715 | RAPID GREEN THRUSTER TRANSITION(RGT2) | $500K |
| Dec 12, 2019 | Department of DefenseFA8649 USAF SBIR STTR CNTRCTNG AFRL | FA864920P0073 | 541715 | CRUISE MISSILE DETECTION AND EARLY WARNING SYSTEM | $50K |
| Oct 22, 2019 | Department of DefenseFA9300 AFTC PZR | FA930018C3001 | 541715 | ELECTRIC PROPULSION BEAM DIVERGENCE | $49K |
| Aug 19, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0350 | 541715 | IN PHASE 1, ONE OR TWO CANDIDATE WELDING TECHNOLOGIES WILL BE SELECTED AND TESTED IN BUSEK VACUUM CHAMBER. | $125K |
| Aug 19, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0439 | 541715 | BUSEK PROPOSES TO DEVELOP A VERSATILE, HIGH-IMPULSE PRECISION POINTING ATTITUDE-CONTROL ACTUATOR EVOLVED FROM NOW FLIGHT-PROVEN ELECTROSPRAY PROPULSION TECHNOLOGY. | $125K |
| Aug 14, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0222 | 541715 | LOW IMPULSE BIT ELECTROSPRAY THRUSTER CONTROL | $750K |
| Jul 11, 2019 | Department of DefenseFA9300 AFTC PZR | FA930018C3001 | 541715 | ELECTRIC PROPULSION BEAM DIVERGENCE | $950K |
| May 29, 2019 | Department of DefenseFA9300 AFTC PZR | FA930019C2006 | 541715 | MONOPROPELLANT THRUSTERS FOR CUBESATS EXECUTION - SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) FOLLOW-ON PHASE II | $747K |
| Mar 22, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019C9211 | 541715 | GEOSYNCHRONOUS ROAMING RECONNAISSANCE AND INSPECTOR SPACECRAFT | $1.5M |
| Feb 27, 2019 | Department of DefenseFA9300 AFTC PZR | FA930019P1001 | 541715 | LONG LIFETIME CATHODE AND IODINE FUELED ELECTRICITY - SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) PHASE I | $150K |
| Dec 14, 2018 | Department of DefenseFA9453 AFRL RVK | FA945319P0543 | 541715 | STANDARDIZED SCALABLE COMPONENTS AND STRUCTURES FOR ESPA CLASS AND BELOW | $150K |
| Sep 5, 2018 | Department of DefenseFA9300 AFTC PZR | FA930018C2001 | 541715 | IGF::OT::IGF SBIR PHASE II - INTEGRATED GREEN MONOPROPELLANT PROCESSING FOR HIGH POWER ELECTROSPRAY THRUSTERS | $750K |
| Aug 17, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865018P2131 | 541715 | IGF::OT::IGF SBIR I: BAA 18.1. INNOVATIVE ENGINE SOLUTIONS FOR UAVS | $150K |
| Aug 3, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2167 | 541715 | THE MAGNETIC TOPOGRAPHY IN HALL EFFECT THRUSTERS (HETS) PLAYS AN IMPORTANT ROLE IN FOCUSING THE ELECTRONS AND CONTROLLING THE PLASMA DISCHARGE WHICH IN TURNS GOVERNS THE THRUSTER PERFORMANCE. THE MAGNETIC CIRCUIT COMPONENTS CONSTITUTE MORE THAN HALF OF THE THRUSTER MASS. TO PRODUCE LOW-MASS THRUSTERS, THE DESIGN OF THE MAGNETIC CIRCUIT NEEDS TO BE OPTIMIZED. THE ADVANCED MAGNETIC ALLOY (AMA) IS THE MATERIAL OF CHOICE FOR THE FERROMAGNETIC PARTS OF AN HET'S MAGNETIC CIRCUIT. IN ADDITION TO ITS SUPERIOR MAGNETIC PROPERTIES, THE AMA IS ALSO THOUGHT TO BE COMPATIBLE WITH REACTIVE PROPELLANTS SUCH AS IODINE. CURRENTLY, TRADITIONAL MACHINING IS EMPLOYED TO FABRICATE THESE FERROMAGNETIC PARTS. THIS RESULTS IN REMOVAL OF NEARLY 80% OF THE EXPENSIVE BULK MATERIAL WHICH THEN GOES UNUSED. ADDITIONALLY, TRADITIONAL MACHINING CAN CAUSE UNWANTED DEFORMATION ON THIN PARTS, REDUCING THE PRODUCTION YIELD. IN PHASE I, BUSEK AND OAK RIDGE NATIONAL LABORATORY (ORNL) PROPOSE TO STUDY THE FEASIBILITY OF 3D PRINTING AMA MAGNETIC CIRCUIT COMPONENTS. OUR TEAM WILL CONSIDER SUITABLE ADDITIVE MANUFACTURING (AM) PROCESSES, INCLUDING EBEAM/LASER AM PROCESSES, AND A BINDERJET PROCESS WITH SUITABLE BINDERS. WE WILL EVALUATE TEST COUPONS PRINTED BY ORNL BY MEASURING THEIR RELEVANT MAGNETIC PROPERTIES AND COMPARING THEM TO THOSE MADE USING TRADITIONAL MACHINING METHODS. ADDITIONALLY, WE WILL APPLY RELEVANT HEAT TREATMENTS TO 3D PRINTED TEST COUPONS AND THEN REMEASURE THEIR MAGNETIC PROPERTIES. THE RESULTS WILL BE COMPARED TO THOSE MADE USING TRADITIONAL MACHINING METHODS THAT WERE SUBJECTED TO IDENTICAL HEAT TREATMENTS. BASED ON THE PHASE I RESULTS, THE BEST AM PROCESS WILL BE DOWN-SELECTED TO PRINT A MAGNETIC CIRCUIT COMPONENT FOR THE BUSEK 200W HET, WITH THE GOAL OF INTEGRATING IT INTO THE THRUSTER IN A POTENTIAL PHASE II PROGRAM. | $125K |
