Federal Contractor Profile
Oakman Aerospace LLC
$193M obligated·116 awards·3 agencies·7 NAICS
Federal Contracts
Showing award actions 151–200 of 200 funded award actions, most recent first.
- Contracts with positive obligations
- 116
- Funded award actions shown
- 200
- Obligations shown
- $193M
- Awarding agencies
- 3
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 July 22, 2026. Source: USAspending federal award records.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| May 23, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0091 | 541715 | BUILDING ON PREVIOUSLY FUNDED WORK BY NASA AND DARPA, ITS INTERNAL RESEARCH AND DEVELOPMENT PROJECTS, AND MANUFACTURING ACTIVITIES OCCURRING ON THE INTERNATIONAL SPACE STATION (ISS), MADE IN SPACE, INC. (MIS) IS DEVELOPING THE VULCAN SYSTEM TO ADDRESS NASA S REQUIREMENT TO PRODUCE HIGH-STRENGTH, HIGH-PRECISION POLYMER AND METALLIC COMPONENTS ON-ORBIT WITH COMPARABLE QUALITY TO COMMERCIALLY-AVAILABLE, TERRESTRIAL MACHINED AND INSPECTED PARTS. SUCH CAPABILITY ENABLES THE IN-SITU MANUFACTURING OF CRITICAL PARTS FOR HUMAN AND ROBOTIC SPACEFLIGHT AND WITHOUT DEPENDENCE ON TERRESTRIAL RESUPPLY. MIS COMBINES SPACEFLIGHT-PROVEN MICROGRAVITY PROCESS CONTROLS AND PAYLOAD SUPPORT SYSTEMS, SUCH AS ENVIRONMENTAL AND THERMAL CONTROLS, WITH A MODULAR MANUFACTURING AND POST PROCESSING SYSTEM THAT GENERATES A NET SHAPE FINAL PRODUCT. | $668K |
| Apr 5, 2018 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $405K |
| Mar 28, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865018P9211 | 541715 | TRIANGULAR ROLLABLE AND COLLAPSIBLE DEBRIS DEORBIT DRAG SAIL (TRAC-3D) | $149K |
| Mar 22, 2018 | Department of DefenseW4PZ USA MED RSCH ACQUIS ACT | W81XWH17C0008 | 541712 | IGF::OT::IGF ARMY SBIR PH II A2-6328, TOPIC A15-061, AWARD TO ROCCOR, LLC PROPOSAL TITLE: "SUPERSATURATED OXYGEN EMULSION FOR TOPICAL TREATMENT OF OCULAR TRAUMA" | $469K |
| Jan 29, 2018 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $1.3M |
| Jan 29, 2018 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $3.0M |
| Dec 6, 2017 | Department of the InteriorIBC ACQ SERVICES DIVISION (00063) | IND17PC00192 | 541712 | IGF::OT::IGF THE EXTERNAL AUGMENTATION OF GENERIC LAUNCH ELEMENTS (EAGLE) SYSTEM | $50K |
| Nov 16, 2017 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833518C0117 | 541715 | IGF::OT::IGF | $125K |
| Nov 7, 2017 | Department of DefenseFA9453 AFRL RVK | FA945317C0426 | 541712 | IGF::OT::IGF DEPLOYABLE STRUCTURAL BOOMS FOR SMALLSAT ANTENNAS | $249K |
| Oct 16, 2017 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $2.2M |
| Oct 13, 2017 | Department of DefenseFA9453 AFRL RVK | FA945317C0426 | 541712 | IGF::OT::IGF DEPLOYABLE STRUCTURAL BOOMS FOR SMALLSAT ANTENNAS | $49K |
| Aug 29, 2017 | Department of DefenseFA9453 AFRL RVK | FA945317P0463 | 541712 | IGF::OT::IGF SHEAR STABILIZATION BASED FRAMEWORK FOR THE FAILURE TESTING AND ANALYSIS OF HSCS | $150K |
| Aug 24, 2017 | Department of DefenseFA9453 AFRL RVK | FA945317C0426 | 541712 | IGF::OT::IGF DEPLOYABLE STRUCTURAL BOOMS FOR SMALLSAT ANTENNAS | $200K |
| Aug 22, 2017 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $1.1M |
| Aug 10, 2017 | Department of DefenseFA9453 AFRL RVK | FA945317C0473 | 541712 | IGF::OT::IGF PRECISION SPACECRAFT INSTRUMENTATION BOOMS | $750K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CL86P | 541712 | IGF::OT::IGF IN RESPONSE TO NASA'S NEED FOR COMPACT, LOW-COST IN-SPACE MODULAR CONSTRUCTION COMPONENTS, ROCCOR PROPOSES TO DEVELOP STRUCTURAL ELEMENTS DESIGNED FOR RAPID IN-SPACE ASSEMBLY AND STRUCTURAL ADAPTATION. THE PROPOSED INVENTION, FASTEN (FULLY ADAPTIVE SLIT-TUBE STRUCTURES WITH ELECTRICALLY INTEGRATED SMART JOINTS), UTILIZES DEPLOYABLE COMPOSITE SLIT-TUBES IN CONJUNCTION WITH ELECTRICALLY INTEGRATED STRUCTURAL JOINT CONNECTORS FOR SIMPLE IN-SPACE ASSEMBLY OF TRUSS-LIKE CONSTRUCTIONS. THE PROPOSED DESIGN WILL ADVANCE AUTONOMOUS IN-SPACE ASSEMBLY OPPORTUNITIES THROUGH INNOVATIVE FEATURES SUCH AS: 1) IMPLEMENTING COILABLE SLIT-TUBES IN STRUCTURAL ARRANGEMENTS AT LOW-WEIGHT, LOW-COST AND MINIMAL STOWAGE VOLUME 2) DEVELOPING RIGID PLUG-AND-PLAY JOINTS FOR CONNECTING SLIT-TUBES IN MODULAR ARRANGEMENTS, 3) INTEGRATING CONDUCTIVE ELEMENTS FOR A FULLY CONNECTED STRUCTURE WITH JOINT CONNECTION VERIFICATION, 4) NEAR ZERO THERMAL EXPANSION IN