Federal Contractor Profile
Oakman Aerospace LLC
$193M obligated·116 awards·3 agencies·7 NAICS
Federal Contracts
Showing award actions 101–150 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 |
|---|---|---|---|---|---|
| Jul 30, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0469 | 541715 | SPACE DEMONSTRATION OF FLEXCOOL THIN FLAT HEAT PIPES | $125K |
| Jul 30, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0397 | 541715 | MOBILE END-EFFECTOR LASER DEVICE (MELD) | $125K |
| Jul 24, 2019 | Department of DefenseFA9453 AFRL RVK | FA945319P0673 | 541715 | HIGH POWER RADIATOR AND SWITCHABLE ADVANCED THERMAL SYSTEMS | $150K |
| Jul 12, 2019 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $12M |
| Jul 10, 2019 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0199 | 541712 | STUDY OF IN-SPACE MANUFACTURING REGOLITH 3D PRINTING TECHNOLOGY DEMONSTRATION ON ISS | $50K |
| Jul 9, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0175 | 541715 | MADE IN SPACE, INC. CONTINUES THE DEVELOPMENT OF AN IN-SPACE MANUFACTURING ARCHITECTURE FOR PRECISION LONG-BASELINE STRUCTURES THAT SUPPORT SPACE INTERFEROMETRY MISSIONS IN THE INFRARED. | $748K |
| Jul 8, 2019 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC19C0137 | 541715 | MIS IS PIONEERING THE USE OF THE MICROGRAVITY ENVIRONMENT ON THE INTERNATIONAL SPACE STATION (ISS) FOR MANUFACTURING TECHNOLOGY AND PRODUCT DEVELOPMENT. | $750K |
| Jun 14, 2019 | Department of DefenseFA9453 AFRL RVK | FA945319P0639 | 541715 | RAPID CUBESAT DEVELOPMENT OBJECTIVE IS TO DEFINE THE MOST EFFECTIVE STRATEGY AND TECHNOLOGY DEVELOPMENT ROADMAP IN ORDER TO DEVELOP THE BETA TEST ACORN RAPID CUBESAT DEVELOPMENT PROCESS MODULE IN PHASE II FOR THIS SBIR TOPIC. | $75K |
| May 16, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019C9228 | 541715 | ROBUST, HIGHLY SCALABLE SOLAR ARRAY FOR HARSH ENVIRONMENTS | $1.5M |
| May 8, 2019 | Department of the InteriorIBC ACQ SERVICES DIVISION (00063) | 140D6318C0056 | 541715 | EXTERNAL AUGMENTATION OF GENERIC LAUNCH ELEMENTS (EAGLE) SYSTEM | $445K |
| Apr 29, 2019 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0137 | 541712 | TO#12 POWER SUPPLY REDESIGN | $150K |
| Apr 3, 2019 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0038 | 541712 | TURBINE CERAMIC PARTS MANUFACTURING DEMONSTRATION | $679K |
| Apr 2, 2019 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0032 | 541712 | INDUSTRIAL CRYSTALLIZATION FACILITY FLIGHT DEMONSTRATION | $941K |
| Apr 2, 2019 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0036 | 541712 | TURBINE SUPERALLOY PARTS MANUFACTURING DEMONSTRATION | $812K |
| Mar 20, 2019 | National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTER | NNM17AA02C | 541712 | IGF::OT::IGF IN-SPACE ROBOTIC MANUFACTURING AND ASSEMBLY SYSTEM (TIPPING POINT TECHNOLOGIES) | $7K |
| Feb 28, 2019 | Department of DefenseMISSILE DEFENSE AGENCY (MDA) | HQ014716C7726 | 541712 | IGF::OT::IGF SBIR PHASE II RESEARCH&DEVELOPMENT | $500K |
| Feb 27, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019C9202 | 541715 | ROBUST, HIGHLY SCALABLE SOLAR ARRAY FOR HARSH ENVIRONMENT | $1.5M |
| Dec 21, 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) | $1.7M |
| Dec 19, 2018 | Department of DefenseFA9453 AFRL RVK | FA945319P0541 | 336419 | IGF::OT::IGF HORIZON ADDITIVE MANUFACTURING QUALIFICATION MEASUREMENT SYSTEM | $149K |
| Dec 17, 2018 | Department of DefenseFA9453 AFRL RVK | FA945319P0542 | 336419 | IGF::OT::IGF STANDARDIZED SCALABLE COMPONENTS FOR ESPA-CLASS POWER SYSTEMS | $150K |
