Federal Contractor Profile
Honeybee Robotics, LTD.
$108.3M obligated·69 awards·4 agencies·9 NAICS
Federal Contracts
Showing contracts 101–150 of 161 total. Sorted by action date, most recent first. Excludes $0 modifications.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Jun 20, 2018 | Department of DefenseW6QK ACC-APG ADELPHI | 0001 | 334516 | IGF::OT::IGF A-DCP SYSTEM SUSTAINMENT SUPPORT SERVICES | $12K |
| May 15, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P1776 | 541715 | DESIGN, FABRICATION, AND TEST OF A SAMPLE CAROUSEL FOR THE LUNAR SURFACE | $15K |
| May 3, 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. | $150K |
| Mar 20, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CK04C | 541712 | IGF::OT::IGF A PHASE III SBIR CONTRACT IS REQUIRED TO INTEGRATE AND REMOTELY OPERATED AN EXISTING SBIR-DEVELOPED DRILL DURING A SEPTEMBER, 2015 INTEGRATED TESTAT JSC. THE SBIR PHASE III CONTRACT IS ALSO REQUIRED TO DEVELOP AN ENGINEERING TEST UNIT THAT MEETS THE DEFINITION OF TRL 6 FOR THE RESOURCE PROSPECTOR MISSION. DELIVERABLES FOR THE BASE YEAR OF THE CONTRACT INCLUDE INTEGRATION AND TESTING OF A TERRESTRIALLY FUNCTIONING DRILL WITH A ROVER IN SEPTEMBER, 2015 AT JSC, ENGINEERING TEST UNIT DRILL MOTOR SPECIFICATION AND DESIGN, VIBRATION TESTING OF DRILL WITH RESULTS SUBMISSION, PROCUREMENT OF MOTORS AND EMI TESTING OF THEM WITH RESULTS SUBMISSION. THE OPTION YEAR DELIVERABLES INCLUDE A CRITICAL DESIGN REVIEW PACKAGE, FABRICATION OF A TRL 6 DRILL FOR RESOURCE PROSPECTOR, AND ENVIRONMENTAL TESTING RESULTS. | $180K |
| Feb 21, 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 |
| Jan 12, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CK07C | 541712 | IGF::OT::IGF IN PHASE 2 WE WILL DEVELOP A FULLY INTEGRATED, AUTONOMOUS FREE-FLYING ROBOTIC SYSTEM BASED ON A COMMERCIAL SKYJIB QUADCOPTER, AND DEMONSTRATE FLYING STRAIGHT AND LEVEL TO A TARGET LOCATION, ACQUISITION OF ROCK AND REGOLITH SAMPLES, AND RETURN TO THE POINT OF ORIGIN. THE WORK PLAN FOR PHASE 2 IS AS FOLLOWS: 1. COMPLETION OF THE GUIDANCE, NAVIGATION, CONTROL, VISION, AND SAMPLE ACQUISITION SUBSYSTEMS. 2. INTEGRATION OF ALL THE PAYLOAD ELEMENTS AT ERAU AND SYSTEM LEVEL CHECK OUT 3. DEMONSTRATION OF THE ENTIRE SYSTEM AT NASA KSC 4. FIELD DEPLOYMENT AT ANALOG LOCATION | $400K |
| Dec 6, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CK04C | 541712 | IGF::OT::IGF A PHASE III SBIR CONTRACT IS REQUIRED TO INTEGRATE AND REMOTELY OPERATED AN EXISTING SBIR-DEVELOPED DRILL DURING A SEPTEMBER, 2015 INTEGRATED TESTAT JSC. THE SBIR PHASE III CONTRACT IS ALSO REQUIRED TO DEVELOP AN ENGINEERING TEST UNIT THAT MEETS THE DEFINITION OF TRL 6 FOR THE RESOURCE PROSPECTOR MISSION. DELIVERABLES FOR THE BASE YEAR OF THE CONTRACT INCLUDE INTEGRATION AND TESTING OF A TERRESTRIALLY FUNCTIONING DRILL WITH A ROVER IN SEPTEMBER, 2015 AT JSC, ENGINEERING TEST UNIT DRILL MOTOR SPECIFICATION AND DESIGN, VIBRATION TESTING OF DRILL WITH RESULTS SUBMISSION, PROCUREMENT OF MOTORS AND EMI TESTING OF THEM WITH RESULTS SUBMISSION. THE OPTION YEAR DELIVERABLES INCLUDE A CRITICAL DESIGN REVIEW PACKAGE, FABRICATION OF A TRL 6 DRILL FOR RESOURCE PROSPECTOR, AND ENVIRONMENTAL TESTING RESULTS. | $70K |
| Nov 28, 2017 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA16BD69C | 541712 | IGF::OT::IGF SBIR PHASE III - ATACAMA ROVER ASTROBIOLOGY DRILLING STUDIES (ARADS) PROJECT | $87K |
| Sep 29, 2017 | Department of DefenseW6QK ACC-APG ADELPHI | 0001 | 334516 | IGF::OT::IGF A-DCP SYSTEM SUSTAINMENT SUPPORT SERVICES | $20K |
| Sep 28, 2017 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | 80GSFC17C0060 | 541712 | CONCEPT DEVELOPMENT, DEFINITION, DESIGN (INCLUDING MODELING), DEVELOPMENT, TESTING, ANALYSIS, TROUBLESHOOTING, DATA INTERPRETATION, REPORTING/PRESENTATION, AND GENERAL TEAM COMMUNICATION SUPPORT, IN THE AREA OF PRECISION SOLID SAMPLE HANDLING SYSTEMSF OR EUROPAN MOLECULAR INDICATORS OF LIFE INVESTIGATION (EMILI) | $299K |
| Sep 13, 2017 | 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. | $120K |
| Sep 8, 2017 | Department of DefenseFA9453 AFRL RVK | FA945310C0065 | 541712 | TORC: MODULAR CMG TECHNOLOGIES FOR SMALL SATELLITES | $31K |
| Sep 7, 2017 | 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. | $109K |
| Aug 28, 2017 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX16C0010 | 541712 | IGF::OT::IGF PERCUSSIVE/AUTOMATED DCP RESEARCH AND DEVELOPMENT | $269K |
