Federal Contractor Profile
Honeybee Robotics, LTD.
$108.3M obligated·69 awards·4 agencies·9 NAICS
Federal Contracts
Showing contracts 51–100 of 161 total. Sorted by action date, most recent first. Excludes $0 modifications.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Sep 2, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $906K |
| Aug 25, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0241 | 541715 | EXTRA-VEHICULAR ACTIVITY CREW DEPLOYED CORING AND.SEALING SYSTEMS | $1.3M |
| Aug 24, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0067 | 541715 | DEVELOPING ROBOTIC INTERFACES FOR TRANSLATION, MANIPULATION AND.CHARGING FOR THE NASA GATEWAY PROGRAM | $40K |
| Aug 11, 2020 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | 80MSFC20C0007 | 541715 | THE CONTRACTOR SHALL DEVELOP TECHNOLOGY FOR ACQUIRING AND TRANSFERRING REGOLITH FROM THE LUNAR SURFACE TO INSTRUMENTS AND SAMPLE RETURN CONTAINERS | $2.2M |
| Jul 31, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC20C0115 | 541330 | THE SAMPLE ACQUISITION AT MARS (SAM) SUITE INVESTIGATION WILL CAST A WIDE ANALYTICAL NET TO CAPTURE CHEMICAL INDICATORS OF THE HABITABILITY OF MARS. SAM WILL "FIND THE CARBON" REVEALING THEIR LIKELY SOURCE AND TRANSFORMATIONAL PROCESSES. | $350K |
| Jul 9, 2020 | Department of DefenseDEF ADVANCED RESEARCH PROJECTS AGCY | HR001120C0143 | 541715 | DISRUPTIVE CAPABILITIES FUTURE WARFARE | $462K |
| Jun 22, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC20C0026 | 541715 | KARLE SAMPLE HANDLING SYSTEM | $389K |
| Jun 11, 2020 | Department of Homeland SecuritySCI TECH ACQ DIV | 70RSAT20CB0000012 | 541715 | BROAD AGENCY ANNOUNCEMENT (BAA) CONTRACT FOR ROBOTIC STEREOSCOPIC SYSTEM | $888K |
| May 14, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0006 | 541715 | ONE-METER CLASS DRILLING FOR PLANETARY EXPLORATION | $203K |
| May 11, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0067 | 541715 | DEVELOPING ROBOTIC INTERFACES FOR TRANSLATION, MANIPULATION AND.CHARGING FOR THE NASA GATEWAY PROGRAM | $50K |
| May 6, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $2.9M |
| Apr 15, 2020 | National Aeronautics and Space AdministrationNASA KENNEDY SPACE CENTER | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $97K |
| Apr 9, 2020 | National Aeronautics and Space AdministrationNASA LANGLEY RESEARCH CENTER | 80LARC20P0018 | 541715 | THE ASSEMBLERS PROJECT WILL TRANSFORM IN-SPACE ASSEMBLY (ISA) EFFORTS BY APPLYING THE LATEST TECHNOLOGICAL ADVANCES IN MACHINE LEARNING, CONTROL THEORY, AND STATE ESTIMATION TO EXPAND CONCEPTS PIONEERED BY NASA. | $150K |
| Mar 16, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $723K |
| Mar 16, 2020 | National Aeronautics and Space AdministrationNASA KENNEDY SPACE CENTER | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $137K |