| Jul 31, 2018 | Department of DefenseFA9300 AFTC PZR | FA930018C3001 | 541715 | ELECTRIC PROPULSION BEAM DIVERGENCE | $1.2M |
| Jul 27, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2070 | 541715 | BUSEK PROPOSES TO DEVELOP A LOW-COST, LIGHTWEIGHT HALL EFFECT THRUSTER (HET) POWER PROCESSING UNIT (PPU) AT TARGETED 1KW/KG POWER DENSITY WITH MORE THAN 97% EFFICIENCY. THE PROPOSED PPU SOLUTION ADOPTS ADVANCED GAN POWER MOSFETS AND PCB BASED PLANAR MAGNETICS TECHNOLOGY TO ENABLE HIGH SWITCHING FREQUENCY OPERATION. REDUCED HEADCOUNT OF MAGNETICS, SEMICONDUCTORS AND ASSOCIATED DRIVER INTEGRATED CIRCUITS WILL ALLOW FOR SIGNIFICANT SIZE REDUCTION OF ALL PASSIVE COMPONENTS TO SUPPORT ULTRA-HIGH POWER DENSITY DESIGNS. THIS INNOVATION WILL FURTHER MINIATURIZE HET PPUS FROM TODAY S STATE-OF-ART BY AN ANTICIPATED 30% IN VOLUME AND MASS, WITH COST REDUCTIONS EXCEEDING 50% VERSUS SOA SOLUTIONS. | $125K |
| Jul 27, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2168 | 541715 | IODINE IS HIGHLY ATTRACTIVE AS AN ALTERNATE ELECTRIC PROPULSION PROPELLANT TO XENON. IT IS EASILY STORED IN A COMPACT VOLUME ON A SPACECRAFT AS A SOLID (GREATER THAN TWICE THE STORAGE DENSITY THAN PRESSURIZED XENON), WHICH NEGATES THE NEED FOR A LARGE PRESSURIZED TANK. THIS, COMBINED WITH ITS LOW COST AND LOWER IONIZATION ENERGY, MAKE IODINE AN IDEAL PROPELLANT FOR A SMALLSAT ELECTRIC THRUSTER SYSTEM. BUSEK CURRENTLY IS DEVELOPING A LINE OF GRIDDED RADIO-FREQUENCY (RF) ION THRUSTERS THAT UTILIZE IODINE AS A PROPELLANT. IN ADDITION TO THEIR SMALL SIZE, THE THRUSTERS ARE LOW POWER AND ARE COMPATIBLE WITH SOLID-STORABLE PROPELLANT IODINE. THIS MAKES THE BIT THRUSTER LINE A MISSION-ENABLING TECHNOLOGY FOR SITUATIONS WHERE VOLUME AND MASS ARE HIGHLY CONSTRAINED. THE CURRENT GENERATION OF BIT THRUSTERS USE THE BRFC-1, AN RF-ION CATHODE TO PROVIDE THE NEUTRALIZATION CURRENT. THE BRFC-1 CONSISTS OF A MINIATURIZED BIT-1 THRUSTER, MODIFIED TO EXTRACT ELECTRONS INSTEAD OF IONS. THIS CATHODE REALIZATION HAS THREE MAIN LIMITATIONS: POWER PROCESSING COMPLEXITY, FEED SYSTEM COMPLEXITY, AND REDUCED SYSTEM ISP (DUE TO THE NEED TO FLOW PROPELLANT TO THE CATHODE THAT DOES NOT GENERATE THRUST). WE PROPOSE TO DEVELOP A PHOTOCATHODE THAT WILL PRODUCE A CURRENT TO BOTH IGNITE AND NEUTRALIZE THE BUSEK LINE OF RF ION THRUSTERS THAT IS HIGHLY EFFICIENT AND IODINE COMPATIBLE. A PHOTOCATHODE EMITS ELECTRONS WHEN STRUCK BY AN INCIDENT LIGHT BEAM. THIS CATHODE, WHEN COMBINED WITH AN EFFICIENT UV LIGHT SOURCE, IS PREDICTED TO SIGNIFICANTLY DECREASE THE POWER REQUIREMENTS OF THE BIT THRUSTER LINE WHILE DRASTICALLY IMPROVING ISP DUE TO ITS PROPELLANTLESS OPERATION. THE PROPOSED WORK WILL MEASURE THE QUANTUM EFFICIENCY OF SPECIALLY-FABRICATED PHOTOCATHODES BEFORE AND AFTER IODINE EXPOSURE TO EVALUATE THEIR POTENTIAL AS AN RF THRUSTER NEUTRALIZER TECHNOLOGY. | $125K |
| Jul 27, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2213 | 541715 | BUSEK PROPOSES TO DEVELOP A NEW FORM OF PASSIVE ELECTROSPRAY THRUSTER CONTROL WHICH WILL ENABLE EXTREMELY FAST THRUSTER OPERATIONS AND THEREBY UNPRECEDENTED MINIMUM IMPULSE BITS. BUSEK S BET-300-P THRUSTER IS UNDER ACTIVE DEVELOPMENT AS A PRECISION REACTION CONTROL SYSTEM (RCS) WHICH WILL PROVIDE ORDERS OF MAGNITUDE IMPROVEMENTS OVER STATE-OF-THE-ART ALTERNATIVE ATTITUDE CONTROL SYSTEMS (ACS) FOR CUBESATS AND SMALL SPACECRAFT. THE LOW INERTIA OF CUBESATS COMBINED WITH VIBRATIONAL DISTURBANCES AND RESOLUTION LIMITATIONS OF STATE-OF-THE-ART ACS PRESENTLY LIMIT PRECISION BODY-POINTING AND POSITION CONTROL. BUSEK S ELECTROSPRAY THRUSTERS ABOARD THE ESA LISA PATHFINDER (NASA ST-7) SPACECRAFT, RECENTLY DEMONSTRATED CONTROL OF A PROOF MASS LOCATION TO WITHIN ~2NM PER ROOT HZ OVER A WIDE BAND. THE BET-300-P, ENHANCED BY EXPLOITATION OF ITS HIGH-SPEED DYNAMIC RESPONSE IN THIS PROGRAM, SEEKS TO EXTEND THAT SUCCESS TO SMALL SPACECRAFT PLATFORMS. | $125K |