| Aug 9, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CK04C | 541712 | IGF::OT::IGF A PHASE III SBIR CONTRACT IS REQUIRED TO INTEGRATE AND REMOTELY OPERATED AN EXISTING SBIR-DEVELOPED DRILL DURING A SEPTEMBER, 2015 INTEGRATED TESTAT JSC. THE SBIR PHASE III CONTRACT IS ALSO REQUIRED TO DEVELOP AN ENGINEERING TEST UNIT THAT MEETS THE DEFINITION OF TRL 6 FOR THE RESOURCE PROSPECTOR MISSION. DELIVERABLES FOR THE BASE YEAR OF THE CONTRACT INCLUDE INTEGRATION AND TESTING OF A TERRESTRIALLY FUNCTIONING DRILL WITH A ROVER IN SEPTEMBER, 2015 AT JSC, ENGINEERING TEST UNIT DRILL MOTOR SPECIFICATION AND DESIGN, VIBRATION TESTING OF DRILL WITH RESULTS SUBMISSION, PROCUREMENT OF MOTORS AND EMI TESTING OF THEM WITH RESULTS SUBMISSION. THE OPTION YEAR DELIVERABLES INCLUDE A CRITICAL DESIGN REVIEW PACKAGE, FABRICATION OF A TRL 6 DRILL FOR RESOURCE PROSPECTOR, AND ENVIRONMENTAL TESTING RESULTS. | $100K |
| Jul 14, 2017 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | 80HQTR17C0006 | 541712 | IGF::OT::IGFRESEARCH AND DEVELOPMENT INTEGRATED SAMPLE ACQUISITION DRILL AND PNEUMATIC SAMPLE DELIVERY FOR OCEAN WORLDS. ONE OF THE MOST PRESSING QUESTIONS IN EXPLORATION IS WHETHER LIFE EXISTS OR EXISTED ANYWHERE ELSE IN THE UNIVERSE. WATER IS A CRITICAL PREREQUISITE FOR LIFE AS WE KNOW IT, THUS TARGETS FOR EXTRATERRESTRIAL LIFE ARE BODIES THAT HAVE OR HAD LIQUID WATER, I.E. OCEAN WORLDS SUCH AS TITAN OR EUROPA. DUE TO THE LARGE RADIATION FLUXES AT EUROPA, OR THE POSSIBILITY FOR BURIAL BY AEOLIAN SEDIMENT AT TITAN, THE SEARCH FOR LIFE DEMANDS THE CAPABILITY TO SAMPLE SUBSURFACE LOCATIONS. | $1.3M |
| Jun 14, 2017 | 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. | $150K |
| Jun 9, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CK08P | 541712 | IGF::OT::IGF PRIOR TO HUMAN ARRIVAL TO THE MOON OR MARS, A CERTAIN AMOUNT OF INFRASTRUCTURE WILL BE REQUIRED IN ORDER TO ENSURE SUCCESS OF THE OVERALL GOALS OF THE MISSION. SUCH INFRASTRUCTURE WILL INCLUDE SOME TYPE OF LANDING PADS. IN ORDER TO REDUCE THE VOLUME/MASS OF CONSTRUCTION MATERIALS TO BE TRANSPORTED FROM EARTH, IT WILL BE CRITICAL TO UTILIZE IN-SITU RESOURCES AS THE MAIN CONSTRUCTION MATERIAL. REGOLITH SEEMS TO BE THE MOST LOGICAL CHOICE GIVEN ITS ABUNDANCE AND EASY ACCESS. THE PROPOSED TECHNOLOGY WOULD ALLOW FOR THE ROBOTIC CONSTRUCTION OF CRITICAL STRUCTURES IN-SITU USING NATIVE RESOURCES. IN PHASE I WE THEREFORE PROPOSE TO: DETERMINE THE IDEAL SHAPES FOR THE BUILDING BLOCKS THAT WILL ALLOW MECHANICAL JOINTING AND CONSTRUCTION OF HORIZONTAL (LANDING PADS, ROADS, ETC.) AND VERTICAL (HABITAT, SHELTER, ETC.) STRUCTURES. MANUFACTURE THE MOLDS TO FABRICATE THESE BUILDING BLOCKS. FINE TUNE THE SINTERING PROCESS (THERMAL PROFILE) TO ENSURE REPEATABILITY OF THE FABRICATION OF THE MATERIAL. PRODUCE PROTOTYPE BUILDING BLOCKS AND TEST THEIR STRUCTURAL PROPERTIES AND STRENGTH OF THE JOINTS. DEVELOP THE ROBOTIC CONCEPT FOR MAKING THE HORIZONTAL AND VERTICAL STRUCTURES. DESIGN A HORIZONTAL AND A VERTICAL STRUCTURE FOR FABRICATION DURING PHASE II. | $119K |
| Jun 9, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CP42P | 541712 | IGF::OT::IGF THE MAIN OBJECTIVE OF THE PROPOSED WORK IS TO DEVELOP A ROBUST AND EFFECTIVE SAMPLE ACQUISITION SYSTEM FOR THE EUROPA LANDER CALLED THE EUROPA DRUM SAMPLER (EDUS). THE PROPOSED DRUM SAMPLING SYSTEM IS BASED ON A TERRESTRIAL ROADHEADER DESIGN AND INCLUDES A THWACKER THAT GENERATES PERCUSSIVE VIBRATIONS DURING ROTARY EXCAVATION. ALL COMPONENTS WILL BE DESIGNED TO WITHSTAND DRY HEAT MICROBIAL REDUCTION AS WELL AS PLANETARY PROTECTION REQUIREMENTS. THE EDUS' STRUCTURAL COMPONENTS INCLUDE A SUPPORT BOOM, A BUFFER PLATE, AND A CUTTER HEAD. THE SUPPORT BOOM IS HOLLOW AND ITS POSITION AND LENGTH CAN BE ADJUSTED DEPENDING ON THE REQUIRED EXCAVATION DEPTH AND VOLUME ON THE LANDER. FOR LAUNCH, THE BOOM WILL BE COMPRESSED AND THEN SPRING-EXTENDED UPON LANDING. A SPRING LOADED BOOM HAS AN ADDED ADVANTAGE OF MITIGATING THWACKER VIBRATIONS TO THE ROBOTIC ARM. THE BUFFER PLATE IS ALSO A STRUCTURAL MEMBER WHOSE MAIN PURPOSE IS TO PREVENT CHIPS FROM FALLING OUT. THE CUTER HEAD IS THE CENTRAL PART OF THE SYSTEM. THE CUTTER HEAD HAS BEEN DESIGNED IN THE SHAPE OF A TYPICAL CYLINDRICAL PRESSURE VESSEL. THE TEETH ARE PLACED ON ALL ROTATING SURFACES, INCLUDING THE CONVEX SIDES. THIS SHAPE CAN DEAL WITH A RANGE OF SURFACE TOPOGRAPHIES FROM FLAT TO VERY JAGGED. THE TEETH ARE VERY SHARP TO REDUCE CUTTING FORCES AND ARE MADE OF CARBIDE TO INCREASE LONGEVITY. THE CUTTER HEAD ALSO INCLUDES A RING OF TEETH WHICH MAKE UP THE THWACKER RATCHET. THWACKING WILL REDUCE CUTTING FORCES AND AID IN SAMPLE DELIVERY. | $119K |