CARBON FIBER COMPOSITE SLIT-TUBES. THE PRINCIPAL OBJECTIVE FOR THE PHASE I PROJECT IS TO CONDUCT A PRELIMINARY DESIGN-ANALYSIS-FABRICATION-TEST LOOP FOR AN ELECTRICALLY INTEGRATED MODULAR SLIT-TUBE BOOM (STB) TRUSS ASSEMBLY. THE PROJECT WILL CLEARLY IDENTIFY ENGINEERING RISKS THAT MUST BE ADDRESSED TO ULTIMATELY ENSURE ADEQUATE PERFORMANCE ON-ORBIT AND IN GRAVITY LOADED ENVIRONMENTS. DETAILED MECHANICAL AND ELECTRICAL DESIGN WILL BE PERFORMED INCLUDING INVESTIGATION OF ATTAINABLE TRUSS GEOMETRIES, REPEATABLE PLUG-AND-PLAY JOINT FASTENING MECHANISMS, MATERIAL SELECTION AND CONDUCTIVE ROUTING. THE DESIGN EFFORTS WILL BE FOLLOWED BY LOCAL AND GLOBAL STRENGTH, STABILITY AND THERMAL ANALYSES TO DESCRIBE THE CAPACITY OF SLIT-TUBES IN TRUSS ARRANGEMENTS AND STRENGTH OF THE CONNECTIVE TRUSS JOINTS. FURTHERMORE, ELEMENTS OF THE CONCEPT WILL BE PROTOTYPED TO TEST AREAS SUCH AS MODULAR ASSEMBLY AND ELECTRICAL CONTINUITY ACROSS SLIT-TUBES AND JOINTS. | $125K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM51P | 541712 | IGF::OT::IGF IN RESPONSE TO NASA'S NEED FOR LOW-COST DEPLOYABLE SOLAR SAIL BOOMS FOR MID-SIZE (~1,000M2) SOLAR SAILS, ROCCOR PROPOSES TO DEVELOP THE COMPOSITE TRUSSED TRAC (T-TRAC) BOOM SYSTEM. LIKE THE ORIGINAL TRAC BOOM, T-TRAC HAS A TRIANGULAR CROSS SECTION THAT FLATTENS AND ROLLS AROUND A SPOOL FOR PACKAGING. UNLIKE TRAC, T-TRAC IS APPLICABLE TO MUCH LARGER SCALE BOOM DESIGNS. THE PROPOSED DESIGN WILL ADVANCE TRAC TECHNOLOGY THROUGH: 1) SCALING UP THE CROSS-SECTION SIZE AND LENGTH OF THE BOOM, 2) LIGHT WEIGHTING THE BOOM THROUGH MATERIAL RE-DISTRIBUTION AND REMOVAL, AND 3) CROSS-SECTION MODIFICATION FOR ENHANCED STRENGTH. PRELIMINARY ANALYSES INDICATE THESE STEPS WILL ACHIEVE MORE THAN A 5X INCREASE IN TRAC BOOM STRUCTURAL MASS EFFICIENCY OVER RECENTLY DEVELOPED HIGH PERFORMANCE COMPOSITE TRAC BOOMS, WHILE MAINTAINING AN EXTREMELY COMPACT ROLL STOWED CONFIGURATION THAT MAINTAINS HERITAGE WITH NASA'S SOLAR SAIL MECHANICAL ARCHITECTURE LINEAGE. THE OVERARCHING PHASE I OBJECTIVE IS TO CONDUCT A PRELIMINARY DESIGN-ANALYSIS-FABRICATION-TEST LOOP FOR A T-TRAC BOOM CAPABLE OF MEETING REQUIREMENTS FOR NASA'S FUTURE MID-SIZED SOLAR SAIL MISSION. MULTI-SCALE MICRO-MECHANICS, LAMINATE, CROSS-SECTION, AND FULL SECTION ANALYSES WILL BE PERFORMED TO QUICKLY NARROW THE LAMINATES AND BOOM DESIGNS TO A FEW CANDIDATES. THESE EFFORTS WILL NECESSARILY BE PERFORMED IN CLOSE COMMUNICATION WITH MATERIAL VENDORS TO SELECT A FEW LAMINATES FOR SHORT COUPON TESTING PRIOR TO BUILDING PROOF OF- CONCEPT BOOMS. DURING PHASE II, A FOUR-BOOM T-TRAC SOLAR SAIL SYSTEM WILL BE DEVELOPED, AND PROTOTYPE UNITS WILL BE BUILT AND TESTED TO ESTABLISH PERFORMANCE FOR MISSIONS OF INTEREST TO NASA. | $125K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM52P | 541712 | IGF::OT::IGF IN RESPONSE TO NASA'S NEED FOR COMPACT, LIGHTWEIGHT AND EFFICIENT, LOW-COST DEPLOYABLE RADIATORS FOR CUBESATS, ROCCOR PROPOSES TO DEVELOP A HIGH-STRAIN LAMINATE COMPOSITE DEPLOYABLE RADIATOR CAPABLE OF DISSIPATING OVER 50-WATTS OF THERMAL ENERGY. THE PROPOSED DESIGN LEVERAGES ROCCOR'S EXPERIENCE IN HIGH-STRAIN COMPOSITE DEPLOYABLE STRUCTURES AND THERMAL MANAGEMENT PRODUCTS FOR CUBESAT AND SMALLSAT APPLICATIONS. WHILE SOLAR ARRAYS AND INSTRUMENT CAPABILITIES IN CUBESAT APPLICATIONS KEEP GROWING, THE LIMITED RADIATOR SURFACE RESULTS IN A THERMAL BOTTLENECK THAT LIMITS THE ACTUAL USE OF SCIENCE OR COMMUNICATION INSTRUMENTS. STATE-OF-THE-ART DEPLOYABLE RADIATORS USE MULTIPLE RIGID PANELS CONNECTED BY A FLEXIBLE HINGE, REPLICATING DESIGNS USED IN LARGE SPACE STRUCTURES. HOWEVER, THE MINIATURIZATION OF SUCH DESIGNS HAVE PROVEN INCAPABLE OF MEETING THE TIGHT MASS AND VOLUME CONSTRAINTS OF CUBESAT APPLICATIONS. ROCCOR PROPOSES TO UTILIZE A NOVEL PACKAGING OF LARGE SURFACE AREAS, MADE OF HIGHLY CONDUCTIVE MATERIALS, AND WITH ENOUGH STRAIN ENERGY TO DEPLOY PASSIVELY IN A RADIAL ARRANGEMENT. | $125K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $1.5M |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CG66P | 541712 | IGF::OT::IGF IN RESPONSE TO NASA'S NEED FOR COMPACT, LOW-COST DEPLOYABLE MAGNETOMETER BOOMS FOR CUBESATS, ROCCOR PROPOSES TO DEVELOP A SIMPLE HIGH-PERFORMANCE ROLL-OUT COMPOSITE (SHROC) MAGNETOMETER BOOM. THE BOOM IS CAPABLE OF MOTOR-LESS SELF-DEPLOYMENT AND LOCK-OUT THROUGH A UNIQUE COMBINATION