| Jul 27, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2215 | 541715 | THE COMPACT HIGH PERFORMANCE PLASMA PROPULSION SYSTEM (CHPPPS) IS AN ELECTRIC PROPULSION SYSTEM FOR 12U 27U CUBESATS. CHPPS IS DESIGNED FOR HIGH-VALUE SCIENCE MISSIONS WHICH REQUIRE HIGH SPECIFIC IMPULSE, HIGH RELIABILITY, AND RADIATION TOLERANCE. CHPPPS INCLUDES A LOW POWER HALL EFFECT THRUSTER (HET), A HOLLOW CATHODE FOR NEUTRALIZING THE ION BEAM, A PROPELLANT MANAGEMENT SYSTEM, AND A POWER PROCESSING UNIT (PPU). THE SYSTEM IS HIGHLY MODULAR AND APPROPRIATE FOR 12U 27 U CUBESATS IN TERMS OF SIZE, MASS, AND POWER. CHPPPS MAY BE AS SMALL AS 4U, DEPENDING UPON THE FUEL LOAD AND SPECIFIC COMPONENT SELECTION. THRUST WILL BE 3-8 MN, DEPENDING ON THE POWER SUPPLIED (60 135 W) AND PEAK SPECIFIC IMPULSE WILL BE>1100 S. THE THRUSTER WILL BE FUELED WITH XENON OR WITH GAME-CHANGING IODINE, WHICH STORES AS A SOLID AT VERY LOW PRESSURE AND MUCH HIGHER DENSITY THAN XENON. THE USE OF IODINE SIGNIFICANTLY DECREASES SPACECRAFT DRY MASS, AND DRAMATICALLY DECREASES PROPELLANT VOLUME. THE IMPACT OF SWITCHING FROM XENON TO IODINE IS MOST SIGNIFICANT FOR VOLUME LIMITED SPACECRAFT LIKE CUBESATS. WHETHER THE THRUSTER IS FUELED BY XENON OR BY IODINE, THE ION BEAM WILL BE NEUTRALIZED BY A HOLLOW CATHODE FLOWING NOBLE GAS. THE THRUSTER WILL BE POWERED BY A COMPACT, RADIATION TOLERANT POWER PROCESSING UNIT (PPU) PREVIOUSLY DEVELOPED FOR NASA AND AIR FORCE APPLICATIONS. ACS MAY BE PROVIDED BY COLD GAS THRUSTERS FED FROM THE NOBLE GAS STORAGE SYSTEM. IN PHASE I, THE SYSTEM DESIGN WILL BE DETAILED AND STUDIED. WORK WILL INCLUDE A PROOF OF CONCEPT HARDWARE DEMONSTRATION AT RELEVANT POWER LEVELS. | $125K |
| Jul 25, 2018 | Department of DefenseFA9550 AFRL AFOSR | FA955018C0013 | 541715 | IGF::OT::IGF SBIR PHASE II - HIGH SPEED PLASMA PROBE AND ELECTRONICS SUITE PROGRAM: TEST SCIENCE FOR TEST AND EVALUATION (T&E) | $750K |
| May 9, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0051 | 541715 | IN COOPERATION WITH ROCCOR LLC, BUSEK SEEKS TO DEVELOP THRUSTER HEADS INTEGRATED WITH DEPLOYABLE BOOMS. THE HIGH RESOLUTION, LOW QUIESCENCE AND EXTREME THROTTLING CAPABILITIES OF BUSEK ELECTROSPRAY PROPULSION, COMBINED WITH THE CUSTOMIZABLE MOMENT ARMS AFFORDED BY ROCCORS COMPACT DEPLOYABLES WILL ENSURE THE SYSTEM IS APPLICABLE TO A WIDE VARIETY OF MISSION CONCEPTS. A PRELIMINARY PERFORMANCE MAP WAS OBTAINED FOR THE BET-1MN THRUSTER, DEMONSTRATING HUNDREDS OF N S OF THRUST FROM A SINGLE EMITTER. TIME OF FLIGHT MEASUREMENTS INDICATED MIXED MODE OPERATION (DROPLETS/IONS), INDICATING THAT UPDATED THRUST CONTROL ALGORITHMS MAY BE NECESSARY, AS PRESENT IMPLEMENTATIONS FOCUS ON DROPLET OR ION DOMINATED EMISSION. THRUST MODULATIONS WERE DEMONSTRATED VIA CONTROL OF FLOW RATE AND BEAM VOLTAGE, DEMONSTRATING DEEP THROTTLING AND OPERATION OVER A WIDE RANGE OF CONDITIONS. SIZE, WEIGHT, AND POWER (SWAP) FOR TWO INTEGRATED BET-1MN THRUSTER SYSTEMS WERE PROVIDED TO THE ROCCOR LLC AND USED TO DEVELOP REQUIREMENTS FOR THE BOOM. A NOTIONAL 2M DEPLOYABLE BOOM DESIGN WAS DEVELOPED AND STATIC LOAD MODELING PERFORMED TO IDENTIFY DEFLECTION. UNDER THE PHASE II EFFORT, BUSEK SHALL UPDATE TEST SETUPS TO INCLUDE IN-SITU MASS FLOW MEASUREMENT DURING DIRECT THRUST MEASUREMENT IN ORDER TO FULLY ASSESS THRUSTER PERFORMANCE. ADDITIONAL THRUSTER CHARACTERIZATION SHALL FOCUS ON COMPLETING PARAMETERIZED THRUSTER PERFORMANCE WHILE ALSO MEASURING THRUST NOISE, STABILITY, AND CAPTURING ELECTROSPRAY PLUME SWEEPS. UPDATED THRUST CONTROL ALGORITHMS WILL BE IMPLEMENTED IN HARDWARE/FIRMWARE AND COMMANDED THRUST CONTROL DEMONSTRATED AS PART OF AN INTEGRATED TEST WITH THE BET-1MN THRUSTER. DEPLOYABLE BOOM REQUIREMENTS WILL BE UPDATED AND A PROTOTYPE BOOM FABRICATED AND TESTED. STATIC LOAD TESTING WILL BE PERFORMED TO VALIDATE PHASE I MODELING RESULTS. | $750K |