| Mar 2, 2020 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0014 | 541715 | ROBOTIC ISRU CONSTRUCTION OF PLANETARY LANDING AND LAUNCH PAD | $501K |
| Jan 15, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC20C0026 | 541715 | KARLE SAMPLE HANDLING SYSTEM | $362K |
| Jan 13, 2020 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $901K |
| Jan 6, 2020 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $200K |
| Dec 9, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20P0259 | 541715 | HONEYBEE CONTRACT - EMILI | $199K |
| Dec 6, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20P0172 | 334511 | HONEYBEE ROBOTICS LAUNCH LOCK VERIFICATION ENVIRONMENTAL TESTING. | $186K |
| Nov 27, 2019 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $200K |
| Nov 19, 2019 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | 80MSFC20C0007 | 541715 | THE CONTRACTOR SHALL DEVELOP TECHNOLOGY FOR ACQUIRING AND TRANSFERRING REGOLITH FROM THE LUNAR SURFACE TO INSTRUMENTS AND SAMPLE RETURN CONTAINERS | $611K |
| Nov 4, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20P0127 | 335312 | MOSAIC HONEYBEE - ENGINEERING - (4) MOTORS | $88K |
| Oct 30, 2019 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $200K |
| Oct 24, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC20C0006 | 541715 | ONE-METER CLASS DRILLING FOR PLANETARY EXPLORATION | $2.0M |
| Sep 25, 2019 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $562K |
| Sep 12, 2019 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX19F0047 | 334516 | ENGINEERING SUPPORT SERVICES, PARTS FOR A-DCP SYSTEM, AND TEST/REPAIR SERVICES. | $13K |
| Sep 10, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0629 | 541715 | PNEUMATIC SAMPLER (P-SAMPLER) JAXA MARTIAN MOONS EXPLORATION (MMX) MISSION | $500K |
| Aug 30, 2019 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG15CR63C | 541330 | IGF::CT::IGF THE PURPOSE OF THIS CONTRACT IS FOR ENGINEERING SUPPORT SERVICES FROM HONEYBEE ROBOTICS. THE CONTRACTOR WILL PROVIDE SUSTAINING ENGINEERING SUPPORT FOR THE SAM/SMS DURING NOMINAL OPERATIONS OF THE SAM PAYLOAD, ANOMALOUS OPERATIONS OF THE SAM PAYLOAD, AND FOR SPECIAL OPERATIONS AND END-OF-LIFE ANALYSIS DURING THE MSL EXTENDED MISSION. | $484K |
| Aug 13, 2019 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA16BD69C | 541712 | IGF::OT::IGF SBIR PHASE III - ATACAMA ROVER ASTROBIOLOGY DRILLING STUDIES (ARADS) PROJECT | $52K |
| Aug 8, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0061 | 541715 | MARTIAN MOONS EXPLORATION (MMX) P-SAMPLER | $350K |
| Jul 31, 2019 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0044 | 334519 | HONEYBEE ROBOTICS COLLABORATIVE ACCEPTANCE AND DISTRIBUTION FOR MEASURING EUROPAN SAMPLES (CADMES) SYSTEM | $700K |