OF BI-STABLE COMPOSITE LAMINATE DESIGN AND FEATURES THAT INCREASE TORSIONAL RIGIDITY AND DEPLOYED PRECISION AT THE END OF DEPLOYMENT. THE BOOM CAN BE BUILT TO DIAMETERS RANGING BETWEEN 1.6 CM (5/8 IN) AND 2.5 CM (1 IN) AND FULLY DEPLOYED LENGTHS RANGING FROM 0.5 M TO 10 M WHILE BEING PACKAGED IN LESS THAN 1/2-U VOLUME (10 CM X 10 CM X 5 CM). A LAUNCH-RETENTION MECHANISM IS PROVIDED TO LOCK THE TIP-MOUNTED INSTRUMENT PACKAGE FOR LAUNCH. FOR DEPLOYMENT, THIS LAUNCH RETENTION MECHANISM IS RELEASED AND THE STRAIN ENERGY STORED WITHIN THE HIGH-STRAIN COMPOSITE BOOM DRIVES THE DEPLOYMENT WITH PREDICTABLE AND NEARLY CONSTANT MOTIVE FORCE. THE OVERARCHING PHASE I OBJECTIVE IS TO CONDUCT A PRELIMINARY DESIGN-ANALYSIS-FABRICATION-TEST LOOP FOR A SHROC MAGNETOMETER BOOM CAPABLE OF MEETING REQUIREMENTS FOR A VARIETY OF FUTURE NASA HELIOPHYSICS SCIENCE MISSIONS. DURING PHASE II ROCCOR WILL ADDRESS THE KEY ENGINEERING DEVELOPMENT RISKS, MATURE THE SYSTEM DESIGN TO A CDR LEVEL OF DEVELOPMENT, AND VALIDATE PERFORMANCE OBJECTIVES THROUGH A SERIES OF GROUND-BASED QUALIFICATION TESTS ON ENGINEERING DEVELOPMENT UNITS. OVERALL, THE ANTICIPATED OUTCOME OF THE COMBINED PHASE I/II PROGRAM IS DEVELOPMENT AND PROTO-FLIGHT VALIDATION OF A SHROC BOOM SYSTEM FOR A WIDE RANGE OF FUTURE HELIOPHYSICS MISSIONS. | $125K |
| May 23, 2017 | Department of DefenseFA9453 AFRL RVK | FA945317C0426 | 541712 | IGF::OT::IGF DEPLOYABLE STRUCTURAL BOOMS FOR SMALLSAT ANTENNAS | $1.5M |
| May 22, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CL76P | 541712 | IGF::OT::IGF STRUCTURAL DEGRADATION AND FAILURE CAN CAUSE MALFUNCTIONS AND LONG-TERM PROBLEMS ABOARD SPACECRAFT, JEOPARDIZING THE CREW, ESPECIALLY IN DEEP SPACE MISSIONS. ON OFF-WORLD HABITATS, THIS CAN LEAD TO EXTENSIVE MAINTENANCE PROCEDURES AND DANGEROUS EVAS TO FIX MALFUNCTIONS. MICROMETEORITE IMPACT AND SHIELDING BREACHES CAN HAVE LASTING IMPACTS THAT POSE A SIGNIFICANT HAZARD TO THE LONGEVITY OF MISSIONS. MADE IN SPACE, INC. (MIS) HAS BEEN DEVELOPING NOVEL ADDITIVE MANUFACTURING (AM) TECHNOLOGIES FOR THE PRODUCTION AND APPLICATION OF EMBEDDED SENSORS AND ACTUATORS. MIS'S STRUCTURAL-HEALTH AWARE FAILURE-TOLERANT ENGINEERED TO RESPOND (SAFER) ADDITIVELY MANUFACTURED SYSTEM IS A SUITE OF INTEGRATED TECHNOLOGIES AND COMPOSITE MATERIALS THAT ARE COMPATIBLE WITH AM PROCESSING TECHNIQUES RANGING FROM FREE-FORM-FABRICATION, DIRECT-WRITE, AND INJECTION MOLDING. USING THE ADVANCED AM TECHNOLOGIES DEVELOPED FOR MICROGRAVITY MANUFACTURING AT MIS AND PIEZOELECTRIC THERMOPLASTICS PROVIDED BY THE OHIO STATE UNIVERSITY (OSU), A MAJOR SUITE OF STRUCTURAL MONITORING AND SENSING TECHNOLOGIES WILL BE MADE AVAILABLE TO DESIGNERS FOR A VARIETY OF APPLICATIONS. THE SAFER ADDITIVE MANUFACTURED SYSTEM WILL INCLUDE A SUITE OF AM SOLUTIONS FOR THE FOLLOWING APPLICATIONS: EMBEDDED STRAIN-SENSORS FOR HEALTH MONITORING AND DIAGNOSIS; PIEZOELECTRIC ACTUATORS AND SENSORS FOR SYSTEM PROGNOSIS; AND EMBEDDED HEATERS AND ACTUATORS FOR SYSTEM SELF-HEALING AND INCREASED RIGIDITY. SAFER EMBEDDED SYSTEMS EMPOWER DESIGNERS TO CUT WEIGHT OF STRUCTURAL MONITORING AND INCREASE STRUCTURAL SAFETY WITH THE FREEDOM OF AM. WITH THE DEVELOPMENT OF A NOVEL PIEZOELECTRIC AM MATERIAL, SAFER WILL BE A KEY COMPONENT TO SAFE LONG-DURATION MANNED SPACE FLIGHT SUCH AS NASA'S JOURNEY TO MARS AND BEYOND. SAFER GIVES NASA PEACE OF MIND BY COUPLING HEALTH-MONITORING AND SELF-REPAIRING MATERIALS. | $119K |
| May 22, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM34P | 541712 | IGF::OT::IGF MADE IN SPACE IS DEVELOPING THE THE VULCAN ADVANCED HYBRID MANUFACTURING SYSTEM (VULCAN) TO ADDRESS NASA'S REQUIREMENT TO PRODUCE HIGH-STRENGTH, HIGH-PRECISION COMPONENTS ON-ORBIT WITH COMPARABLE QUALITY TO COMMERCIALLY-AVAILABLE, TERRESTRIAL MACHINED PARTS. SUCH CAPABILITY ENABLES THE IN-SITU MANUFACTURING OF CRITICAL PARTS FOR HUMAN SPACEFLIGHT AND WITHOUT DEPENDENCE ON TERRESTRIAL RESUPPLY. MADE IN SPACE INTEGRATES FLIGHT-PROVEN MICROGRAVITY PROCESS CONTROLS AND PAYLOAD SUPPORT SYSTEMS, SUCH AS ENVIRONMENTAL AND MASTER CONTROLS, WITH A MODULAR MANUFACTURING&TOOL SYSTEM THAT GENERATES A NEAR NET SHAPE FOR SURFACE FINISHING OR OTHER INDUSTRIAL PROCESSING INTO THE FINAL PRODUCT. ONE OF THE KEY INNOVATIONS OF MADE IN SPACE'S VULCAN IS THE ABILITY TO PRODUCE FINISHED METAL PARTS WITH ONE DEVICE, ELIMINATING