| May 7, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0052 | 541715 | BUSEK PROPOSES TO DEVELOP A HIGHLY MODULAR ATTITUDE CONTROL SYSTEM (ACS) WHICH WILL PROVIDE ORDERS OF MAGNITUDE IMPROVEMENTS OVER STATE-OF-THE-ART ALTERNATIVE ACS FOR CUBESATS. THE LOW INERTIA OF CUBESATS COMBINED WITH VIBRATIONAL DISTURBANCES AND RESOLUTION LIMITATIONS OF STATE-OF-THE-ART ACS PRESENTLY LIMIT BODY-POINTING AND POSITION CONTROL ACCURACY. BUSEK S ELECTROSPRAY THRUSTERS ABOARD THE ESA LISA PATHFINDER SPACECRAFT RECENTLY DEMONSTRATED PRECISION CONTROL AT NM SCALES; THIS WORK EXTENDS THAT SUCCESS TO CUBESAT PLATFORMS. PASSIVELY FED ELECTROSPRAY THRUSTERS ARE HIGHLY COMPACT, INCLUDING FULLY INTEGRATED PROPELLANT SUPPLIES, AND ARE CAPABLE OF ~100NN THRUST CONTROL AT 10 S OF NN NOISE. THRUST CAN BE THROTTLED OVER>30X, TO A SCALABLE MAXIMUM OF 10 S OF UN. THESE TRAITS, COMBINED WITH>900S ISP ENABLE THESE SYSTEMS TO REPLACE TRADITIONAL REACTION WHEEL ACS; IMPROVING POINTING ERROR FROM ARCSECS TO 10 S OF MILLIARCSEC. THIS WORK ADDRESSES CRITICAL DEVELOPMENT GAPS, IN BOTH THRUSTER-HEADS AND A MULTI-AXIS POWER PROCESSING UNIT, PRESENTLY GATING THE TECHNOLOGY. PHASE I ESTABLISHED A THOROUGH BASELINE DATASET, WHICH CONFIRMED CRITICAL PERFORMANCE METRICS, AND ESTABLISHED DEVELOPMENT GAPS. PHASE II WILL EMPHASIZE TOTAL IMPULSE GOALS AND THRUSTER SYSTEM MATURATION. TASK 1 WILL EXECUTE DESIGN MODIFICATIONS DEVELOPED IN PHASE I AND AUGMENT EXISTING TEST CAPABILITIES. TASK 2 WILL IDENTIFY AND ADDRESS IMPULSE LIMITING MECHANISMS. TASK 3 WILL DEVELOP AND VALIDATE SOLUTIONS TO KNOWN MECHANICAL RISKS AND INCORPORATE EVOLVED REQUIREMENTS INTO A LOW-MASS ENGINEERING-MODEL THRUSTER MODULE. TASK 4 WILL FOCUS ON POWER PROCESSING DEVELOPMENT, TARGETING A CONTROL ARCHITECTURE WHICH MAXIMIZES THE PRECISION CONTROL CAPABILITIES OF THE TECHNOLOGY AND SERVES MULTIPLE THRUSTER HEADS. THESE EFFORTS WILL CONVERGE IN TASK 5 WHERE ENGINEERING MODEL THRUSTER PERFORMANCE WILL BE RIGOROUSLY EVALUATED OVER A COMPLETE LIFE DEMONSTRATION. | $750K |
| Apr 10, 2018 | Department of DefenseFA9300 AFTC PZR | FA930012C3000 | 541712 | IGF::OT::IGF SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) PHASE III - SPACE PLASMA CHARACTERIZATION SOURCE (SPCS) | $200K |
| Feb 20, 2018 | Department of DefenseFA9300 AFTC PZR | FA930014C3000 | 541712 | IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT | $50K |
| Sep 30, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CC90C | 541712 | IGF::OT::IGF BUSEK, IN PARTNERSHIP WITH MOREHEAD STATE UNIVERSITY (MSU), PROPOSES TO DEVELOP A VERSATILE 6U CUBESAT CAPABLE OF REACHING A LUNAR ORBIT FROM GEO. THE PRIMARY OBJECTIVE OF THE PHASE II EFFORT IS TO DEMONSTRATE A COMPLETE, MINI ION PROPULSION SYSTEM THAT PROVIDES ~3000SEC ISP HERETOFORE UNAVAILABLE TO CUBESATS, WITH A SOLID-STORABLE IODINE PROPELLANT. THIS TYPE OF PROPULSION TECHNOLOGY WOULD BE A HUGE MISSION ENABLER AND IDEAL FOR VOLUME-LIMITED SATELLITES SUCH AS CUBESATS. THE 6U BUS, COMBINED WITH ION PROPULSION, HAS ALREADY SHOWN BEING HIGHLY ATTRACTIVE TO SCIENCE PAYLOAD DEVELOPERS TARGETING THE UPCOMING SLS/EM-1 LUNAR MISSION. DURING PHASE I BUSEK SUCCESSFULLY DEMONSTRATED THE WORLD'S FIRST IODINE-FUELED GRIDDED ION THRUSTER BIT-3. KEY PERFORMANCE CHARACTERISTICS OF BIT-3 INCLUDE A COMPACT DESIGN ENVELOPE (<2U VOLUME), NOMINAL 60W CONSUMPTION, HIGHLY-THROTTLEABLE THRUST OF ~1.4MN, AND ISP UP TO 3200SEC (NEARLY IDENTICAL AS WITH XENON). BIT-3 HAS A UNIQUE ADVANTAGE OF BEING IODINE-COMPATIBLE DUE TO ITS PLASMA GENERATION MECHANISM AND CONSTRUCTION MATERIAL. THE ABILITY TO USE IODINE AS PROPELLANT IS A TRUE GAMECHANGER FOR CUBESAT PROPULSION, BECAUSE IODINE CAN BE STORED AS A DENSE SOLID (AT 4.9G/CC) AND ITS SUB- TORR STORAGE PRESSURE ENABLES VERY LIGHTWEIGHT, EVEN PLASTIC TANKS. WITH A MERE 300CC IODINE TANK ONBOARD, THE BIT-3 THRUSTER IS CAPABLE OF PROVIDING>2.8KM/S DELTA-V TO A 6U/12KG CUBESAT. THE ULTIMATE GOAL OF THE LUNARCUBE PROGRAM IS TO UNDERTAKE A MISSION TO THE MOON FROM GEO OR A TRANSLUNAR TRAJECTORY (SUCH AS THE EM-1 DROP-OFF) THAT WOULD DEMONSTRATE THE PROPULSION SYSTEM, AND CARRY OUT A LUNAR SCIENCE PROGRAM AS A CAPABILITY DEMONSTRATION OF THE PLATFORM. DURING THIS MISSION, A RELATED GOAL IS TO DEMONSTRATE THAT MUCH OF THE SPACECRAFT'S MINIATURE ELECTRONICS, PRIMARILY C&DH, COMMUNICATIONS, AND THE PROPULSION SYSTEM'S PPU CAN BE BASED ON LOW COST COMPONENTS AND SURVIVE THE HARSH DEEP-SPACE ENVIRONMENT. | $500K |