| Jul 19, 2019 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $168K |
| Jul 19, 2019 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $375K |
| May 23, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0028 | 541715 | OCEAN WORLDS AND MARS ARE OF PARTICULAR INTEREST TO ASTROBIOLOGY SINCE THEY COULD OFFER CLUES IN THE QUEST TO DISCOVER LIFE BEYOND OUR HOME PLANET. EUROPA HAS BEEN A PRIMARY TARGET IN THE SEARCH FOR PAST OR PRESENT LIFE BECAUSE IT IS STILL GEOLOGICALLY ACTIVE AND HAS A LARGE OCEAN UNDERNEATH AN ICE SHELL (DESPITE BEING SMALLER THAN OUR MOON, EUROPA HAS MORE WATER THAN EARTH). THEREFORE, WE WILL FOCUS TECHNOLOGY DEVELOPMENT ON EUROPA. HOWEVER THE PROPOSED TECHNOLOGY (WITH VARIOUS DEGREE OF MODIFICATION) COULD ALSO BE USED ON OTHER OCEAN WORLDS AND MARS. TO ADVANCE FORWARD, A PROBE WOULD NEED TO􀁇DESTROY􀁇 THE FORMATION AND MOVE THE DRILLED MATERIAL BEHIND IT. THIS CAN BE ACHIEVED VIA TWO PRIMARY METHODS: THERMAL AND MECHANICAL. EACH OF THESE TWO METHODS HAS UNIQUE ADVANTAGES AND DISADVANTAGES BUT NEITHER IS SUFFICIENT TO REACH THE OCEAN. THERMAL PROBES (E.G. MELT PROBES, CLOSED CYCLE HOT WATER DRILLS - CCHWD, LASERS) ARE VERY ROBUST PENETRATORS THAT REQUIRE JUST HEAT TO MELT THROUGH AND ADVANCE DEEPER BELOW THE SURFACE. THERMAL PROBES, HOWEVER, ARE SLOW (ESPECIALLY IN CRYOGENIC ICE), REQUIRE SIGNIFICANT AMOUNT OF POWER (KW TO 10S OF KW, DEPENDING ON THE PROBE􀁇S DIAMETER AND LENGTH), AND ARE INEFFICIENT, BECAUSE>90% OF THE HEAT IS LOST INTO SURROUNDING ICE. MECHANICAL DRILLING SYSTEMS, ON THE OTHER HAND, ARE APPROXIMATELY 100X MORE EFFICIENT AND SIGNIFICANTLY FASTER. FOR THAT REASON THEY ARE PRIMARY METHODS OF MAKING HOLES AND CAPTURING ICE CORES IN GREENLAND AND ANTARCTICA. THEY CAN ALSO PENETRATE MATERIALS OTHER THAN ICE (E.G. SALTS). THE MAJOR DRAWBACK OF THESE DRILLS RELATES TO CHIPS REMOVAL. CHIPS NEED TO BE REMOVED BY EITHER PERIODICALLY LIFTING THE DRILL WITH CHIPS BASKET OUT OF THE HOLE (CONVENTIONAL METHOD USED IN TERRESTRIAL ICE DRILLING) OR LIFTING THE CHIPS ABOVE THE PROBE AND RECOMPACTING THEM TO THEIR ORIGINAL DENSITY (E.G. INCH WORM APPROACH). IN SUMMARY, MECHANICAL SYSTEMS HAVE VERY EFFICIENT FORMATION BREAKING APPROACH WHILE THERMAL SYSTEMS HAVE VERY EFFECTIVE CHIPS REMOVAL APPROACH. SLUSH IS A THERMO-MECHANICAL PROBE THAT COMBINES THE BEST FROM THESE TWO TECHNIQUES: MECHANICAL DRILL TO BREAK THE FORMATION AND MELTING TO REMOVE THE CUTTINGS). HOWEVER, INSTEAD OF MELTING AN ENTIRE VOLUME OF ICE, SLUSH MELTS JUST A FRACTION OF IT TO FORM SLUSH. SLUSH BEHAVES LIKE LIQUID BUT IS STILL PARTIALLY FROZEN THIS ENABLES SIGNIFICANT REDUCTION IN POWER DRAW. SINCE MECHANICAL APPROACH GENERATES HIGHER PENETRATION RATES, SLUSH CAN ALSO REACH THE