| Jun 6, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CA33P | 541712 | IGF::OT::IGF CURRENTLY, NO UNIVERSAL ELECTROMECHANICAL ENGAGEMENT INTERFACE EXISTS FOR FREE-FLYING ROBOTS, LIMITING THEIR ABILITY TO DOCK, PERCH, RECHARGE, CHANGE TOOLS, MANIPULATE PAYLOADS, AND ASSEMBLE IN MODULAR STRUCTURES FOR INTRAVEHICULAR, EXTRAVEHICULAR, AND PLANETARY SURFACE OPERATIONS. HONEYBEE ROBOTICS (HONEYBEE) PROPOSES TO DEVELOP A UNIVERSAL DOCKING INTERFACE (UDI) THAT PROVIDES A COMMON ELECTROMECHANICAL CONNECTION ARCHITECTURE FOR FREE-FLYING ROBOTS. THE UDI WILL ENHANCE CAPABILITIES TO MOUNT AND MANIPULATE TOOLS, SENSORS, PAYLOADS; DOCK FOR POWER AND DATA TRANSFER; PERCH FOR SHORT- OR LONG-TERM STORAGE; AND CREATE NEW MODULAR STRUCTURES FOR INTRAVEHICULAR, EXTRAVEHICULAR, AND SURFACE TASKS IN SUPPORT OF COMMERCIAL OPERATIONS AND HUMAN SPACEFLIGHT. THE UDI WILL BE BASED ON HONEYBEE'S EXISTING SOLUTIONS FOR ROBOTIC SATELLITE SERVICING AND PLANETARY ROVER RECHARGE , MODIFIED TO MEET NASA'S SPACE TECHNOLOGY MISSION DIRECTORATE (STMD) HUMAN EXPLORATION TELEROBOTICS REQUIREMENTS. THIS RELIABLE PLUG-AND-PLAY DOCKING AND MANIPULATION INTERFACE WILL PROVIDE AN ELECTROMECHANICAL QUICK-CONNECT/DISCONNECT FOR TOOLS, SENSORS, AND OTHER PAYLOADS, AS WELL AS ENABLING TRULY MODULAR ASSEMBLY IN MICROGRAVITY. THE PROPOSED PHASE 1 EFFORT WILL PERFORM A DETAILED INVESTIGATION OF TOOL CHANGE, SENSOR PAYLOAD INTERFACE, MANIPULATION AND DOCKING REQUIREMENTS FOR FREE-FLYING ROBOTS SUPPORTING MISSIONS ON-ORBIT, TO MARS, THE MOON, OR NEOS. INTERFACE REQUIREMENTS SUCH AS MATE/DE-MATE CYCLES, STIFFNESS, STRENGTH, REPEATABILITY, MISALIGNMENT TOLERANCE, HUMAN SAFETY, DEBRIS MITIGATION, AND ELECTRICAL FEED THROUGH CHARACTERISTICS WILL BE DERIVED THROUGH CONTACT WITH POTENTIAL END USERS TO CHARACTERIZE POTENTIAL USE CASES AND FUTURE MISSION PAYLOADS. | $119K |
| Jun 6, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CP43P | 541712 | IGF::OT::IGF ALTHOUGH HONEYBEE AND OTHERS HAVE MADE HUGE ADVANCES IN DEVELOPING MECHANISMS, MOTORS, AND ELECTRONICS FOR USE IN HIGH TEMPERATURE/HIGH PRESSURE ENVIRONMENTS SUCH AS THE SURFACE OF VENUS (460C), CERTAIN TYPES OF CRITICAL ELECTRONIC AND SENSING TECHNOLOGIES ARE INHERENTLY TEMPERATURE SENSITIVE. THE LACK OF HIGH TEMPERATURE TOLERAT CAMERAS AND OPTICAL SENSORS HAS, TO DATE, PREVENTED UP-CLOSE IN-SITU ANALYSIS OF THE VENUSIAN SURFACE. IN THIS SBIR WE WILL CLOSE THAT TECHNOLOGY GAP BY DEVELOPING A MINIATURE STIRLING COOLER, SUITABLE FOR INTEGRATION WITH A SENSOR PACKAGE AT THE END OF AN EFFECTOR OR ROBOT ARM, WHICH IS CAPABLE OF KEEPING CONVENTIONAL ELECTRONICS COOL OUTSIDE OF THE SPACECRAFT BODY IN THE HIGH TEMPERATURE VENUS ENVIRONMENT. THIS ADVANCE WOULD VASTLY EXPAND THE LIST OF TECHNOLOGIES WHICH CAN BE DEPLOYED ON THE SURFACE OF VENUS, AND CORRESPONDINGLY ADVANCE THE TYPES OF SCIENCE THAT CAN BE PERFORMED. WE WILL DEMONSTRATE IN PHASE-I A BRASSBOARD SYSTEM AT HIGH TEMPERATURE, FOLLOWED BY A FLIGHT LIKE SYSTEM IN FULL VENUSIAN CONDITIONS IN PHASE-II. | $119K |
| Jun 6, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CP44P | 541712 | IGF::OT::IGF WE PROPOSE TO BUILD AND CRITICALLY TEST THE INSTRUMENTED BIT FOR IN-SITU SPECTROSCOPY (IBISS), A NOVEL SYSTEM FOR IN-SITU, RAPID ANALYSES OF PLANETARY SUBSURFACE MATERIALS (FIG 2.1). IBISS WILL PROVIDE A RAPID AND UNAMBIGUOUS CHEMICAL/MINERALOGICAL CHARACTERIZATION OF SUBSURFACE MATERIALS BY INTEGRATING AN INNOVATIVE, MINIATURE LIBS (LASER-INDUCED BREAKDOWN SPECTROSCOPY) PROBE WITH A DRILL BIT. SPECIFICALLY, WE WILL: 1)DESIGN AND ASSEMBLE AN IBISS BREADBOARD SYSTEM (MK 1) AND VALIDATE THE OPTICAL CIRCUIT: THROUGH MODEL SIMULATION AND EXPERIMENTAL WORK, WE WILL INVESTIGATE THE PERFORMANCE OF THE VARIOUS OPTICAL ELEMENTS. WE WILL DETERMINE THE FIGURES OF MERIT OF THE LASER, OPTICAL FIBER, AND LENSES. WE WILL USE COTS OR MODIFIED COTS FOR ALL OPTICAL, MECHANICAL, AND ELECTRONIC SYSTEMS. 2) DESIGN AND ASSEMBLE AN IBISS MINIATURIZED SYSTEM (MK 2), INTEGRATE IT WITH THE DRILL BIT, AND BENCH TEST IT: WE WILL PERFORM COMPONENT INTEGRATION AND SYSTEM TESTING. WE WILL DETERMINE SCIENTIFIC PERFORMANCE PARAMETERS OF IBISS AND COMPARE THEM TO THOSE OF BENCH-TOP LIBS INSTRUMENTS AND DRILLING ENGINEERING PERFORMANCE METRICS. WE WILL USE EXISTING, CERTIFIED/ INDEPENDENTLY CHARACTERIZED SAMPLES OF LUNAR AND MARTIAN REGOLITH SIMULANT. | $120K |
| Jun 4, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CP41P | 541712 | IGF::OT::IGF THERE ARE AT LEAST TWO FUNDAMENTAL DESIGN APPROACHES ONE COULD USE WHEN TRYING TO PENETRATE THE ICY SHELL ON EUROPA AND OTHER PLANETARY BODIES: A MELT PROBE AND AN ELECTRO-MECHANICAL DRILL. A MELT PROBE USES A HOT POINT TO MELT THROUGH ICE AND PENETRATE DOWNWARD. IN THIS REGARD, IT IS A VERY SIMPLE APPROACH - IT REQUIRES A HEAT SOURCE. HOWEVER, THE POWER REQUIRED TO MELT 50-110K ICE IS 10S OF KW, OF WHICH 90% IS LOST INTO THE SURROUNDING ICE. IN ADDITION, MELT PROBES WILL NOT PENETRATE ANYTHING ELSE BUT ICE, AND IF THE HEAT IS PROVIDED BY INTEGRATED RTGS, THE PROBE WILL OVERHEAT AND MELT IF THE CONDUCTIVE PROPERTIES OF ICE CHANGE (E.G. IF ICE BECOMES POROUS, IT WILL BECOME A VERY GOOD INSULATOR). THE ELECTRO-MECHANICAL APPROACH IS AN ORDER OF MAGNITUDE MORE ENERGY EFFICIENT THAN A MELT PROBE. HOWEVER, THE DRILL NEEDS