| Sep 30, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC17C0079 | 541712 | IGF::OT::IGF IN THIS CCRPP PROGRAM, BUSEK PROPOSES TO PERFORM A QUALIFICATION LIFE TEST ON A HIGH POWER HALL EFFECT THRUSTERS (HET) AND CENTER MOUNTED HOLLOW CATHODE ASSEMBLY (HCA). THE EFFORT BUILDS UPON A NASA PHASE 2 SBIR UNDER CONTRACT NUMBER NNX14CC24C. SPACE SYSTEMS/LORAL, LLC (SSL) IS BOTH THE COMMERCIALIZATIONPARTNER AND THE INVESTOR INTO THE CCRPP PROGRAM. AN ENGINEERING MODEL THRUSTER AND CATHODE WAS BUILT AND PERFORMANCE TESTED AND WILL BE ENTERING A QUALIFICATION PROGRAM IN 3RD QUARTER OF CY 2017. THE THRUSTER QUALIFICATION PROGRAM INCLUDES BUILDING TWO EQM THRUSTERS. ONE UNIT WILL UNDERGO PERFORMANCE, ENVIRONMENTAL TESTING (MODAL, RANDOM AND SINUSOIDAL VIBRATION AND SHOCK) AND TVAC. THE SECOND UNIT WILL UNDERGO LIFE AND CYCLE TESTING WHICH IS THE ONLY TASK IN THE THRUSTER QUALIFICATION PROGRAM BEING PROPOSED WITH CCRPP MATCHING FUNDS. THIS TESTING IS SCHEDULED TO BEGIN IN THE 4TH QUARTER OF CY 2018. SSL LEADS THE WORLD IN THE NUMBER OF SATELLITES FLYING HALL THRUSTERS. TO DATE THEIR PREFERRED SUPPLIER HAS BEEN OKB FAKEL OF RUSSIA. BUSEK S DEVELOPMENT AND COMMERCIAL SUPPLY FOR SSL, SIGNIFICANTLY STRENGTHENS THE US INDUSTRIAL BASE FOR MULTI-KILOWATT HALL THRUSTERS, WHILE ALSO PROVIDING NASA AND THE DOD A HIGH-PERFORMANCENEXT GENERATION DESIGN IN THE MULTI-KW POWER RANGE. THE PRIMARY NEAR TERM NASA APPLICATION OF THE THRUSTER IS THE PSYCHE MISSION, WHICH IS CURRENTLY PLANNED TO EMPLOY SPT-140 THRUSTERS. INITIAL PERFORMANCE DATA OF THE BHT-5000 INDICATES SIGNIFICANT ADVANCEMENT OVER PSYCHE S PRESENT THRUSTER TECHNOLOGY AND ARE STRONG REASONS TO CONSIDER THE BUSEK THRUSTER AS A REPLACEMENT FOR THE SPT-140. BUSEK S THRUSTER WILL BE THE WORLD S ONLY COMMERCIALLY AVAILABLE THRUSTER WITH AN INTERNAL CATHODE, LOCATED ON THE THRUSTER S CENTRAL AXIS. JPL RECOGNIZES THIS ARCHITECTURE PROVIDES SIGNIFICANT BENEFITS TO THE THRUSTER PERFORMANCE AND PROVIDED A LETTER OF SUPPORT RECOMMENDING THE USE OF CCRPP MATCHING FUNDS TO DEMONSTRATE THRUSTER LIFE. | $465K |
| Sep 27, 2017 | Department of DefenseNAVAL INFORMATION WARFARE SYSTEMS | N0003917C0004 | 541712 | IGF::OT::IGF = OTHER FUNCTION; SEACUBE OCEAN ALTIMETER FOR CUBESATS | $2.9M |
| Sep 26, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC17C0091 | 541712 | IGF::OT::IGF | $250K |
| Sep 15, 2017 | Department of DefenseFA9300 AFTC PZR | FA930017C2003 | 541712 | IGF::OT::IGF - AWARD OF FUEL FLEXIBLE HALL THRUSTER FOR MULTI-MODE PROPULSION SYSTEMS SBIR PHASE II EFFORT | $187K |
| Sep 13, 2017 | Department of DefenseFA9300 AFTC PZR | FA930014C3000 | 541712 | IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT | $185K |
| Sep 11, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC15CA06C | 541712 | THE DEVELOPMENT OF CRITICAL COMPONENTS FOR 600W IODINE HALL PROPULSION SYSTEM IS A SBIR PHASE III FOLLOW-ON TO WORK COMPLETED UNDER SBIR PHASE I CONTRACT NNX12CD99P AND SBIR PHASE II CONTRACT NNX13CC82C. IGF::OT::IGF | $198K |
| Aug 24, 2017 | Department of DefenseW6QK ACC-APG DURHAM | W911NF17P0044 | 541712 | IGF::OT::IGF NEW DARPA SBIR PHASE I CONTRACT; PROPOSAL TITLED, A LOW WORK FUNCTION THERMIONIC CONVERSION ELECTRODE FOR SPACE POWER GENERATION. SOLICITATION: DARPA 17.1 SBIR. | $100K |
| Aug 3, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017P9222 | 541712 | IGF::OT::IGF GEOSYNCHRONOUS ROAMING RECONNAISSANCE AND INSPECTOR SPACECRA | $150K |
| Jul 31, 2017 | Department of DefenseFA9300 AFTC PZR | FA930014C3000 | 541712 | IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT | $100K |