OCEAN IN MUCH SHORTER TIME. SLUSH LOOKS LIKE A TORPEDO WITH A DRILL BIT IN FRONT AND ANTI-TORQUE BLADES ON THE SIDE (PROVEN SYSTEM IN ANTARCTIC WIRELINE DRILLS). IT HOUSES SCIENTIFIC INSTRUMENTS FOR IN-SITU ANALYSIS. IT IS CONNECTED TO A SURFACE LANDER BY AN UMBILICAL FOR DATA AND POWER. TO REDUCE POWER DRAW FROM THE SURFACE ENERGY SUPPLY NEEDED FOR PARTIAL MELTING, SLUSH INCORPORATES GENERAL PURPOSE HEAT SOURCE􀁇 BRICKS WITH ~250 WATT THERMAL POWER. ONCE SLUSH PASSES THROUGH THE CRYOGENIC LICE (A FEW KM THICK), IT CAN USE JUST A THERMAL APPROACH TO MELT THROUGH THE WARMER ICE WITHOUT THE NEED FOR MECHANICAL CUTTING. THERMAL PROBES ARE SIGNIFICANTLY MORE EFFICIENT IN TEMPERED (WARM) ICE. UNDER PICASSO, THE TRL OF SLUSH WILL BE INCREASED FROM TRL2 TO TRL4. WE WOULD FOCUS ON TWO OF THE MOST CRITICAL TECHNICAL ASPECTS: DRILLING/MELTING AND CHIPS TRANSPORT. TO REACH TRL4, WE PROPOSE TO: 1. DEVELOP HIGH LEVEL DESIGNS AND THERMAL MODELS FOR CRYOGENIC AND WARM ICE TO ESTABLISH POWER LEVELS NEEDED FOR PARTIAL MELTING, AND CONSTRAIN PROBE􀁇S DIAMETER AND LENGTH. 2. BREADBOARD CRITICAL SUBSYSTEMS THAT WILL SUPPORT TRL4 SLUSH DESIGN. 3. DESIGN AND BUILD TRL 4 SLUSH AND TEST IT IN OUR 5 M TALL FREEZER AND IN OUR 3.5 M TALL THERMAL VACUUM CHAMBER IN EUROPA ANALOG ICE. 4. UPDATE HIGH LEVEL SLUSH DESIGN BASED ON TEST DATA. | $866K |
| May 17, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0056 | 541715 | TESTING OF TRL-6 TRIDENT IN HBR LARGE TVAC CHAMBER. DESIGN, FABRICATE AND TEST BREADBOARD RESOLVER-TO-DIGITAL CONVERTER SUBSYSTEM. DESIGN BREADBOARD MOTOR DRIVE SUBSYSTEM (FABRICATE AND TEST UNDER NEXT MOD). WRITE AND TEST CONTROL SOFTWARE (MAKE PROGRESS NOT DELIVERED UNTIL NEXT MOD). | $625K |
| Apr 29, 2019 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX19F0047 | 334516 | ENGINEERING SUPPORT SERVICES, PARTS FOR A-DCP SYSTEM, AND TEST/REPAIR SERVICES. | $468K |
| Apr 19, 2019 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | 80HQTR19C0024 | 541715 | REDWATER COMBINES THE TWO TECHNOLOGIES INTO ONE: IT USES THE CT APPROACH TO CREATE A HOLE (FIGURE 1). ONCE THE HOLE IS MADE, THE COILED TUBING IS LEFT IN THE HOLE AND USED AS CONDUIT FOR WATER EXTRACTION. THE BHA CONTAINS A ROTARY-PERCUSSIVE DRILL SUBSYSTEM (SIMILAR TO THE ONE USED IN HONEYBEE ROBOTICS DEEP DRILL3), A DOWNHOLE PUMP, AND HEATERS. THE TUBE HOUSES AN INSULATED AND HEATED HOSE AS WELL AS WIRES FOR DOWNHOLE MOTORS AND HEATERS. DURING DRILLING, COMPRESSED GAS IS SEND DOWNHOLE THROUGH THE HOSE. THE GAS ESCAPES THROUGH THE ANNUAL SPACE BETWEEN THE TUBE AND BOREHOLE WALL AND REMOVES CHIPS THAT CAN BE COLLECTED AND ANALYZED FOR SCIENCE. UPON REACHING AN ICE LAYER, THE DRILL CONTINUES FOR ANOTHER 3 M AND THEN STOPS ADVANCING FORWARD, BUT THE BIT CONTINUOUS SPINNING. HEATERS