TO GET RID OF THE CUTTINGS IT IS GENERATING. THE DRILL CAN ALSO FREEZE IN-PLACE IF IT ENCOUNTERS ANY LIQUID WATER. NUMEROUS DRILLS DEPLOYED IN ANTARCTICA, FOR EXAMPLE, FROZE IN-PLACE WHILE DRILLING DOWN THE BOREHOLE, BECAUSE ICE TUNED INTO LIQUID WATER AT THE CUTTER-ICE INTERFACE. WE THEREFORE PROPOSE A HYBRID APPROACH THAT TAKES THE BEST OF BOTH WORLDS AND REDUCES RISKS POSED BY EACH OF THE OPTIONS ABOVE. SLUSH IS A HOT-POINT ELECTRO-MECHANICAL DRILL THAT CUTS THROUGH ICE USING ROTARY-PERCUSSIVE ACTION, AND MELTS CHIPS WITH ITS HOT BIT TO FORM SLUSH. THE SLUSH MOVES UP THE HOLE WHERE IT REFREEZES BEHIND THE DRILL. SLUSH IS APPROXIMATELY 14 CM IN DIAMETER AND 2.5 M LONG. BECAUSE SLUSH USES MECHANICAL ACTION TO BREAK ICE, IT IS SIGNIFICANTLY FASTER THAN A MELT PROBE AND ALSO SIGNIFICANTLY MORE EFFICIENT, SINCE SLUSH DOES NOT HAVE AS MUCH TIME TO LOOSE HEAT INTO THE SURROUNDING ICE. SINCE SLUSH USES A HAMMER DRILL, IT CAN ALSO PENETRATE MATERIAL WITH A SIGNIFICANT FRACTION OF INSOLUBLE MATERIAL (E.G. SILT). AN ADDED BENEFIT OF SLUSH IS THAT SCIENCE INSTRUMENTS CAN DRAW LIQUID DIRECTLY FROM THE OUTSIDE FOR ANALYSIS. | $119K |
| May 31, 2017 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH17CS40C | 541712 | IGF::OT::IGF THIS CONTRACT IS A RESULT OF A DOWNSELECT FROM AWARDS ISSUED AS A RESULT OF NNH15ZDA001N-S3GSI. A SUMMARY OF THE RESEARCH IS AS FOLLOWS: FUTURE ROBOTIC MISSIONS TO VENUS REQUIRE ACTUATORS FOR POWERING ROBOTIC ARMS, SAMPLING SYSTEMS, AND GIMBALS FOR THE POSITIONING OF CAMERAS AND ANTENNAS. THERE ARE MANY TYPES OF ACTUATORS (E.G. PNEUMATIC, HYDRAULIC); HOWEVER ELECTRIC ACTUATORS OFFER THE GREATEST VERSATILITY FOR SPACE MISSIONS. AN ELECTRIC ACTUATOR CONSISTS OF AN ELECTRIC MOTOR AND A POSITION SENSOR. THE ELECTRIC MOTOR CONVERTS ELECTRICAL ENERGY (ELECTRICITY) INTO MECHANICAL OUTPUT (SHAFT ROTATION). THE POSITION SENSOR, ON THE OTHER HAND, DETERMINES THE ANGULAR POSITION OF THE MOTOR SHAFT, WHICH THEN IS PROCESSED BY DRIVE ELECTRONICS TO COMMUTATE AND CONTROL THE MOTOR. BECAUSE OF THE EXTREME CONDITIONS ON THE VENUS SURFACE (92 BAR PRESSURE, 462 C TEMPERATURE, AND SUPERCRITICAL CO2 ATMOSPHERE), CONVENTIONAL ACTUATORS WILL NOT BE ABLE TO FUNCTION PROPERLY, OR AT ALL. THE MAIN CHALLENGES PERTAIN TO CHANGES IN ELECTRICAL PROPERTIES LIKE AN INCREASE IN WIRE RESISTANCE (LEADING TO GREATER LOSSES), CHANGES IN MAGNETIC PROPERTIES LIKE PERMEABILITY AND RETENTIVITY (LEADING TO DEMAGNETIZATION OF MAGNETS), AND CHANGES IN PHYSICAL PROPERTIES SUCH AS LINEAR EXPANSION, DECREASE IN STRENGTH, INCREASE IN FRICTION, AND ACCELERATED OXIDATION. HONEYBEE HAS DEVELOPED A 48V BRUSHLESS DC MOTOR (BLDC) AND CUSTOM POSITION SENSOR CALLED THE PULSED INJECTION POSITION SENSOR (PIPS) FOR MOTOR COMMUTATION AND FEEDBACK CONTROL. THE MOTOR AND PIPS ARE AT TECHNOLOGY READINESS LEVEL (TRL) 5. THE MAIN OBJECTIVE OF THE PROPOSED WORK IS TO MATURE THE VENUS ACTUATOR TECHNOLOGY THROUGH AN ITERATIVE PROCESS OF VENUS CHAMBER TESTING OF A TRL5 ACTUATOR, FOLLOWED BY RE-DESIGN AND FABRICATION OF A TRL6 ACTUATOR AND SUBSEQUENT VENUS CHAMBER QUALIFICATION TESTING OF THAT ACTUATOR. THE CRITICAL OBJECTIVES TO BE MET ARE AS FOLLOWS: 1. DESIGN OF A MOTOR WITH 28V WINDINGS, 2. INCREASE PIPS RESOLUTION (THIS WILL MAKE MOTOR MORE EFFICIENT AND ALLOW ACTUATOR TO BE USED FOR PRECISION POSITIONING SYSTEMS ROBOTIC ARMS AND GIMBALS), 3. ESTABLISH REPRODUCIBLE PROCEDURES, STANDARDS, AND GUIDELINES FOR FABRICATING, ASSEMBLY, TEST, AND INSPECTION OF VENUS ACTUATORS (CURRENTLY ACTUATORS ARE HAND CRAFTED BY SELECTED ENGINEERS THIS KNOWLEDGE NEEDS TO BE CAPTURED SO THAT ANY SKILLED PERSON WILL BE ABLE TO FABRICATE VENUS ACTUATOR WHENEVER NEEDED). THIS EFFORT WILL BE ACHIEVED IN ONE YEAR PERIOD TO ENABLE TECHNOLOGY INFUSION INTO THE NEW FRONTIERS (NF) VENUS IN SITU EXPLORER (VISE) MISSION. | $300K |
| May 5, 2017 | 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 |
| Apr 21, 2017 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA14AB24C | 541711 | IGF::OT::IGF RESEARCH AND DEVELOPMENT FOR BIOTECH FOR (ICEBITE) | $25K |
| Apr 21, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CA13C | 541712 | IGF::OT::IGF THE FIRST LUNAR SOFT LANDER WAS SURVEYOR 1, IN 1966. IT HAD THREE TASKS, ONE OF WHICH WAS TO DETERMINE LUNAR SURFACE BEARING STRENGTH. KNOWING THE STRENGTH OF THE LUNAR SURFACE WAS THE SINGLE MOST IMPORTANT PARAMETER - THIS ESSENTIALLY DICTATED WHETHER LANDING ON THE MOON WITH SIGNIFICANT MASS LIKE THAT OF THE LUNAR MODULE WAS IN FACT FEASIBLE. DURING THE APOLLO PROGRAM, ASTRONAUTS USED A SELF-RECORDING PENETROMETER (SRP) TO MEASURE GEOTECHNICAL PROPERTIES OF LUNAR SOIL. ONE OF THE INSTRUMENTS OF THE 1970 AND 1976 SOVIET LUNOKHOLD ROVERS INCLUDED A SHEAR VANE GEOTECHNICAL TOOL. SINCE 1976, THERE HAVE BEEN NO GEOTECHNICAL