| Jun 9, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CP31P | 541712 | IGF::OT::IGF THE PROPOSED INNOVATION IS A LONG LIFETIME, COMPACT HOLLOW CATHODE THAT CAN BE MOUNTED ALONG THE AXIS OF A 600 W-CLASS HALL EFFECT THRUSTER. TESTING AT KILOWATT POWER LEVELS AND ABOVE HAS SHOWN THAT THE THRUSTER AXIS IS THE OPTIMAL POSITION FOR THRUSTER THROTTLING AND PLUME DIVERGENCE. IT ALSO MINIMIZES THE IMPACT OF BACKGROUND CONDITIONS UPON GROUND BASED PERFORMANCE MEASUREMENTS, REDUCING PROGRAMMATIC AND TECHNICAL RISK TO THE END USER. THE PROPOSED COMPACT CATHODE WILL EXTEND THESE BENEFITS TO LOW POWER HALL THRUSTERS. THE CATHODE WILL BE COMPATIBLE WITH IODINE AS WELL AS WITH NOBLE GASES. HOLLOW CATHODES ARE A CRITICAL, LIFE-LIMITING COMPONENT FOR HALL EFFECT THRUSTERS AND GRIDDED ION ENGINES. FAILURE MECHANISMS INCLUDE DEGRADATION, POISONING AND EVAPORATION OF THE ELECTRON EMITTER, KEEPER AND EMITTER TUBE ORIFICE EROSION, AND HEATER FAILURE. TO ACHIEVE>10,000 HR LIFETIME, COMPACT CATHODE WILL USE A HEXABORIDE (LAB6 OR CEB6) ELECTRON EMITTER. HEXABORIDES DEGRADE MORE SLOWLY THAN STATE-OF-THE-ART BARIUM OXIDE IMPREGNATED TUNGSTEN EMITTERS AT EQUIVALENT CURRENT DENSITIES. HEXABORIDES ARE ALSO RESISTANT TO CONTAMINATION FROM OXYGEN AND OTHER IMPURITIES. THE CATHODE ALSO INCLUDES A NEW, HIGH TEMPERATURE HEATER. TO MINIMIZE KEEPER AND ORIFICE EROSION, THE DESIGN WILL BE OPTIMIZED THROUGH TESTING AND PLASMA MEASUREMENTS. IN PHASE I, BUSEK SHALL DESIGN, BUILT AND TEST THE COMPACT CATHODE. THE PLASMA PLUME WILL BE INTERROGATED WITH AN EMISSIVE PROBE TO DETERMINE SPOT AND PLUME MODE OPERATING REGIMES ON XENON AND IODINE. AN INTEGRATED CATHODE-THRUSTER TEST WILL ALSO BE PERFORMED TO DETERMINE THE CATHODE'S PERFORMANCE WITH A THRUSTER. THE PHASE II TEST PROGRAM WILL INCLUDE DURATION TESTING OF THE CATHODE AND THRUSTER-CATHODE SYSTEM WITH A FULLY MODIFIED BHT-600, THERMAL CYCLING AND PLASMA MODELING. AT THE END OF PHASE II A CATHODE WILL BE DELIVERED TO NASA FOR TESTING WITH A 600W-CLASS HALL THRUSTER. | $125K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM20P | 541712 | IGF::OT::IGF GROWING SCIENTIFIC AND PRACTICAL NEEDS EXIST FOR PRECISION SPACECRAFT POINTING AT MILLIARCSEC (MAS) LEVELS. PRESENT STATE-OF-THE-ART REACTION WHEELS, OR SIMILAR, ACTUATORS INTRODUCE VIBRATIONAL JITTER AND CAN ULTIMATELY DRIVE POINTING ERROR. BUSEK ELECTROSPRAY THRUSTERS ABOARD THE ESA LISA PATHFINDER MISSION HAVE RECENTLY DEMONSTRATED NM SCALE POSITION CONTROL. THE PROPOSED SYSTEM WILL PROVIDE VIBRATION-FREE SUB-MAS POINTING CONTROL THROUGH INTEGRATION OF FOLLOW-ON INNOVATIONS AND NEW DEPLOYABLE BOOM TECHNOLOGIES. RECENT THRUSTER INNOVATIONS HAVE DRAMATICALLY INCREASED MAXIMUM THRUST, WHILE RETAINING CONTROL RESOLUTION, AND REDUCED PROPELLANT LOADS THROUGH INCREASED SPECIFIC IMPULSE. THESE GAINS WILL BE APPLIED IN THIS WORK TO REPLACE REACTION WHEEL ACTUATORS FOR BOTH PRECISION CONTROL AND SLEW MANEUVERS. ACCORDINGLY, ACTUATOR INDUCED VIBRATIONS ARE VIRTUALLY ELIMINATED WHILE BODY POINTING WILL BE DRAMATICALLY IMPROVED; RESULTING IN MAJOR REDUCTIONS IN ACS SWAP AND IN THE COMPLEXITY OF VIBRATION COMPENSATING CONTROLLERS/ACTIVE SENSORS. WITH APPLICATIONS TO, FOR EXAMPLE, OBSERVATION AND LASER COMMUNICATION MISSIONS THESE BENEFITS WOULD BOTH ENABLE HIGH-CAPABILITY BUT REDUCED COST SPACECRAFT AND PAVE THE WAY FOR NEW, PRESENTLY, UNOBTAINABLE LEVELS OF CONTROL AUTHORITY ON LARGE SPACECRAFT. PHASE I WILL EMPHASIZE ACQUISITION AND ANALYSIS OF PRECISION THRUST CONTROL MEASUREMENTS USING THE BET-1MN THRUSTER-HEAD WHICH, UNIQUELY, CAN BE OPERATED IN EITHER A HIGH THRUST, LOW ISP, OR LOW THRUST, HIGH ISP CONFIGURATION. THE ASSOCIATED COMPLEX PERFORMANCE MAP WILL BE ANALYZED IN THE CONTEXT OF HIGHLY QUIESCENT ACS NEEDS. THESE DATA WILL THEN BE APPLIED TO DEFINE NECESSARY CONTROL, CIRCUITRY AND MECHANICAL REQUIREMENTS NEEDED TO REALIZE THE FULL-ATTITUDE CONTROL POTENTIAL OF THE TECHNOLOGY. A CONCEPTUAL SYSTEM LEVEL DESIGN PERFORMED IN COLLABORATION WITH ROCCOR WILL OUTLINE STRATEGIES TO OVERCOME REQUIRED DEVELOPMENTS AND PRODUCE A COMPLETE SYSTEM DEMONSTRATION IN PHASE II. | $125K |