THE NEED FOR SEPARATE ADDITIVE MANUFACTURING AND SUBTRACTIVE MACHINING FACILITIES. THE WIRE FEED ARCHITECTURE OF BOTH THE THERMOPLASTIC EXTRUDER AND METAL MANUFACTURING HEAD ALLOWS THE HARDWARE TO BE INTERCHANGEABLE AND SUPPORTED ON THE SAME GANTRY WITHOUT REQUIRING MODIFICATION OF ANY OF THE COMPONENTS. THE TWO MANUFACTURING HEADS FOLLOW THE SBM-SPEC INTERFACE STANDARDS FOR PLUG-AND-PLAY OPERATION. THUS, THE MANUFACTURING HEADS CAN BE EXCHANGED EASILY BY CREWMEMBERS WITH NO FORMAL MANUFACTURING TRAINING. USING THIS CAPABILITY, THE VULCAN DEVICE PRODUCES BOTH NON-METALLIC AND METALLIC REPLACEMENT PARTS WITH A MINIMUM OF CREW INTERACTION. VULCAN IS SCALABLE AND SUPPORTS THE OPEN SBM-SPEC ARCHITECTURE FOR THE THERMOPLASTIC AND METAL MANUFACTURING HEADS, RESULTING IN A MANUFACTURING METHODOLOGY THAT USES MULTIPLE MATERIALS AND CAN BE UPGRADED OVER TIME. | $125K |
| May 15, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CA37P | 541712 | IGF::OT::IGF MADE IN SPACE, INC. (MIS) PROPOSES THE DEVELOPMENT OF AN INDUSTRIAL CRYSTAL FACILITY (ICF) FOR MICROGRAVITY PRODUCT MANUFACTURING AND APPLIED RESEARCH. THE ICF IS FOCUSED ON ADVANCED MATERIALS ENGINEERING, RATHER THAN BIOMEDICAL RESEARCH, AND SERVES A COMPLIMENTARY ROLE TO EXISTING NASA-DEVELOPED HARDWARE, EXPANDING UTILIZATION OF ISS. INTENDED APPLICATIONS INCLUDE NONLINEAR OPTICAL SINGLE CRYSTALS AND OTHER RELATIVELY LARGE MATERIAL FORMULATIONS. THIS IS A CRITICAL NEXT STEP IN THE DEVELOPMENT OF LOW EARTH ORBIT AS AN ECONOMIC DEVELOPMENT ZONE, USING THE ISS NATIONAL LAB AS A PROVING GROUND AND FOLLOWING THE FORTHCOMING MADE IN SPACE FIBER (MIS FIBER) DEMONSTRATION OF MANUFACTURING A PRODUCT IN SPACE WITH ECONOMICALLY-SIGNIFICANT INTRINSIC VALUE ON THE GROUND. THE ISS NATIONAL LAB SERVES AS AN IDEAL PLATFORM TO EXPLORE WHETHER INDUSTRIAL CRYSTALS CAN BE GROWN IN MICROGRAVITY TO LARGER SIZES AND/OR IMPROVED QUALITY AS COMPARED WITH TERRESTRIAL SOURCES. EXISTING LOW TEMPERATURE SOLUTION GROWTH METHODS TAKE DAYS TO WEEKS TO COMPLETE, SO PARABOLIC FLIGHTS AND SUBORBITAL VEHICLES ARE NOT SUITABLE FOR ESTABLISHING PROCESS BASELINES AND MAKING EFFECTIVE COMPARISONS. MICROGRAVITY PRODUCTION HOLDS THE POTENTIAL FOR ROOM-TEMPERATURE PRODUCTION OF NLO MATERIALS FOR HIGH-ENERGY APPLICATIONS WITH SIZE AND QUALITY UNDIMINISHED BY THE EFFECTS OF SEDIMENTATION AND CONVECTION. A NEW FACILITY IS NEEDED TO EXPLORE THE FEASIBILITY OF MICROGRAVITY-ENABLED INDUSTRIAL CRYSTALS AS A NEW PRODUCT MARKET FOR LOW EARTH ORBIT. | $125K |
| May 1, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CL07C | 541712 | IGF::OT::IGF A NEW DEPLOYABLE SPACECRAFT BOOM TECHNOLOGY CALLED THE TRIANGULAR ROLLABLE AND COLLAPSIBLE BOOM (TRACTM BOOM), INVENTED BY THE AIR FORCE RESEARCH LABORATORY AND EXCLUSIVELY LICENSED BY ROCCOR, IS BEING CONSIDERED BY NASA FOR NUMEROUS MISSIONS INCLUDING THE COMET RENDEZVOUS, SAMPLE ACQUISITION, ISOLATION, AND RETURN (CORSAIR) MISSION BEING DEVELOPED BY NASA GODDARD. FOR CORSAIR, NASA HAS BASELINED A RATHER ROBUST HIGH STRAIN COMPOSITE (HSC) TRAC BOOM TO TETHER A COMET SAMPLE ACQUISITION AND RETRIEVING PROJECTILE (SARP) TO THE SPACECRAFT AND PREVENT THE HARPOON-LIKE PENETRATOR FROM RECOILING BACK AND IMPACTING THE SPACECRAFT DURING RETRIEVAL. HOWEVER, QUESTIONS REMAIN AS TO HOW TO DESIGN AND BUILD A COMPOSITE TRAC BOOM WITH SUFFICIENT STRENGTH SO AS TO TOLERATE THE RELATIVELY LONG STORAGE TIME (SEVERAL YEARS IN-TRANSIT TO THE COMET) AND RELATIVELY HIGH DEPLOYMENT SPEEDS (~30-150 F/S) NECESSARY FOR THE CORSAIR HARPOON SYSTEM. TO ADDRESS THIS CHALLENGE DURING PHASE II, ROCCOR PROPOSES TO IMPROVE THE PERFORMANCE OF THE BONDLINE IN COMPOSITE TRAC BOOMS BY REINFORCING THE ADHESIVE JOINT AND DEVELOPING MECHANICAL END FITTINGS THAT ALLOW HIGHER PACKAGING STRAINS WHILE MINIMIZING CREEP. WE ALSO PROPOSE TO VALIDATE A RELATIVELY LOW COST, OUT-OF-AUTOCLAVE PROCESS FOR AFFECTING THE BOND, AND VALIDATE ANALYTICAL MODELS TO SIMULATE THE TIME- AND TEMPERATURE-DEPENDENT VISCOELASTIC BEHAVIOR OF COMPOSITE TRAC BONDED JOINT, AND GUIDE ENGINEERING QUALIFICATION OF THE JOINTS FOR FUTURE NASA MISSIONS, INCLUDING CORSAIR. MOREOVER, ROCCOR WILL ALSO FURTHER OPTIMIZE THE SYSTEM DESIGN, INCLUDING PROXIMAL AND DISTALL END FITTINGS THAT CONNECT TRAC BOOM INTO THE CORSAIR STORAGE CANISTER AND SAMPLE RETURN PROJECTILE TO VALIDATE STRENGTH AND CREEP PERFORMANCE TO MISSION REQUIREMENTS, AND TO INCORPORATE LOAD-LIMITING FEATURES THAT PREVENT CATASTROPHIC FAILURE OF THE TRAC BOOM DURING OPERATION. | $752K |