INSTRUMENTS DEPLOYED ON ANY PLANETARY BODY. OUR INTENT IS TO PROVIDE A GEOTECHNICAL TOOL THAT WILL ALLOW US TO BEGIN EXPLORATION AGAIN. THE APOLLO PENETROMETER APPROACH WAS EXCELLENT FOR GREATER DEPTHS, WHILE THE SOVIET APPROACH WORKED WELL FOR THE NEAR-SURFACE. WE COMBINE THE TWO APPROACHES INTO WHAT WE CALL THE STINGER, A PERCUSSIVE SHEAR VANE PENETROMETER CAPABLE OF MEASURING NEAR-SURFACE AND SUBSURFACE SOIL PROPERTIES TO A DEPTH OF 50 CM OR GREATER. THE OBJECTIVES OF PHASE I WERE TO DESIGN AND BUILD A SIMPLIFIED BREADBOARD STINGER GEOTOOL AND TEST IT IN LUNAR AND MARTIAN SOIL SIMULANTS TO DETERMINE ITS APPLICABILITY FOR ROBOTIC AND HUMAN MISSIONS. THE RESULTS OF PHASE I SHOW NOT ONLY ACCURACY AND PRECISION IN DETERMINING SOIL PROPERTIES, BUT ALSO FLAWLESS EXECUTION OF THE BREADBOARD DESIGN. THIS PAVES THE WAY FOR THE PHASE II EFFORT. THE PRIMARY OBJECTIVE OF THE PROPOSED PHASE II EFFORT IS TO DEVELOP A COMPACT IMPACT SHEAR VANE PENETROMETER - THE STINGER - UP TO TRL5/6 TO DETERMINE SOIL PHYSICAL PROPERTIES NEAR THE SURFACE AND DOWN TO 50 CM DEPTH. IN CONJUNCTION WITH THE INSTRUMENT DEVELOPMENT, A SOIL MECHANICS MODEL WILL BE FORMULATED BASED ON LABORATORY TESTS WITH THE INSTRUMENTS, IN SOIL SIMULANTS, AND IN VACUUM CONDITIONS. | $723K |
| Apr 21, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CL09C | 541712 | IGF::OT::IGF THE SIZE OF SPACE SYSTEMS IS CURRENTLY LIMITED TO PAYLOAD ENVELOPES OF EXISTING LAUNCH VEHICLES. DUE TO THIS AND THE CUSTOMIZED NATURE OF SATELLITES, EXISTING SPACE SYSTEMS ARE VERY COSTLY TO STAND UP. NOR ARE THEY DESIGNED FOR REPAIR, UPGRADE, OR REUSE TO AMORTIZE THE COST OVER MULTIPLE MISSIONS. AS MISSIONS GET FURTHER FROM LOW-EARTH ORBIT (LEO), THE DANGERS OF HUMAN EXTRA-VEHICULAR ACTIVITY (EVA) FOR MANUAL ON-ORBIT ASSEMBLY OR REPAIR INCREASES, MAKING ROBOTIC ASSEMBLY OF LARGE STRUCTURES VERY DESIRABLE. HONEYBEE ROBOTICS (HONEYBEE) PROPOSES TO CONTINUE DEVELOPMENT OF THE STRUT ATTACHMENT SYSTEM (SAS) THAT PROVIDES A COMMON ELECTROMECHANICAL CONNECTION ARCHITECTURE FOR ROBOTIC ON-ORBIT STRUCTURES ASSEMBLY. THE SAS ENABLES THE CREATION OF NETWORKED SPACE FRAME STRUCTURES WITH A STRUT/NODE ARCHITECTURE; ENABLE PAYLOAD DOCKING TO THOSE STRUCTURES FOR POWER AND DATA TRANSFER; AND ENABLE THE CREATION OF REUSABLE, SERVICEABLE, AND UPGRADABLE VEHICLE SYSTEMS IN SUPPORT OF LOWER COST SPACE EXPLORATION. THE PROPOSED PHASE 2 WORK PLAN IS TO DEVELOP THE STRUT ATTACHMENT SYSTEM TO TRL 4 WITH A ROBOTIC ASSEMBLY DEMONSTRATION OF A NETWORKED STRUCTURE SHOWING POWER AND DATA NETWORK CONNECTIVITY. THE SAS WILL CONSIST OF THE STRUT ATTACHMENT MECHANISM, STRUT RECEPTACLE, STRUT, AND NODE. PHASE 2 WILL INCLUDE FURTHERING THE DEVELOPMENT OF THE STRUT ATTACHMENT MECHANISM AND STRUT RECEPTACLE, AS WELL AS BEGINNING DEVELOPMENT OF THE STRUT AND EMBEDDED SYSTEMS THAT ENABLE A SELF-HEALING POWER AND COMMUNICATIONS NETWORK ACROSS AN ASSEMBLED STRUCTURE. THE PHASE 1 PROJECT RESULTED IN A STRUT ATTACHMENT MECHANISM AND STRUT RECEPTACLE AT TRL 3 AT THE END OF PHASE 1 AND PHASE 2 PLANS WILL BRING THE SAS (STRUT ATTACHMENT MECHANISM, STRUT RECEPTACLE, STRUT, AND EMBEDDED SYSTEMS) TO TRL 4 AT THE END OF PHASE 2. | $726K |
| Apr 10, 2017 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX16C0010 | 541712 | IGF::OT::IGF PERCUSSIVE/AUTOMATED DCP RESEARCH AND DEVELOPMENT | $565K |
| Mar 28, 2017 | 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. | $16K |
| Jan 13, 2017 | 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. | $100K |
| Nov 18, 2016 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA16BD69C | 541712 | IGF::OT::IGF SBIR PHASE III - ATACAMA ROVER ASTROBIOLOGY DRILLING STUDIES (ARADS) PROJECT | $145K |
| Nov 2, 2016 | 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. | $90K |
| Oct 18, 2016 | National Aeronautics and Space AdministrationNASA AMES RESEARCH CENTER | NNA14AB24C | 541711 | IGF::OT::IGF RESEARCH AND DEVELOPMENT FOR BIOTECH FOR (ICEBITE) | $25K |
| Sep 30, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CK17C | 541712 | IGF::OT::IGF THE WORLD IS NOT ENOUGH (WINE) IS A NEW GENERATION OF CUBESATS THAT TAKE ADVANTAGE OF ISRU TO EXPLORE SPACE. THE WINE TAKES ADVANTAGE OF EXISTING CUBESAT TECHNOLOGY AND COMBINES IT WITH 3D PRINTING TECHNOLOGY AND AN IN SITU RESOURCE UTILIZATION (ISRU) WATER EXTRACTION SYSTEM. 3D PRINTING ENABLES DEVELOPMENT OF STEAM THRUSTERS (HIGHER ISP THAN COLD GAS) AS WELL AS TANKS THAT FIT WITHIN THE AVAILABLE SPACE WITHIN THE CUBESAT. THE ISRU MODULE CAPTURES AND EXTRACTS WATER, AND TAKES ADVANTAGE OF THE HEAT GENERATED BY THE CUBESAT ELECTRONICS SYSTEM WITH SUPPLEMENTAL POWER FROM SOLAR CHARGED BATTERIES. THE WATER IS STORED IN A STEAM THRUSTER TANK AND USED FOR PROPULSION. THUS, THE SYSTEM CAN USE THE WATER THAT IT HAS JUST EXTRACTED AS FUEL TO FLY TO ANOTHER LOCATION. THE WINE IS IDEALLY SUITED AS A PROSPECTING MISSION AND RECONNAISSANCE MISSION BEFORE THE MINING/EXPLORATION MISSIONS ARE LAUNCHED. | $750K |