| Jun 6, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CG30P | 541712 | IGF::OT::IGF BUSEK PROPOSES TO DEVELOP A HIGHLY MODULAR ATTITUDE CONTROL SYSTEM (ACS) WHICH WILL PROVIDE ORDERS OF MAGNITUDE IMPROVEMENTS OVER STATE-OF-THE-ART ALTERNATIVE ACS FOR CUBESATS. THE LOW INERTIA OF CUBESATS COMBINED WITH VIBRATIONAL DISTURBANCES AND RESOLUTION LIMITATIONS OF STATE-OF-THE-ART ACS PRESENTLY LIMIT BODY-POINTING AND POSITION CONTROL ACCURACY. BUSEK'S ELECTROSPRAY THRUSTERS ABOARD THE ESA LISA PATHFINDER SPACECRAFT RECENTLY DEMONSTRATED PRECISION CONTROL AT NM SCALES; THIS WORK EXTENDS THAT SUCCESS TO CUBESAT PLATFORMS. PASSIVELY FED ELECTROSPRAY THRUSTERS ARE HIGHLY COMPACT, INCLUDING FULLY INTEGRATED PROPELLANT SUPPLIES, AND ARE CAPABLE OF ~100NN THRUST AT 10'S OF NN NOISE. THRUST CAN BE THROTTLED OVER>25X, TO A SCALABLE MAXIMUM OF 10'S OF UN. THESE TRAITS, COMBINED WITH>1200S ISP ENABLE THESE SYSTEMS TO REPLACE TRADITIONAL REACTION WHEEL ACS; IMPROVING POINTING ERROR FROM ARCSECS TO 10'S OF MILLIARCSEC. THIS WORK ADDRESSES CRITICAL DEVELOPMENT GAPS, IN BOTH THRUSTER-HEADS AND A MULTI-AXIS POWER PROCESSING UNIT WITH INTEGRATED FIRMWARE, PRESENTLY GATING THE TECHNOLOGY. PHASE I WILL FOCUS ON ESTABLISHING A BASELINE SET OF DATA AND METHODOLOGIES PERMITTING DETAILED VERIFICATION OF THE TECHNOLOGY AND DEFINITION OF DEVELOPMENT GAPS. THE OUTPUT OF EXISTING DESIGNS WILL BE SCALED TO TARGET ACS APPLICABLE PERFORMANCE IN TASK 1, CULMINATING IN ASSEMBLY OF TWO THRUSTERS. A PRECISELY MEASURED PERFORMANCE MAP INCLUDING THRUST RANGE, RESOLUTION AND NOISE WILL BE MEASURED IN TASK 2 FROM BOTH THRUSTER HEADS. THOSE DATA WILL PERMIT PPU SYSTEM REQUIREMENTS TO BE DEFINED AND WILL FEED DEVELOPMENT OF CONTROL LAWS TO BE EVALUATED, IN TASK 3, USING A HARDWARE-IN-THE-LOOP PRECISION POINTING TEST APPARATUS. ELECTRONICS REQUIREMENTS WILL BE ASSESSED AGAINST EXISTING SINGLE-AXIS ARCHITECTURES AND NEW HV CONVERTER MEASUREMENTS IN TASK 4, ALONG WITH IDENTIFICATION OF THRUSTER HEAD DEVELOPMENT NEEDS; ESTABLISHING A PATH TOWARDS A FULL SYSTEM DEVELOPMENT IN PHASE II. | $125K |
| Jun 4, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CC32P | 541712 | IGF::OT::IGF BUSEK PROPOSES A NOVEL, UNIVERSAL, MODULAR, 2.5KW DISCHARGE CONVERTER FOR HALL EFFECT THRUSTER (HET) POWER PROCESSING UNIT (PPU). THE UNIQUE ADVANTAGES OF THE PROPOSED SYSTEM INCLUDE:(1) A WIDE INPUT VOLTAGE RANGE (28V TO 100V) WITH A WIDE OUTPUT VOLTAGE (150V TO 400V) WHILE MAINTAINING HIGH EFFICIENCY OPERATION. THEREFORE, IT PROVIDES A UNIVERSAL SOLUTION FOR AEROSPACE SYSTEMS WITH DIFFERENT BUS VOLTAGES. (2) THIS MODULAR CONVERTER WILL BE CAPABLE OF INPUT-PARALLEL OUTPUT-SERIES (IPOS) OPERATION TO SUPPORT HIGHER OUTPUT VOLTAGE (800V-1200V OR HIGHER) AND INPUT-PARALLEL OUTPUT-PARALLEL (IPOP) OPERATION TO SUPPORT HIGHER OUTPUT POWER (20KW OR HIGHER). AN INTELLIGENT "PLUG-N-PLAY" POWER SHARING AND VOLTAGE BALANCING CONTROL IS PROPOSED TO SUPPORT THE IPOS AND IPOP OPERATIONS. (3) THE PROPOSED CONVERTER ADOPTS A SOFT-SWITCHING DC/DC TOPOLOGY USING THE ADVANCED GAN POWER MOSFETS TO ENABLE HIGH EFFICIENCY WITH HIGH SWITCHING FREQUENCY OPERATION, WHICH LEADS TO SIGNIFICANT SIZE REDUCTION OF MAGNETICS AND OTHER PASSIVE COMPONENTS TO PUSH FOR HIGH POWER DENSITY DESIGN. THE TARGETING POWER DENSITY FOR SINGLE MODULE IS MORE THAN 1KW/KG. THE PHASE I EFFORT INCLUDES DESIGN AND ANALYSIS OF MODULAR DISCHARGE CONVERTER WITH THE GAN POWER MOSFETS AND THE "PLUG-N-PLAY" POWER SHARING AND VOLTAGE BALANCING CONTROL SYSTEM TO SUPPORT IPOS AND IPOP OPERATION. THE BREAD BOARD WILL USE COTS EEE PARTS. ITS TESTING WILL VALIDATE THE PERFORMANCE OVER THE WIDE INPUT/OUTPUT VOLTAGE RANGE. TWO MODULES WILL VERIFY IPOS AND IPOP OPERATION. THE INITIAL SYSTEM INTEGRATION TEST WITH BUSEK HET WILL ALSO BE CONDUCTED. IN PHASE II WE WILL FULLY CHARACTERIZE THE BREADBOARD DISCHARGE CONVERTER WITH A THRUSTER AND DEVELOP A PROTO-FLIGHT BRASS-BOARD LEVEL UNIT WITH MULTIPLE DISCHARGER MODULES USING GAN DEVICES. AT THE CONCLUSION OF PHASE II WE WILL BUILD AND DELIVER SEVERAL DISCHARGER MODULES TO NASA FOR ADDITIONAL CHARACTERIZATION TESTING. | $125K |