| May 1, 2017 | Department of DefenseW4PZ USA MED RSCH ACQUIS ACT | W81XWH17C0008 | 541712 | IGF::OT::IGF ARMY SBIR PH II A2-6328, TOPIC A15-061, AWARD TO ROCCOR, LLC PROPOSAL TITLE: "SUPERSATURATED OXYGEN EMULSION FOR TOPICAL TREATMENT OF OCULAR TRAUMA" | $507K |
| Apr 17, 2017 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | NNJ17GU30T | 541712 | IGF::OT::IGF DESIGN VALUE TEST PLAN FOR ACRYLONITRILE-BUTADIENE-STYRENE (ABS) | $44K |
| Apr 14, 2017 | Department of the InteriorIBC ACQ SERVICES DIVISION (00063) | IND17PC00192 | 541712 | IGF::OT::IGF THE EXTERNAL AUGMENTATION OF GENERIC LAUNCH ELEMENTS (EAGLE) SYSTEM | $100K |
| Mar 29, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CG03P | 541712 | IGF::OT::IGF THE NASA GSFC IRAD PROGRAM IS CURRENTLY EXPLORING A NOVEL METHOD TO GRAB A SAMPLE OF A ROTATING COMET THAT CAN BE MOVING THROUGH THE SOLAR SYSTEM AT PERIHELION VELOCITIES OF MORE THAN 100 KM/SEC. WHILE SPEWING CHUNKS OF ICE, ROCK AND DUST. THE GSFC TECHNIQUE IS DESIGNED TO AVOID THE RISKY BUSINESS OF LANDING ON THE COMET'S ROTATING AND OUTGASSING SURFACE. INSTEAD, THE TEAM OF NASA ENGINEERS AND SCIENTISTS LED BY DR. JOSEPH NUTH WANT TO FIRST RENDEZVOUS WITH THE COMET, THEN FIRE A HARPOON TO RAPIDLY ACQUIRE SAMPLES FROM PRECISELY-TARGETED LOCATIONS ON THE COMET WHILE STAYING ABOVE THE TARGET (FIGURE 1). USING THIS "STANDOFF" TECHNIQUE ALLOWS SAMPLES TO BE COLLECTED FROM AREAS THAT ARE TOO RUGGED OR DANGEROUS TO PERMIT THE SAFE LANDING, SURFACE OPERATION AND TAKEOFF OF A SPACECRAFT. ACCORDING TO THE TEAM, THE SPACECRAFT MAY ALSO HAVE MULTIPLE SAMPLE COLLECTION HARPOONS WITH A VARIETY OF POWDER CHARGES TO HANDLE AREAS ON A COMET WITH DIFFERENT COMPOSITIONS AND MATERIAL PROPERTIES | $5K |
| Feb 16, 2017 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | NNJ17GU28T | 541712 | IGF::OT::IGF OPTIMIZATION AND ON-BOARD PRINTING OF TWO, 2, RADIO ANTENNA FEED HORNS. THE KABOOM PROJECT TEAM REQUIRES TWO, 2, RF FEED HORN UNITS FABRICATED IN MICROGRAVITY FOR EXPERIMENTATION ON GROUND. NASA WILL PROVIDE THE CAD DESIGN OF THE PART TO MADE IN SPACE, MIS, FOR OPTIMIZATION AND PRINTING ON THE AMF IN ABS PLASTIC. SIX, 6, GROUND SAMPLES THAT WILL BE IDENTICAL TO THE TWO FLIGHT UNITS WILL BE SHIPPED TO THE KABOOM TEAM FOR GROUND TESTING. THE TWO FLIGHT UNITS WILL BE PRINTED ON ORBIT WITH THE GOAL TO DOWN MASS THEM PRIOR TO APRIL 15, 2017, IF POSSIBLE. PRINTING AND DOWNMASSING IS LIMITED BY ISS CREW TIME AVAILABILITY AND THE SCHEDULE OF VISITING VEHICLES. THE CAD DESIGN MUST BE PROVIDED TO MIS NLT FEBRUARY 17, 2017 IN ORDER TO MAKE IT POSSIBLE TO MEET THE TARGET DELIVERY DATE OF APRIL 15TH. | $24K |
| Feb 15, 2017 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | NNJ17GU29T | 541712 | IGF::OT::IGF EXPLORATION TECHNOLOGY DEMONSTRATION AND NATIONAL LAB UTILIZATION ENHANCEMENTS THE RADWORKS TEAM REQUIRES 3D PRINTED ENCLOSURES TO ATTACH TO THE REM SENSOR FOR ON-ORBIT EXPERIMENTS ON THE BEAM MODULE. ENCLOSURES IN THREE DIFFERENT THICKNESSES 1.1MM, 3.3MM, 10MM WILL BE PRINTED FOR THESE EXPERIMENTS. NASA WILL PROVIDE THE CAD DESIGN OF THE PARTS TO MADE IN SPACE, MIS, FOR OPTIMIZATION AND PRINTING ON THE ADDITIVE MANUFACTURING FACILITY, AMF, IN ABS PLASTIC. THE 1.1MM AND 3.3MM THICK ENCLOSURES WILL FALL UNDER THE CATEGORY OF SMALL PARTS WHILE THE 10MM THICK ENCLOSURE WILL BE A MEDIUM PART. THE THREE UNIQUE PARTS WILL BE OPTIMIZED FOR PRINTING AND PRINTED ON ORBIT. A TOTAL OF 3 GROUND PRINTS, 1 FOR EACH THICKNESS WILL BE PROVIDED DURING OPTIMIZATION. THE TARGET SCHEDULE OF THIS PROJECT IS TO PRINT ALL 3 ITEMS ON ORBIT BY MARCH 8TH, IF POSSIBLE. MEETING THIS SCHEDULE IS SUBJECT TO ISS CREW TIME AVAILABILITY. THE CAD DESIGN MUST BE PROVIDED TO MIS NLT FEBRUARY 17, 2017 IN ORDER TO MAKE IT POSSIBLE TO MEET THE TARGET OF DELIVERING THE PART BY MARCH 8TH | $27K |
| Jan 26, 2017 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $2.6M |
| Dec 21, 2016 | Department of DefenseW6QK ACC-APG DURHAM | W911NF15C0009 | 541712 | IGF::OT::IGF BASE EFFORT - SBIR PHASE II ELECTRONIC COMPONENT FINGERPRINTING TO DETERMINE MANUFACTURING ORIGIN | $500K |
| Oct 27, 2016 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $5.5M |