| Sep 30, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CP10C | 541712 | IGF::OT::IGF DURING PHASE 1, WE INVESTIGATED A NUMBER OF BLADE DESIGNS FOR 2, 3, AND 4 BLADE SAMPLER GEOMETRIES. WE FOUND THAT BLADES WITH SMALL APEX ANGLES CAN PENETRATE HARDER FORMATIONS WITH MUCH LOWER ENERGIES. WE PROPOSE TO DEVELOP A 3 OR 4 BLADE DESIGN FOR SAMPLING MUCH HARDER (4 MPA AND MORE) MATERIAL. DURING PHASE 2 WE WILL INITIALLY PERFORM MORE EXTENSIVE BLADE TESTING TO DETERMINE OPTIMUM DESIGN, WE WILL ALSO INVESTIGATE USE OF PYROS TO DEPLOY BLADES, BREADBOARD AND TEST FORCE NEUTRAL DEPLOYMENT AND INVESTIGATE ONE RESETTABLE VS MULTIPLE SAMPLERS ARCHITECTURES. THESE STUDIES WILL LEAD TO 3 VS 4 BLADE ARCHITECTURE STUDY (TETRAHEDRON COMET SAMPLER OR TECOS AND PYRAMID COMET SAMPLER OR PYCOS) AND DOWNSELECTION. THE TRL 4 TECOS OR PYCOS WILL THEN BE BUILD AND TESTED. THE RESULTS WILL BE USED TO DESIGN TRL 5 SYSTEM. THE TRL PROTOTYPE WILL THEN BE BUILD AND TESTED IN A RANGE OF ANALOG MATERIALS FROM 5 DOF ARM TO MIMIC 2-3 DOF TAG ARM AND SPACECRAFT MOVEMENT. | $500K |
| Sep 30, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX15CP04C | 541712 | IGF::OT::IGF UNDER PHASE 1, WE INVESTIGATED HT DRILL, HT TRENCHER, AND PNEUMATIC SAMPLE DELIVERY. WE FOUND THAT HT TRENCHER AND BLOWERBASED PNEUMATIC SYSTEM WON'T BE FEASIBLE OR CARRIED HIGH RISK ASSOCIATED WITH DEVELOPMENT OF HT CUTTER MATERIALS. ROTARY DRILL ALSO DID NOT PENETRATE HARD ROCKS. FOR PHASE 2, WE PROPOSE HT ROTARY-PERCUSSIVE DRILL AND 'SUCTION' BASED PNEUMATIC SAMPLE DELIVERY. HONEYBEE IS ALSO SUBMITTING A SEPARATE PHASE 2 FOR 3 DOF HT ARM. IF THAT PROPOSAL GETS SELECTED, THE ARM WILL DEPLOY THE DRILL AND DEPOSIT THE SAMPLE. THE PNEUMATIC SYSTEM WOULD STILL BE NEEDED TO MOVE THE SAMPLE INTO AN INSTRUMENT. WE PLAN TO DESIGN AND BUILD TRL 5 SYSTEM AND INCORPORATE HT MOTORS DEVELOPED BY HONEYBEE UNDER PRIOR SBIR PROJECTS. THE DEMONSTRATION WILL BE DONE IN A HT CHAMBER. WE WILL INVESTIGATE POSSIBILITY OF TESTING AT NASA JPL'S VENUS CHAMBER. THE DEMO WILL INCLUDE DRILLING INTO HARD ROCKS AND SAMPLE TRANSFER TO A MOCK UP INSTRUMENT. | $300K |
| Sep 9, 2016 | 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. | $76K |
| Aug 9, 2016 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX16C0010 | 541712 | IGF::OT::IGF PERCUSSIVE/AUTOMATED DCP RESEARCH AND DEVELOPMENT | $594K |
| Aug 2, 2016 | 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. | $100K |
| Aug 1, 2016 | Department of DefenseMISSILE DEFENSE AGENCY (MDA) | HQ014716C7749 | 541712 | IGF::OT::IGF SBIR PHASE II RESEARCH&DEVELOPMENT | $1.5M |
| Jul 8, 2016 | Department of DefenseW6QK ACC-APG ADELPHI | W911QX16C0010 | 541712 | IGF::OT::IGF PERCUSSIVE/AUTOMATED DCP RESEARCH AND DEVELOPMENT | $44K |
| Jun 22, 2016 | 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. | $60K |
| Jun 10, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CJ44P | 541712 | IGF::OT::IGF FUTURE HUMAN MISSIONS TO MARS, THE MOON, NEAR-EARTH OBJECTS (NEOS) AND OTHER PLANETARY BODIES WILL REQUIRE A SPACESUIT EQUIPPED WITH A COMPACT, LIGHTWEIGHT, RELIABLE, DUST TOLERANT, HIGH PRESSURE OXYGEN QUICK DISCONNECT (QD) FOR ASTRONAUT EXTRAVEHICULAR ACTIVITY. THE NEXT GENERATION OF QDS MUST TRANSFER HIGH PRESSURE OXYGEN (HPO2) BETWEEN THE VEHICLE AND SPACE SUITS UNDER ADVERSE CONDITIONS, INCLUDING AN EXTREME RANGE OF TEMPERATURES, IN A HIGH VACUUM, AND AMID PERVASIVE DUST. CURRENTLY, NO QDS DELIVER O2 AT SUFFICIENT PRESSURE, NOR ARE THEY ABLE TO MATE IN THE PRESENCE OF DUST. HONEYBEE ROBOTICS PROPOSES TO DEVELOP A DUST TOLERANT, HIGH PRESSURE OXYGEN QUICK DISCONNECT SUITABLE FOR ADVANCED SPACESUIT AND AIRLOCK APPLICATIONS. THIS SYSTEM WILL INTEGRATE FORM, FIT, AND FUNCTION OF EXISTING AND NEW SUBSYSTEMS FOR UMBILICAL QUICK DISCONNECTS, LEVERAGING BOTH THE DESIGN WORK COMPLETED TO-DATE BY OCEANEERING (PROVIDED BY NASA) AND THE DUST-TOLERANT QD CONNECTOR PROTOTYPES THAT HONEYBEE DEVELOPED TO TRL 6 FOR SPACESUIT APPLICATIONS FOR NASA'S CONSTELLATION PROGRAM. THESE QDS HAVE BEEN SUCCESSFULLY TESTED AT 6X10-6 MBAR COATED IN JSC-1AF LUNAR DUST SIMULANT. MATERIALS INTEGRAL TO THE DUST-TOLERANT SYSTEM CAN PERFORM ACCEPTABLY AT -160 C. THE PHASE 1 EFFORT WILL FOCUS ON MODIFICATIONS NECESSARY TO APPLY EXISTING DUST-TOLERANT ELECTRICAL CONNECTION TECHNOLOGY (US PATENT NO. 8,011,941) TO HIGH-PRESSURE OXYGEN DELIVERY. THIS WILL INCLUDE DEVELOPING AND PERFORMANCE TESTING A MODEL IN THE PRESENCE OF SIGNIFICANT AMOUNTS OF JSC-1A LUNAR SIMULANT. A SUCCESSFUL END POINT WILL DEMONSTRATE THE DESIGN'S CAPABILITY TO TRANSMIT GAS OVER THE INTERFACE AND PREVENT DUST FROM ENTERING THE GAS STREAM OVER MULTIPLE MATE/DE-MATE CYCLES. A DESIGN PATH WILL BE LAID OUT FOR PHASE 2 TO ADDRESS REMAINING TECHNICAL CHALLENGES AND CREATE HIGHER-FIDELITY HARDWARE SUITABLE FOR TESTING AT NASA. | $124K |