| Apr 20, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CC02C | 541712 | IGF::OT::IGF AS PART OF A NASA GAME CHANGING TECHNOLOGIES PROGRAM, BUSEK DEVELOPED A FULLY INTEGRATED PROTOTYPE 100UN-CLASS SYSTEM (BET-100UN) SUITABLE FOR INTEGRATION INTO CUBESAT PLATFORMS. THIS STATEMENT OF WORK OUTLINES THE EFFORT TO FLIGHT-QUALIFY THE ELECTROSPRAY SYSTEM DEVELOPED AS PART OF THE MICROFLUIDIC ELECTROSPRAY PROPULSION (MEP) PHASE I PROGRAM. THE FINAL INTEGRATED UNITS DELIVERED AS PART OF THE PHASE I WERE INTENDED TO BE VIABLE FOR LOW EARTH ORBIT (LEO) DEMONSTRATION AFTER COMPLETION OF A QUALIFICATION EFFORT. THE WORK DESCRIBED HEREIN IS INTENDED TO: PERFORM ADDITIONAL ANALYSIS AND TESTING TO FURTHER CHARACTERIZE THE PHASE I DELIVERABLE DESIGN, CONDUCT A QUALIFICATION PROGRAM, FABRICATE FLIGHT HARDWARE, SUPPORT PROPULSION SYSTEM INTEGRATION INTO THE SPACECRAFT, AND SUPPORT FLIGHT OPERATIONS. THE FLIGHT UNITS ARE INTENDED FOR INTEGRATION INTO A 6U CUBESAT AND LEO DEMONSTRATION AS PART OF THE NASA PATHFINDER TECHNOLOGY DEMONSTRATOR PROJECT, SPONSORED BY THE SMALL SPACECRAFT TECHNOLOGY PROGRAM (SSTP). THE INTEGRATED ELECTROSPRAY THRUSTER SYSTEM CONSISTS OF A TWO-BOARD ELECTRICAL STACK, WITH EXTERNAL DIMENSIONS OF 9.5CM X 9.5CM X 3.3CM, EQUIVALENT TO 1/3U IN A CUBESAT FROM FACTOR. THE FIRST 9.5CM X 9.5CM BOARD HOUSES THE ENTIRETY OF THE ELECTRONICS; A POWER PROCESSING UNIT (PPU), AND THE DIGITAL CONTROL INTERFACE UNIT (DCIU) LOCATED ON A SMALL MEZZANINE BOARD. THE SECOND 9.5CM X 9.5CM BOARD HOUSES THE 100?N ELECTROSPRAY THRUSTER, AS WELL AS A CARBON NANOTUBE FIELD EMISSION CATHODE (CNTFEC) USED TO NEUTRALIZE THE EMITTED ELECTROSPRAY BEAM. | $641K |
| Apr 19, 2017 | Department of DefenseFA8601 AFLCMC PZIO | FA860117P0121 | 336415 | IODINE ION THRUSTER | $165K |
| Apr 18, 2017 | Department of DefenseFA9300 AFTC PZR | FA930014C3000 | 541712 | IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT | $100K |
| Mar 31, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CC02C | 541712 | IGF::OT::IGF AS PART OF A NASA GAME CHANGING TECHNOLOGIES PROGRAM, BUSEK DEVELOPED A FULLY INTEGRATED PROTOTYPE 100UN-CLASS SYSTEM (BET-100UN) SUITABLE FOR INTEGRATION INTO CUBESAT PLATFORMS. THIS STATEMENT OF WORK OUTLINES THE EFFORT TO FLIGHT-QUALIFY THE ELECTROSPRAY SYSTEM DEVELOPED AS PART OF THE MICROFLUIDIC ELECTROSPRAY PROPULSION (MEP) PHASE I PROGRAM. THE FINAL INTEGRATED UNITS DELIVERED AS PART OF THE PHASE I WERE INTENDED TO BE VIABLE FOR LOW EARTH ORBIT (LEO) DEMONSTRATION AFTER COMPLETION OF A QUALIFICATION EFFORT. THE WORK DESCRIBED HEREIN IS INTENDED TO: PERFORM ADDITIONAL ANALYSIS AND TESTING TO FURTHER CHARACTERIZE THE PHASE I DELIVERABLE DESIGN, CONDUCT A QUALIFICATION PROGRAM, FABRICATE FLIGHT HARDWARE, SUPPORT PROPULSION SYSTEM INTEGRATION INTO THE SPACECRAFT, AND SUPPORT FLIGHT OPERATIONS. THE FLIGHT UNITS ARE INTENDED FOR INTEGRATION INTO A 6U CUBESAT AND LEO DEMONSTRATION AS PART OF THE NASA PATHFINDER TECHNOLOGY DEMONSTRATOR PROJECT, SPONSORED BY THE SMALL SPACECRAFT TECHNOLOGY PROGRAM (SSTP). THE INTEGRATED ELECTROSPRAY THRUSTER SYSTEM CONSISTS OF A TWO-BOARD ELECTRICAL STACK, WITH EXTERNAL DIMENSIONS OF 9.5CM X 9.5CM X 3.3CM, EQUIVALENT TO 1/3U IN A CUBESAT FROM FACTOR. THE FIRST 9.5CM X 9.5CM BOARD HOUSES THE ENTIRETY OF THE ELECTRONICS; A POWER PROCESSING UNIT (PPU), AND THE DIGITAL CONTROL INTERFACE UNIT (DCIU) LOCATED ON A SMALL MEZZANINE BOARD. THE SECOND 9.5CM X 9.5CM BOARD HOUSES THE 100?N ELECTROSPRAY THRUSTER, AS WELL AS A CARBON NANOTUBE FIELD EMISSION CATHODE (CNTFEC) USED TO NEUTRALIZE THE EMITTED ELECTROSPRAY BEAM. | $100K |
| Mar 30, 2017 | Department of DefenseFA9300 AFTC PZR | FA930017C2003 | 541712 | IGF::OT::IGF - AWARD OF FUEL FLEXIBLE HALL THRUSTER FOR MULTI-MODE PROPULSION SYSTEMS SBIR PHASE II EFFORT | $563K |
| Mar 29, 2017 | Department of DefenseFA9550 AFRL AFOSR | FA955017P0005 | 541712 | IGF::OT::IGF "(SBIR PHASE I) HIGH SPEED PLASMA PROBE AND ELECTRONICS SUITE" | $150K |
| Mar 14, 2017 | Department of DefenseFA9300 AFTC PZR | FA930017C1002 | 541712 | IGF::OT::IGF SBIR PHASE I - INTEGRATED GREEN MONOPROPELLANT PROPELLANT PROCESSING FOR HIGH POWER ELECTROSPRAY THRUSTERS | $150K |
| Mar 14, 2017 | Department of DefenseFA9300 AFTC PZR | FA930017C1001 | 541712 | IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH (SBIR) 1, FY16 MODEL CONTRACT | $150K |
| Mar 9, 2017 | Department of DefenseMISSILE DEFENSE AGENCY (MDA) | HQ014717C7103 | 541712 | IGF::OT::IGF STTR PHASE II RESEARCH&DEV | $996K |
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