| Oct 19, 2016 | Department of DefenseFA9453 AFRL RVK | FA945317P0422 | 541712 | IGF::OT::IGF DIMENSIONALLY STABLE HSC (DISH) BOOMS FOR RF ANTENNA | $150K |
| Sep 26, 2016 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM13AA02C | 541712 | IGF::CT::IGF ADDITIVE MANUFACTURING TECHNOLOGY DEMONSTRATION(AMTD) | $3K |
| Sep 20, 2016 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | NNJ16GU32T | 541712 | IGF::OT::IGF SPHERES CONNECTOR ASSEMBLY, MADE IN SPACE,MIS, PROVIDES OPTIMIZATION AND PRINT SERVICES FOR TWO SMALL PARTS IN ABS, TWO PRINTS OF EACH ON ORBIT. THESE SERVICES SHALL INCLUDE: COORDINATION WITH THE ISS SAFETY REVIEW PANEL, ISRP, HUMAN FACTORS INTEGRATION TEAM HFIT, CREW OFFICE, AND OTHER ISS INTEGRATION TEAMS TO DETERMINE DESIGN ISSUES AND POTENTIAL HAZARDS. DESIGN OPTIMIZATION AND DEVELOPMENT OF AMF PRINT FILES. PRODUCTION OF GROUND TEST PRINTS, UP TO 5 FOR EACH PART, ON THE AMF FOR VERIFICATION OF PART DESIGN AND FUNCTIONALITY. CERTIFICATION OF PRINT ACTIVITY ON-BOARD ISS INCLUDING INTERFACES, HUMAN FACTORS, SAFETY, AND OTHER REQUIREMENTS. AMF PLANNING AND OPERATIONS SUPPORT. PRINTING OF PARTS IN THE AMF. INSPECTION OF PRINTED PARTS FOR QUALITY AND ACCURACY; AND COORDINATION OF TIMELY RETURN OF PARTS TO THE USER POST-FLIGHT IF REQUESTED. AT THE CONCLUSION OF THESE SERVICES, MIS SHALL DELIVER TO NASA THE FOLLOWING: GROUND TEST PRINTS UP TO 5 PER PART. OPTIMIZED CAD MODEL. DOCUMENTED VERIFICATION OF THE QUALITY OF THE PRINTED PARTS AND ACCURACY AS COMPARED TO AGREED DESIGN REQUIREMENTS. PRINTED PARTS. | $12K |
| Jul 20, 2016 | Department of DefenseMISSILE DEFENSE AGENCY (MDA) | HQ014716C7726 | 541712 | IGF::OT::IGF SBIR PHASE II RESEARCH&DEVELOPMENT | $999K |
| Jun 7, 2016 | Department of DefenseFA9453 AFRL RVK | FA945316M0468 | 541712 | IGF::OT::IGF FSRA: A FLEXIBLE-SUBSTRATE RESILIENT ARRAY | $150K |
| Jun 2, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CM36P | 541712 | IGF::OT::IGF IN RESPONSE TO SIGNIFICANT GAPS IN ADVANCED THERMAL CONTROL SYSTEMS ONBOARD CUBESATS AND SMALLSATS, AND BUILDING OFF OF THE SUCCESSFUL DEVELOPMENT OF SPACEBASED FLEXCOOLTM TWO-PHASE THERMAL STRAPS FOR CUBESATS BY ITS AFFILIATED COMPANY I2C SOLUTIONS, ROCCOR PROPOSES TO DEVELOP A COMPREHENSIVE THERMAL MANAGEMENT COMPONENT BY ADDING A PHASE CHANGE MATERIAL (PCM) THERMAL ENERGY STORAGE (TES) LAYER TO THE THIN, FLEXIBLE, HIGH CONDUCTIVITY FLEXCOOL THERMAL STRAP TECHNOLOGY. THE RESULTING FLEXIBLE THERMAL ENERGY MANAGEMENT, (FLEXTHERM) PRODUCT IS A SINGLE THIN FLEXIBLE COMPONENT THAT INTEGRATES EASILY INTO CUBESAT GEOMETRIES, OPERATES RELIABLY IN VACUUM, AND EFFICIENTLY SERVES THERMAL ACQUISITION, TRANSPORT, REJECTION AND THERMAL ENERGY STORAGE FUNCTIONS WITH A MINIMUM SIZE AND VOLUME. TO THAT END, THE MAIN OBJECTIVE OF THE PROPOSED PHASE I PROGRAM IS TO DEMONSTRATE THE TECHNICAL FEASIBILITY OF INTEGRATING PCMS WITH FLEXCOOL, A THIN, FLAT, FLEXIBLE HEAT PIPE TECHNOLOGY WHOSE FEASIBILITY WAS PREVIOUSLY DEMONSTRATED FOR OPERATION IN THE SPACE ENVIRONMENT. THE PCM LAYER WILL INCLUDE PARAFFIN WAXES AS THE MATRIX MATERIAL INSIDE A METAL CASING WITH AN INTERNAL METAL WOVEN MESH. THE INTERNAL MESH ACTS AS A MECHANICAL LOAD BEARING LAYER, AS WELL AS THERMAL CONDUCTIVITY ENHANCEMENT MATERIAL TO SPREAD HEAT INTO THE TES MATERIAL. | $124K |
| Jun 2, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CL50P | 541712 | IGF::OT::IGF IN RESPONSE TO NASA'S NEED FOR COMPACT, LOW-COST DEPLOYABLE SOLAR SAIL BOOMS FOR CUBESATS, ROCCOR PROPOSES TO DEVELOP A HIGH PERFORMANCE COMPOSITE TRAC (TRAC HP) BOOM SYSTEM. THE PROPOSED DESIGN WILL ADVANCE TRAC TECHNOLOGY THROUGH: 1) THE USE OF THIN-PLY COMPOSITE LAMINATES THAT ARE CAPABLE OF HIGHER PACKAGING STRAINS, 2) THE USE OF HIGH MODULUS CARBON FIBERS TO INCREASE SPECIFIC MODULUS OF THE DEPLOYED BOOMS, AND 3) INCORPORATING A STEPPED TAPER OF THE BOOM LAMINATE THICKNESS ALONG ITS LENGTH TO IMPROVE COMPRESSION EFFICIENCY WHILE MINIMIZING IMPACT TO PACKAGED VOLUME. PRELIMINARY ANALYSES INDICATE A COMPOSITE TRAC HP BOOM CAN ACHIEVE MORE THAN A 3X INCREASE IN BUCKLING STRENGTH AND 15X REDUCTION IN THERMAL DEFORMATIONS COMPARED TO THE ELGILOY TRAC DESIGN CURRENTLY BASELINED FOR NASA?S NEA SCOUT MISSION. THE OVERARCHING PHASE I OBJECTIVE IS TO CONDUCT AN PRELIMINARY DESIGN-ANALYSIS-FABRICATION-TEST LOOP FOR A TRAC HP FOUR-BOOM SYSTEM CAPABLE OF MEETING REQUIREMENTS FOR NASA?S NEA SCOUT MISSION, AND CLEARLY IDENTIFY ENGINEERING DEVELOPMENT RISKS THAT MUST BE ADDRESSED TO ULTIMATELY ENSURE ADEQUATE PERFORMANCE OF THESE BOOMS ON-ORBIT. DURING PHASE II, THE TRAC HP BOOM SYSTEM WILL BE DEVELOPED TO A PROTO-FLIGHT LEVEL OF MATURITY (ENGINEERING DESIGN TO FLIGHT CDR, AND MANUFACTURING/TEST PLAN IN CONFORMANCE WITH FLIGHT HARDWARE QUALITY STANDARDS), AND NUMEROUS HARDWARE PROTOTYPES WILL BE BUILT AND TESTED TO ESTABLISH PERFORMANCE FOR NEA SCOUT AND OTHER CUBESAT SOLAR SAIL MISSIONS OF INTEREST TO NASA. | $125K |