| Jun 10, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CL72P | 541712 | IGF::OT::IGF THE SIZE OF SPACE SYSTEMS IS CURRENTLY LIMITED TO PAYLOAD ENVELOPES OF EXISTING LAUNCH VEHICLES. DUE TO THIS AND THE CUSTOMIZED NATURE OF SATELLITES, EXISTING SPACE SYSTEMS ARE VERY COSTLY TO STAND UP. NOR ARE THEY DESIGNED FOR REPAIR, UPGRADE, OR REUSE TO AMORTIZE THE COST OVER MULTIPLE MISSIONS. AS MISSIONS GET FURTHER FROM LOW-EARTH ORBIT (LEO), THE DANGERS OF HUMAN EXTRA-VEHICULAR ACTIVITY (EVA) FOR MANUAL ON-ORBIT ASSEMBLY OR REPAIR INCREASES MAKING ROBOTIC ASSEMBLY OF LARGE STRUCTURES VERY DESIRABLE. HONEYBEE ROBOTICS (HONEYBEE) PROPOSES TO DEVELOP A STRUT ATTACHMENT SYSTEM (SAS) THAT PROVIDES A COMMON ELECTROMECHANICAL CONNECTION ARCHITECTURE FOR ROBOTIC ON-ORBIT STRUCTURES ASSEMBLY. THE SAS WILL ENABLE THE CREATION OF NETWORKED SPACE FRAME STRUCTURES WITH A STRUT/NODE ARCHITECTURE; ENABLE PAYLOAD DOCKING TO THOSE STRUCTURES FOR POWER AND DATA TRANSFER; AND ENABLE THE CREATION OF REUSABLE, SERVICEABLE, AND UPGRADABLE VEHICLE SYSTEMS IN SUPPORT OF LOWER COST SPACE EXPLORATION. THE SAS WILL LEVERAGE TECHNOLOGY THAT HONEYBEE DEVELOPED FOR ROBOTIC SATELLITE SERVICING (DARPA SATLET GRASPER TOOL | TRL-5). THE PROPOSED PHASE 1 TECHNICAL APPROACH IS TO MODIFY THE SATLET GRASPER TOOL AND RECEPTACLE DESIGNS TO INCREASE THE CONNECTION'S STRENGTH, RIGIDITY, AND POWER/DATA TRANSMISSION CAPABILITY. THE SAS WILL CONSIST OF THE STRUT ATTACHMENT MECHANISM, STRUT RECEPTACLE, AND NODE. THE PHASE 1 PROJECT WILL RESULT IN A STRUT ATTACHMENT MECHANISM AND STRUT RECEPTACLE AT TRL OF 4 AT THE END OF PHASE 1 AND TRL 5-6 AT THE END OF PHASE 2. | $124K |
| Jun 9, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CK09P | 541712 | IGF::OT::IGF THE APOLLO 15 LUNAR MODULE ROCKET PLUME EXCAVATED REGOLITH WHICH SANDBLASTED AT SPEEDS IN EXCESS OF 1000 M/S THE SURVEYOR 2 LANDER 200 M AWAY. A CURIOSITY ROVER INSTRUMENT WAS PERMANENTLY DAMAGED DURING SKYCRANE LANDING ON MARS. ANY FUTURE HUMAN SURFACE MISSIONS TO PLANETARY BODIES COVERED IN REGOLITH (E.G. MARS, MOON) WOULD NEED TO ADDRESS EJECTA CREATED DURING LANDING OR TAKEOFF. THE INTENT OF THIS PROJECT IS TO DEVELOP A FULLY ROBOTIC SYSTEM FOR BUILDING LANDING PADS ON PLANETARY BODIES. THE SYSTEM WILL EXCAVATE IN-SITU REGOLITH, SORT ROCKS ACCORDING TO NEEDED PARTICLE SIZES, AND LAYOUT A CAREFULLY DESIGNED LANDING/LAUNCH PAD APRON TO LOCK IN THE SMALL REGOLITH PARTICLES. TO THAT EXTENT, HONEYBEE/MTU PROPOSE TO DESIGN AND BUILD A ROBOTIC TOOL TO PERFORM THE FOLLOWING 3 ACTIONS: PICK UP OR EXCAVATE ROCKS, SORT THE ROCKS IN THREE SIZE RANGES, AND DEPOSIT SAID ROCKS IN THREE LAYERS WITH THE PURPOSE TO STABILIZE THE FINE REGOLITH IN THE SECONDARY APRON ZONE OF LUNAR AND MARTIAN LANDING PADS FOR REPEATED LANDINGS AND TAKE-OFFS. | $125K |
| Jun 9, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CA55P | 541712 | IGF::OT::IGF THE US CONGRESS HAS INSTRUCTED NASA TO INCLUDE A LANDER COMPONENT IN THE NEXT EUROPA MISSION. THE MISSION HAS A TARGET LAUNCH DATE OF 2022, AND ITS PRIMARY GOAL WILL BE TO SEARCH EUROPA'S ICY SURFACE FOR EVIDENCE OF LIFE THAT MAY PERSIST WITHIN THE ICE SHELL OR SUBSURFACE OCEAN. THE EUROPA LANDER STUDY SPECIFICALLY RECOMMENDS A COMBINATION OF A MASS SPECTROMETER AND A RAMAN SPECTROMETER TO INVESTIGATE EUROPA'S HABITABILITY. CURRENT FLIGHT PROTOTYPES, BY DESIGN, EXISTING PLANETARY RAMAN INSTRUMENTS CANNOT DETECT ORGANIC COMPOUNDS ON EUROPA DOWN TO THE REQUIRED 1 PPB. WE PROPOSE TO BUILD AND CRITICALLY TEST THE IN-SITU SPECTROSCOPIC EUROPA EXPLORER (ISEE), A NEXT-GENERATION PROTOTYPE OF A COMPACT, ARM-MOUNTED RAMAN SPECTROMETER. ISEE UTILIZES AN INNOVATIVE COMBINATION OF LIGHT SOURCE, ADAPTIVE SPATIAL CODING OPTICS, AND DETECTOR. IT INTEGRATES A HIGH-PERFORMANCE SIGNAL PROCESSOR AND DATA PROCESSING ALGORITHMS THAT ENABLE UNPRECEDENTED MEASUREMENTS: IN-SITU CHEMICAL IDENTIFICATION AND QUANTITATION OF COMPLEX ORGANIC COMPOUNDS, INCLUDING PRE-BIOTIC COMPOUNDS; BIOMOLECULES; MINERALS; AND VOLATILES. ISEE ALSO PROVIDES SAMPLE CONTEXT, INCLUDING ICE COMPOSITION, CRYSTALLINITY, AND ICE PHASE DISTRIBUTION. OUR PROJECT IS RESPONSIVE TO 'T8.03 DETECTION TECHNOLOGIES FOR EXTANT OR EXTINCT LIFE FOR USE ON ROBOTIC MISSIONS.' OUR PHASE I R&D WILL DEVELOP AND INTEGRATE KEY SUBSYSTEMS OF ISEE AND EVALUATE ITS PERFORMANCE USING STANDARDS AND NATURAL SAMPLES, PARTICULARLY WITH RESPECT TO THE DETECTION OF ORGANIC COMPOUNDS AND BIOMARKERS. WE WILL DEMONSTRATE THE FEASIBILITY OF ISEE TO PERFORM QUANTITATIVE ANALYSIS OF ORGANIC CONTENT, MINERALS, AND VOLATILES AT OR<1 PPB IN SOLID MATRICES. THE TECHNICAL OBJECTIVES OF PHASE I ARE: 1) VALIDATE ISEE'S OPTICAL PATH; 2) BUILD AN ISEE BREADBOARD SYSTEM; 3) DETERMINE PERFORMANCE PARAMETERS; 4) DEMONSTRATE THE CAPABILITY TO DETECT ORGANIC COMPOUNDS AND BIOMARKERS IN BIOLOGICALLY LEAN NATURAL SAMPLES. | $120K |