ARE TURNED ON TO MELT THE SURROUNDING ICE. ONCE ICE STARTS TO MELT, THE PERISTALTIC PUMP STARTS PUMPING A FRACTION OF THE MELTED WATER UP THE SAME HOSE THAT WAS USED FOR THE COMPRESSED GAS, AND INTO A STORAGE TANK ON THE SURFACE VIA A 3-WAY HEATED VALVE (VALVE SWITCHES BETWEEN THE GAS TANK AND WATER TANK). THE REMAINING WATER PASSES THROUGH A DOWNHOLE HEATER AND IS PUMPED INTO THE ROTATING BIT FOR WATER JETTING THIS CONTINUOUS STIRRING OF WATER AND INJECTION OF HOT WATER SPEEDS UP THE MELTING PROCESS. AFTER MELTING A SECTION OF ICE, THE CT IS REACTIVATED TO DRILL FURTHER AND THE MELTING PROCESS CONTINUES. SINCE ATMOSPHERIC PRESSURE AT ARCADIA PLANITIA IS ABOVE THE TRIPLE POINT OF WATER, LIQUID WATER CAN EXIST. HOWEVER, IT IS UNSTABLE AND CAN BOIL OFF VERY QUICKLY. FOR THIS REASON, IT WOULD BE DESIRABLE TO SEAL OFF THE HOLE. THIS CAN BE ACHIEVED VIA ACTIVE MEANS (A PACKER CAN EXPAND IN A HOLE AND SEAL THE ANNULAR SPACE BETWEEN THE TUBE AND THE BOREHOLE) OR PASSIVE MEANS (WATER VAPOR WOULD RE-CONDENSE ON THE COLD BOREHOLE WALL AND SEAL IT THIS IN FACT HAS BEEN OBSERVED). THE TUBE WOULD HAVE TO BE HEATED TO FREE ITSELF UP BEFORE CONTINUING FURTHER DOWN, WHEN NEEDED. OUR PNEUMATIC EXCAVATION TESTS AT 7 TORR SHOWED PENETRATION RATES OF 1 M/MIN IN REGOLITH4. THE MASS RATIO OF GAS USED TO MATERIAL REMOVED OUT OF THE HOLE WAS 1:500. ASSUMING A 5 CM DIAMETER HOLE (CURRENT BASELINE FOR REDWATER), THE REQUIRED MASS OF GAS WOULD BE 10 KG. MOST OF THE SOURCES OF COMPRESSED GAS ARE AT HIGH TRL. GAS CAN BE BROUGHT FROM THE EARTH (MARS2020 MISSION BRINGS A TANK OF COMPRESSED N2 TO BLOW DUST OFF ROCKS), HELIUM PRESSURANT CAN BE USED FROM LANDED SYSTEMS, ROCKET FUEL CAN BE BURNED AND TURNED INTO GAS, AND ISRU GASSES (H2/O2) COULD ALSO BE USED. FINALLY, A COMPRESSOR COULD COMPRESS MARTIAN AIR. MOXI ON MARS2020 HAS A COMPRESSOR THAT WOULD TAKE 100 HOURS TO COMPRESS 10 KG OF CO2 FROM 7 TORR TO 760 TORR. TO EXTRACT THE REQUIRED 16 TONS OF WATER, A POOL OF APPROXIMATELY 3.1 M IN DIAMETER HAS TO BE CREATED, WHICH IS FEASIBLE. THE PROCESS OF WATER EXTRACTION WOULD TAKE SEVERAL WEEKS. OUR THERMAL MODELS USING MATHCAD AS WELL AS CALCULATIONS SHOW THAT REQUIRE HEAT FOR MELTING IS 1.5 KW AND FOR KEEPING THE WATER HOSE WARM ALONG THE 25 M LENGTH IS 1 KW. FIGURE 1 SHOWS REDWATER SYSTEM ON ATHLETE ROVER. IT USES SOLAR PANELS AND MMRTG TO PROVIDE ELECTRICAL POWER AND HEAT. FIGURE 2 SHOWS REDWATER IN ITS STORED CONFIGURATION FOR LAUNCH WHILE FIGURE 3 SHOWS THE UNDERCARRIAGE AND BHA. | $187K |
| Mar 25, 2019 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA16BD69C | 541712 | IGF::OT::IGF SBIR PHASE III - ATACAMA ROVER ASTROBIOLOGY DRILLING STUDIES (ARADS) PROJECT | $17K |