| Jun 2, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CL55P | 541712 | IGF::OT::IGF A NEW DEPLOYABLE SPACECRAFT BOOM TECHNOLOGY CALLED THE TRIANGULAR ROLLABLE AND COLLAPSIBLE BOOM (TRACTM-BOOM) HAS BEEN INVENTED BY THE AIR FORCE RESEARCH LABORATORY AND IS BEING CONSIDERED BY NASA FOR NUMEROUS MISSIONS INCLUDING THE NEAR EARTH ASTEROID SCOUT (NEA SCOUT) AND LUNAR FLASHLIGHT SOLAR SAIL MISSIONS BEING DEVELOPED BY NASA MARSHALL SPACEFLIGHT CENTER AS WELL AS THE CORSAIR COMET SAMPLE RETURN MISSION BEING DEVELOPED BY NASA GODDARD. THE GREATEST RISK/CONCERN VOICED BY THESE MISSION DEVELOPMENT TEAMS RELATED TO COMPOSITE TRAC?-BOOM TECHNOLOGY IS THE HIGHLY NONLINEAR AND TIME-DEPENDENT CREEP AND STRESS RELAXATION BEHAVIOR OF THE BONDED ?RIDGE-JOINT? THAT JOINS THE TWO CIRCULAR FLANGES AND ENDURES SUSTAINED STRESS WHEN THE BOOM IS FLATTENED AND STOWED. TO ADDRESS THIS CONCERN, ROCCOR PROPOSES TO IMPROVE THE PERFORMANCE OF THE BONDLINE IN COMPOSITE TRAC?-BOOMS BY REINFORCING THE ADHESIVE JOINT WITH HIGH STIFFNESS ELEMENTS THAT ALLOW HIGHER PACKAGING STRAINS WHILE MINIMIZING CREEP. WE ALSO PROPOSE TO VALIDATE A RELATIVELY LOW COST, OUT-OF-AUTOCLAVE PROCESS FOR AFFECTING THE BOND, AND VALIDATE ANALYTICAL MODELS TO SIMULATE THE TIME- AND TEMPERATURE-DEPENDENT VISCOELASTIC BEHAVIOR OF COMPOSITE TRAC? BONDED JOINT, AND GUIDE ENGINEERING QUALIFICATION OF THE JOINTS FOR FUTURE NASA MISSIONS. THE RESULTS OF THE PROPOSED PHASE 1 PROGRAM WILL INCLUDE: 1) ASSESSMENT OF THE FEASIBILITY OF ROCCORS CREEP-RESISTANT BONDLINE TECHNOLOGY, 2) VALIDATION OF AN ENGINEERING FRAMEWORK (THROUGH MODEL AND TEST CORRELATION) FOR FLIGHT VALIDATION OF COMPOSITE TRAC?-BOOM DESIGNS, AND 3) DEVELOPMENT OF A PHASE 2 PLAN FOR ELEVATION OF THE TECHNOLOGY FROM TRL 3 TO TRL 5 FOR FUTURE NASA FLIGHT APPLICATIONS. | $125K |
| May 31, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX14CP08C | 541712 | IGF::OT::IGF IN PHASE II, ROCCOR PROPOSES TO BUILD UPON THE RESULTS OF PHASE I TO INCREASE THE TECHNOLOGY READINESS LEVEL (TRL) OF THE NASA JPL DEPLOYABLE EXTERNAL OCCULTER. AN OCCULTER, WHICH IS A SATELLITE FLYING FAR FROM A TELESCOPE AND EMPLOYING A LARGE SCREEN OR, STARSHADE, TO SUPPRESS THE INCOMING STARLIGHT, IS USED FOR DETECTING AND CHARACTERIZING EXOPLANETS. DETECTING EARTHLIKE PLANETS EXISTING WITHIN THE HABITABLE ZONES OF NEARBY STARS IS A KEY ELEMENT OF NASA'S SPACE EXPLORATION MISSION. THE NASA JPL STARSHADE INCORPORATES A DEPLOYABLE CENTER RING-TRUSS AS A HUB AND FLOWER-LIKE PETALS THAT WRAP AROUND THE HUB FOR PACKAGING. AS A RESULT, IT EXHIBITS EXCEPTIONALLY CHALLENGING DEPLOYMENT KINEMATICS. ROCCOR'S PHASE II WILL CONTRIBUTE TO MATURING THE DESIGN OF THE NASA JPL DEPLOYABLE STARSHADE THROUGH SYSTEM AND COMPONENT DESIGN AND ANALYSIS AND SUPPORTING GROUND-DEMO HARDWARE THEREBY HELPING TO POSITION IT FOR SPACEFLIGHT SHOULD IT BE TRANSITIONED TO A NASA FLIGHT MISSION.ROCCOR'S BROAD PHASE II FOCUS IS ON MATURING EACH OF THE DEPLOYABLE STARSHADE SYSTEM ELEMENTS THAT SUPPORT THE PETALS INCLUDING THE UNFURLING CONTROL SYSTEM, THE LAUNCH CONTROL SYSTEM, AND THE DEPLOYED STRUT SYSTEM. INNOVATIVE SOLUTIONS HAVE BEEN CONCEPTUALIZED FOR EACH OF THESE PETAL SUPPORT FUNCTIONS AS PART THE PHASE I PROGRAM. IN PHASE II, ROCCOR WILL EMPHASIZE DEVELOPING AND DEMONSTRATING THE PROPOSED PETAL UNFURLING TECHNOLOGY CULMINATING IN A 1/3 SCALE FULLY FUNCTIONAL AND MOTORIZED HARDWARE DEMONSTRATION WITH 30 PETAL SIMULATORS, 3 OF THEM BEING INSTRUMENTED AND STRENGTHREPRESENTATIVE (E.G. FRAGILE AND NARROW PETAL TIPS). ROCCOR WILL ALSO FURTHER DEVELOP THE LAUNCH CONTROL SYSTEM AND DEPLOYED STRUT-SUPPORT SYSTEM THROUGH EXTENSIVE DESIGN AND AN OUTRIGGER COMPONENT FOR A DEPLOYABLE OCCULTER SYSTEM ANALYSIS. | $497K |