| Jun 9, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CG30P | 541712 | IGF::OT::IGF FUTURE VENUS OR COMET MISSION ARCHITECTURES MAY FEATURE ROBOTIC SAMPLING SYSTEMS COMPRISED OF A SAMPLING TOOL AND DEPLOYMENT MECHANISM. SINCE 2005, HONEYBEE HAS BEEN DEVELOPING EXTREMETEMPERATURE MOTORS, POSITION SENSORS, BRAKES, AND GEARBOXES, RESULTING IN MULTIPLE SUCCESSFUL DEMONSTRATIONS OF COMPONENT-LEVEL TECHNOLOGIES UNDER VENUS-LIKE ENVIRONMENTAL CONDITIONS. AN IMPORTANT NEXTSTEP TOWARD A VIABLE VENUS OR COMET SURFACE MISSION ARCHITECTURE IS TO COMBINE THESE COMPONENTS AND RAISE THE TRL OF THE TOTAL SAMPLING SYSTEM INCLUDING THE DEPLOYMENT MECHANISM. THE PROPOSED WORK WILL LEVERAGE COMPONENT DEVELOPMENT TO DATE BY INTEGRATING EXTREME TEMPERATURE ACTUATORS WITH FUNCTIONAL ELEMENTS TO DEMONSTRATE A COMPLETE MULTI-DOF DEPLOYMENT MECHANISM SUITABLE FOR CANDIDATE SURFACE MISSIONS. | $124K |
| Jun 5, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CA17P | 541712 | IGF::OT::IGF FLAWLESS OPERATION OF PLANETARY MOBILITY SYSTEMS, EXCAVATION, MINING AND ISRU OPERATIONS, REGOLITH TRANSPORT AND MANY OTHERS DEPEND ON KNOWLEDGE OF GEOTECHNICAL PROPERTIES OF THE SOIL. KNOWING, FOR EXAMPLE, THE SOIL STRENGTH AND ITS DENSITY AND IN TURN FUNDAMENTAL SOIL PARAMETERS SUCH AS FRICTION ANGLE AND APPARENT OR TRUE COHESION, WILL GUIDE THE DESIGN OF THE WHEELS AND EXCAVATION SYSTEMS AND HELP TO DETERMINE ANTICIPATED EXCAVATION ENERGIES, TIME, AND FORCES. NEARLY ALL PLANETARY ROVERS TO-DATE HAVE EXPERIENCED SOME TYPE OF PROBLEM DUE TO THE UNKNOWN NATURE OF PLANETARY REGOLITH. THE MER SPIRIT MISSION ENDED WHEN THE ROVER BOGGED DOWN. THE MER OPPORTUNITY ROVER BARELY RECOVERED FROM A SAND TRAP. MSL CURIOSITY SPENT OVER A MONTH TRYING TO FIND A SAFER ROUTE AROUND A SAND DUNE. APOLLO LUNAR ROVING VEHICLE GOT STUCK AND HAD TO BE LIFTED AND PLACED ON FIRMER GROUND WHILE LUNOKHOD MANAGED TO RECOVER FROM A 'NEAR' STUCK POSITION. HONEY ROBOTICS, THEREFORE, PROPOSES TO DESIGN AND TEST A PROTOTYPE GEOTECHNICAL TOOL CALLED THE STINGER, THAT COMBINES SOIL BEARING STRENGTH MEASUREMENTS WITH SHEAR TEST MEASUREMENTS. THE STINGER INSTRUMENT CONSISTS OF A PERCUSSIVE CONE SHEAR-VANE PENETROMETER CAPABLE OF MEASURING NEAR-SURFACE AND SUBSURFACE SOIL PROPERTIES TO A DEPTH OF 50 CM OR GREATER. THE CONE DEPLOYMENT IS PERCUSSIVE, BECAUSE THIS APPROACH REDUCES PENETRATION FORCES, AN IMPORTANT CONSIDERATION WHEN A TOOL IS DEPLOYED IN A LOW GRAVITY ENVIRONMENT FROM A SMALL VEHICLE. DURING PERCUSSIVE CONE DEPLOYMENT, THE SOIL BEARING STRENGTH IS MEASURED. THE SHEAR VANE IS INITIALLY HOUSED INSIDE A CONE AND IT IS PUSHED OUT WHENEVER SHEAR TESTS ARE REQUIRED. WHEN THE SHEAR VANE IS OUT, THE CONE-VANE IS ROTATED TO MEASURE SHEAR STRENGTH OF THE SOIL. THIS MEASUREMENT CAN BE PERFORMED AT ANY DEPTH. BASED ON RESULTS OF THE BREADBOARD TESTING, A PRELIMINARY DESIGN FOR A TRL6 STINGER GEOTOOL WILL ALSO BE REALIZED. | $124K |
| Jun 5, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CP23P | 541712 | IGF::OT::IGF THE MAJORITY OF PLANETARY BODIES OF INTEREST TO EXPLORATION ARE COVERED WITH A LAYER OF GRANULAR MATERIAL CALLED REGOLITH. THESE BODIES INCLUDE THE MOON, MERCURY, VENUS, MARS, ASTEROIDS, COMETS AND MOONS OF MARS, JUPITER, URANUS, AND NEPTUNE. SURFACE MISSIONS TO THESE BODIES, WOULD MOST PROBABLY REQUIRE SOME TYPE OF A SAMPLING SYSTEM TO CAPTURE SAMPLES AND DELIVER THEM TO IN-SITU INSTRUMENTS OR SAMPLE RETURN CONTAINERS. HONEYBEE ROBOTICS, THEREFORE, PROPOSES TO DEVELOP A ROBUST ON-DEMAND SAMPLE ACQUISITION AND DELIVERY SYSTEM ENABLED BY A HIGH EFFICIENCY BLOWER. THE SYSTEM WILL BE AKIN TO CONVENTIONAL VACUUM CLEANERS ON EARTH, BUT ADAPTED FOR VENUS CONDITIONS. AS SUCH, THE MAIN TECHNOLOGY AREAS WILL INCLUDE DEVELOPMENT OF THE FOLLOWING FOUR SUBSYSTEMS: BLOWER, CYCLONE, NOZZLE AND TUBING; WITH THE BLOWER BEING MOST CRITICAL. THE TARGET MISSION WILL BE VENUS IN SITU EXPLORER (VISE), HOWEVER, THE TECHNOLOGY COULD BE ADOPTED TO MARS MISSIONS. WE WILL USE CFD FLUENT TO PERFORM BLOWER AND CYCLONE ANALYSIS SIMULATING VENUS' ATMOSPHERE AND GRAVITY, AS GRAVITY AFFECTS CYCLONE PERFORMANCE. WE WILL FABRICATE AND TEST A BLOWER UNDER RELEVANT PRESSURE CONDITIONS IN A HIGH PRESSURE CHAMBER. WE WILL ALSO FABRICATE A CYCLONE AND SUCTION TUBES. THE SYSTEM WILL BE ASSEMBLED TO ALLOW END TO END TESTING. FURTHER, WE WILL DEVELOP A TRL 5/6 DESIGN FOR THE PNEUMATIC SYSTEM, WHICH WOULD BE FABRICATED AND TESTED IN PHASE 2 | $124K |
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