| Mar 11, 2019 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA16BD69C | 541712 | IGF::OT::IGF SBIR PHASE III - ATACAMA ROVER ASTROBIOLOGY DRILLING STUDIES (ARADS) PROJECT | $25K |
| Mar 7, 2019 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG15CR63C | 541330 | IGF::CT::IGF THE PURPOSE OF THIS CONTRACT IS FOR ENGINEERING SUPPORT SERVICES FROM HONEYBEE ROBOTICS. THE CONTRACTOR WILL PROVIDE SUSTAINING ENGINEERING SUPPORT FOR THE SAM/SMS DURING NOMINAL OPERATIONS OF THE SAM PAYLOAD, ANOMALOUS OPERATIONS OF THE SAM PAYLOAD, AND FOR SPECIAL OPERATIONS AND END-OF-LIFE ANALYSIS DURING THE MSL EXTENDED MISSION. | $260K |
| Feb 22, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0036 | 541715 | WBS 1.REVIEW AND FORMALIZE REQUIREMENTS DURING THIS TASK WE WILL REVIEW THE REQUIREMENTS AND TURN THEM INTO ENGINEERING REQUIREMENTS, IF NEEDED WBS 2.SUPPORT CONTRACT NEGOTIATIONS BY PROVIDING ADDITIONAL TECHNICAL INFORMATION DURING THIS TASK WE WILL PROVIDE INPUT DURING CONTRACT NEGOTIATIONS RELATED TO TECHNICAL ASPECTS OF THE PROJECT. SOME INPUT MAY REQUIRE ENGINEERING CALCULATIONS OR VENDOR QUOTE FOR EXAMPLE. WBS 3.DEVELOP UPDATED HIGH-LEVEL DESIGN OF THE P-SAMPLER. PROPRIETARY DATA HBR QN 2018-129 R1 FEB 14, 2019 4 DURING THIS TASK, WE WILL PERFORM A HIGH LEVEL DESIGN OF THE PS. THE DESIGN WILL NOT TAKE INTO ACCOUNT TOLERANCES STACK OR MATERIAL SELECTION BUT RATHER WILL BE USED AS A STARTING POINT FOR TRL6 DESIGN WBS 4.PERFORM TRADE STUDY RELATED TO METHODS FOR VERIFYING SAMPLE HAS BEEN CAPTURED DURING THIS TASK, WE WILL IDENTIFY VARIOUS OPTIONS FOR SAMPLE VERIFICATION. WE WILL PERFORM TRADE STUDY AND PROVIDE FINAL RESULTS. WBS 5.SUPPORT IN-PERSON MEETINGS AND TELECONS DURING THIS TASK WE WILL SUPPORT ANY IN-PERSON MEETINGS AND TELECONS WBS 6.PROVIDE FINAL REPORT AT THE END OF THE PROJECT, WE WILL PROVIDE FINAL SUMMARY REPORT IN THE FORM OF A PPT SLIDES OR WORD DOCUMENT. | $300K |
| Dec 17, 2018 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC19C0022 | 541330 | DRAGONFLY RELOADABLE LANDER TO EXPLORE TITAN'S PREBIOTIC CHEMISTRY AND HABITABILITY ANNOUNCEMENT OF OPPORTUNITY NNH16ZD011O | $310K |
| Nov 13, 2018 | Department of DefenseW6QK ACC-APG ADELPHI | 0001 | 334516 | IGF::OT::IGF A-DCP SYSTEM SUSTAINMENT SUPPORT SERVICES | $6K |
| Sep 28, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0234 | 541715 | MARTIAN MOON EXPLORATION (MMX) HAS SET THE TWO MISSION GOALS: (1) DETERMINING THE ORIGIN OF THE MARTIAN MOONS AND (2) OBSERVING PROCESSES IN THE CIRCUMPLANETARY ENVIRONMENT OF MARS, BASED ON REMOTE SENSING AND IN?SITU OBSERVATIONS AND LABORATORY ANALYSES OF RETURNED SAMPLES OF PHOBOS REGOLITH (NNH17ZDA004O?MMX; MMX?SCIRD?ALL). THE ORIGINS OF PHOBOS AND DEIMOS ARE STILL A MATTER OF SIGNIFICANT DEBATE: CAPTURE OF ASTEROIDS VERSUS IN?SITU FORMATION BY A GIANT IMPACT ON MARS (E.G., HESSELBROCK AND MINTON, 2017; HIGUCHI AND IDA, 2017; HYODO ET AL. 2017; ROSENBLATT, 2016;). IN EITHER CASE, MMX WILL DEFINITELY PROVIDE CLUES ABOUT THEIR ORIGINS AND OFFER AN OPPORTUNITY TO DIRECTLY EXPLORE THE SATELLITE BUILDING BLOCKS OR JUVENILE CRUST,MANTLE COMPONENTS OF MARS. THE NEW KNOWLEDGE OF MARS AND ITS MOONS ACQUIRED BY MMX WILL BE FURTHER LEVERAGED TO CONSTRAIN THE INITIAL CONDITION OF THE MARSMOON SYSTEM, TO GAIN VITAL INSIGHTS REGARDING THE SOURCES AND DELIVERY PROCESS OF WATER AND ORGANICS INTO 3 THE INNER ROCKY PLANETS, AND TO EVENTUALLY FILL THE KNOWLEDGE GAPS TOWARDS THE PLANNED FUTURE HUMAN EXPLORATION OF PHOBOS AND MARS. TO FULFILL THE MISSION GOALS, MMX SHOULD COLLECT BOTH ENDOGENOUS AND EXOGENOUS SAMPLES FROM THE REGOLITH COVERING THE PHOBOS SURFACE. THE FORMER REPRESENTS PHOBOS BUILDING BLOCKS THAT RECORD INFORMATION OF THE MOONS ORIGIN, WHILE THE LATTER IS EXPECTED TO CONTAIN SOLAR SYSTEM PROJECTILES AND EJECTA DERIVED FROM MARS AND DEIMOS. ALTHOUGH THE DEPTH PROFILE OF PHOBOS REGOLITH REGARDING MATERIAL DISTRIBUTION IS UNKNOWN, A RATIO OF [EXOGENOUS, ENDOGENOUS] ABUNDANCES IS EXPECTED TO BE HIGHEST AT THE TOP?MOST REGOLITH LAYER. | $100K |
| Sep 26, 2018 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG15CR63C | 541330 | IGF::CT::IGF THE PURPOSE OF THIS CONTRACT IS FOR ENGINEERING SUPPORT SERVICES FROM HONEYBEE ROBOTICS. THE CONTRACTOR WILL PROVIDE SUSTAINING ENGINEERING SUPPORT FOR THE SAM/SMS DURING NOMINAL OPERATIONS OF THE SAM PAYLOAD, ANOMALOUS OPERATIONS OF THE SAM PAYLOAD, AND FOR SPECIAL OPERATIONS AND END-OF-LIFE ANALYSIS DURING THE MSL EXTENDED MISSION. | $250K |
| Aug 24, 2018 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG15CR63C | 541330 | IGF::CT::IGF THE PURPOSE OF THIS CONTRACT IS FOR ENGINEERING SUPPORT SERVICES FROM HONEYBEE ROBOTICS. THE CONTRACTOR WILL PROVIDE SUSTAINING ENGINEERING SUPPORT FOR THE SAM/SMS DURING NOMINAL OPERATIONS OF THE SAM PAYLOAD, ANOMALOUS OPERATIONS OF THE SAM PAYLOAD, AND FOR SPECIAL OPERATIONS AND END-OF-LIFE ANALYSIS DURING THE MSL EXTENDED MISSION. | $50K |
| Aug 20, 2018 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG15CR63C | 541330 | IGF::CT::IGF THE PURPOSE OF THIS CONTRACT IS FOR ENGINEERING SUPPORT SERVICES FROM HONEYBEE ROBOTICS. THE CONTRACTOR WILL PROVIDE SUSTAINING ENGINEERING SUPPORT FOR THE SAM/SMS DURING NOMINAL OPERATIONS OF THE SAM PAYLOAD, ANOMALOUS OPERATIONS OF THE SAM PAYLOAD, AND FOR SPECIAL OPERATIONS AND END-OF-LIFE ANALYSIS DURING THE MSL EXTENDED MISSION. | $50K |
| Jun 29, 2018 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA16BD69C | 541712 | IGF::OT::IGF SBIR PHASE III - ATACAMA ROVER ASTROBIOLOGY DRILLING STUDIES (ARADS) PROJECT | $30K |
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