| May 4, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CP03C | 541712 | IGF::OT::IGF JET PROPULSION LABORATORY (JPL) IS INVOLVED IN AN ONGOING EFFORT TO DESIGN AND DEMONSTRATE A FULL-SCALE (30-32M DIAMETER) STARSHADE ENGINEERING DEMONSTRATOR THAT MEETS THE AGGRESSIVE DEPLOYMENT DIMENSIONAL REPEATABILITY AND STABILITY REQUIREMENTS FOR EXOPLANET DETECTION. A KEY COMPONENT OF THE STARSHADE STRUCTURAL SYSTEM IS A SERIES OF DIMENSIONALLY STABLE COMPOSITE CABLES (OR SPOKES) THAT CONNECT THE CENTER STRUCTURAL HUB TO THE PERIMETER TRUSS AND LARGELY DETERMINE THE DEPLOYED SHAPE AND STIFFNESS OF THE SYSTEM MUCH LIKE A BICYCLE WHEEL. THERE ARE MANY CHALLENGES IN DEVELOPING THE STARSHADE SPOKE. PERHAPS MOST NOTABLE IS THAT MEETING THE CTE REQUIREMENT NECESSITATES ACCURATE CONTROL OF FIBER VOLUME FRACTION (RESIN CONTENT) TO LESS THAN 1%. ALSO CHALLENGING IS THAT MEETING THE STIFFNESS PRECISION GOAL OF LESS THAN 0.5% VARIATION BETWEEN CABLES DEMANDS THAT MINIMAL FIBER FRAYING AND DAMAGE BE ALLOWED DURING THE TOW SPREADING AND ALIGNMENT PROCESS AND THAT THE NET CROSS SECTION BE MADE IN ONE STEP WITH NO REQUIRED POSTPROCESSING. FURTHERMORE, MEETING THE LENGTH PRECISION GOAL REQUIRES UNCOMMON ASSEMBLY AND END FITTING BONDING METHODOLOGIES. FINALLY, THERE ARE CHALLENGES ASSOCIATED WITH INTEGRATING SUCH HIGH-PERFORMANCE CABLES INTO THE STARSHADE WHILE ENSURING SNAG-FREE DEPLOYMENT AND PROPER ON-ORBIT OPERATION. THE DS3 CABLE TECHNOLOGY ADDRESSES ALL OF THESE CHALLENGES WITH A HIGHLY TAILORABLE THERMOPLASTIC-TAPE DESIGN THAT USES DUAL RESIN BONDING TECHNOLOGY FOR STRENGTH AND DIMENSIONAL STABILITY AT THE END FITTINGS | $750K |
| May 3, 2016 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM13AA02C | 541712 | IGF::CT::IGF ADDITIVE MANUFACTURING TECHNOLOGY DEMONSTRATION(AMTD) | $37K |
| Apr 25, 2016 | Department of the InteriorIBC ACQ SERVICES DIVISION (00063) | IND16PC00114 | 541712 | IGF::OT::IGF SCANNING AND ADDITIVE MANUFACTURING END-EFFECTOR FOR ROBOTIC GEO SERVICING SPACECRAFT | $129K |
| Apr 19, 2016 | Department of DefenseMID ATLANTIC REG MAINT CTR | N5005416P0019 | 323120 | DIGITAL PACKAGE ISS. IGF::OT::IGF | $10K |
| Mar 22, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CG03P | 541712 | IGF::OT::IGF THE NASA GSFC IRAD PROGRAM IS CURRENTLY EXPLORING A NOVEL METHOD TO GRAB A SAMPLE OF A ROTATING COMET THAT CAN BE MOVING THROUGH THE SOLAR SYSTEM AT PERIHELION VELOCITIES OF MORE THAN 100 KM/SEC. WHILE SPEWING CHUNKS OF ICE, ROCK AND DUST. THE GSFC TECHNIQUE IS DESIGNED TO AVOID THE RISKY BUSINESS OF LANDING ON THE COMET'S ROTATING AND OUTGASSING SURFACE. INSTEAD, THE TEAM OF NASA ENGINEERS AND SCIENTISTS LED BY DR. JOSEPH NUTH WANT TO FIRST RENDEZVOUS WITH THE COMET, THEN FIRE A HARPOON TO RAPIDLY ACQUIRE SAMPLES FROM PRECISELY-TARGETED LOCATIONS ON THE COMET WHILE STAYING ABOVE THE TARGET (FIGURE 1). USING THIS "STANDOFF" TECHNIQUE ALLOWS SAMPLES TO BE COLLECTED FROM AREAS THAT ARE TOO RUGGED OR DANGEROUS TO PERMIT THE SAFE LANDING, SURFACE OPERATION AND TAKEOFF OF A SPACECRAFT. ACCORDING TO THE TEAM, THE SPACECRAFT MAY ALSO HAVE MULTIPLE SAMPLE COLLECTION HARPOONS WITH A VARIETY OF POWDER CHARGES TO HANDLE AREAS ON A COMET WITH DIFFERENT COMPOSITIONS AND MATERIAL PROPERTIES | $60K |
| Dec 11, 2015 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CG01C | 541712 | IGF::OT::IGF THE STRATEGY OF THIS EFFORT IS TO DEVELOP AND VALIDATE THROUGH GROUND TESTING A DEPLOYABLE LOW-COST, HIGH-STRAIN, COMPOSITE BOOM SYSTEM FOR FUTURE NASA CUBESAT RF ANTENNA AND MAGNETOMETER APPLICATIONS. SPECIFICALLY, ROCCOR WILL DEVELOP THE ENGINEERING DESIGN OF BOTH RF ANTENNA AND MAGNETOMETER CONFIGURATIONS USING ROCCOR'S SO-CALLED ROC-BOOM TECHNOLOGY TO PDR-LEVEL MATURITY AND DRAFT ICD AND OPERATIONS DOCUMENTS FOR THE INTEGRATION OF THE BOOM SYSTEM INTO NASA'S CUBESAT DESIGNS. FURTHER, ROCCOR WILL FABRICATE AND TEST ENGINEERING DEVELOPMENT ARTICLES TO VALIDATE DEPLOYMENT AND MECHANICAL PERFORMANCE OF THE BOOM. ROCCOR WILL DELIVER TO NASA QUALIFIED ENGINEERING TEST ARTICLES FOR SUBSEQUENT TESTING TO VALIDATE THE BOOMS PERFORMANCE IN NASA'S MAGNETOMETER APPLICATIONS IN SIMULATED SPACE ENVIRONMENTS (TESTING TO TRL-5). | $350K |
| Oct 14, 2015 | Department of DefenseNAVAL RESEARCH LABORATORY | N0017316P0083 | 541330 | IGF::OT::IGF TEST PLAN&REPORT | $76K |
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