| Dec 6, 2018 | Department of DefenseFA9453 AFRL RVK | FA945319C0597 | 541715 | SHEAR STABILIZATION BASED FRAMEWORK FOR THE FAILURE TESTING AND ANALYSIS OF HSCS | $750K |
| Nov 28, 2018 | Department of DefenseMISSILE DEFENSE AGENCY (MDA) | HQ014719C7040 | 541715 | SBIR/STTR PHASE I RESEARCH&DEVELOPMENT - SYSTEM FOR ULTRAHIGH RATE AND GRAVIMETRICALLY EFFICIENT STORAGE | $99K |
| Nov 19, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0038 | 541712 | TURBINE CERAMIC PARTS MANUFACTURING DEMONSTRATION | $1.2M |
| Nov 19, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0036 | 541712 | TURBINE SUPERALLOY PARTS MANUFACTURING DEMONSTRATION | $1.4M |
| Nov 13, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC019F0032 | 541712 | INDUSTRIAL CRYSTALLIZATION FACILITY FLIGHT DEMONSTRATION | $1.7M |
| Nov 9, 2018 | Department of DefenseDEF ADVANCED RESEARCH PROJECTS AGCY | HR001118C0108 | 541715 | HALO SYSTEM FUNCTIONAL DEVELOPMENT STUDY | $254K |
| Oct 23, 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) | $855K |
| Sep 21, 2018 | Department of the InteriorIBC ACQ SERVICES DIVISION (00063) | 140D6318C0056 | 541715 | EXTERNAL AUGMENTATION OF GENERIC LAUNCH ELEMENTS (EAGLE) SYSTEM | $500K |
| Aug 23, 2018 | Department of DefenseMISSILE DEFENSE AGENCY (MDA) | HQ014715C7215 | 541712 | 7215 PHASE II R&D IGF::OT::IGF FOR OTHER FUNCTIONS | $499K |
| Aug 8, 2018 | Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIV | N6833518C0117 | 541715 | IGF::OT::IGF | $100K |
| Aug 7, 2018 | Department of DefenseDCSO PHILADELPHIA | SP470118P0104 | 541611 | IGF::OT::IGF!8505526102!SERVICES - BASIC | $98K |
| Jul 23, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P1988 | 541715 | MADE IN SPACE, INC. (MIS) IS A GLOBAL LEADER IN MANUFACTURING TECHNOLOGIES FOR HARSH ENVIRONMENTS. MIS DEVELOPED, OWNS AND OPERATES A COMMERCIAL ADDITIVE MANUFACTURING FACILITY (AMF) ABOARD THE INTERNATIONAL SPACE STATION (ISS), USED FOR BOTH GOVERNMENT AND COMMERCIAL USE. OVER MULTIPLE YEARS OF OPERATION, MIS DEVELOPED QUALITY PROCESSES THAT ENSURE THE SUCCESS OF PRINTING IN THE MICROGRAVITY ENVIRONMENT WHICH IS OPERATED AND MONITORED FROM THE GROUND CONTROL STATION AT MIS MOFFETT FIELD FACILITY. THESE PROCESSES INCLUDE GROUND TESTING, COMPUTER MODELING, AND SIMULATIONS OF THE FINAL PRODUCT TO OPTIMIZE MANUFACTURING ON ORBIT. THESE QUALITY PROCESSES ARE KEY TO THE SUCCESSFUL OPERATION OF AMF. MIS CONTINUES TO BREAK NEW GROUND: RECENT SUCCESSES INCLUDE AN OPTICAL FIBER EXPRESS RACK PAYLOAD, THE FIRST OPERATION OF POLYMER ADDITIVE MANUFACTURING IN A SIMULATED LOW EARTH ORBIT ENVIRONMENT, AND A GUINNESS BOOK OF WORLD RECORDS AWARD FOR LONGEST 3D PRINTED STRUCTURE. BUT WHY STOP THERE? MIS HAS BEEN RESEARCHING METAL ADDITIVE MANUFACTURING SINCE ITS FOUNDING. THE VULCAN PHASE I SBIR TECHNOLOGY DEVELOPMENT PROGRAM (TDP) COMBINES METAL ADDITIVE MANUFACTURING WITH TRADITIONAL MANUFACTURING METHODS, ENABLING COMPONENTS TO BE PRODUCED IN GRAVITY INDEPENDENT ENVIRONMENTS. IN DEVELOPING THESE VARIOUS MANUFACTURING TECHNOLOGIES, MIS HAS EXTENSIVELY RESEARCHED NEW VERIFICATION AND VALIDATION (V&V) METHODS TO CONFIRM FABRICATED COMPONENTS MEET THE RIGOROUS STANDARDS REQUIRED FOR AEROSPACE APPLICATIONS. BUILDING ON THE SUCCESSES OF AMF AND SAMEE, A DARPA FUNDED SBIR PHASE I TDP (SECTION 5), AMARU WOULD ENHANCE THE STATE OF THE ART V&V METHODS BY COMBINING AND INTEGRATING ADVANCED SENSOR TECHNOLOGY AND SIEMEN S INDUSTRY LEADING NX SOFTWARE TOOLS. | $125K |
| Jul 23, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P1993 | 541715 | MIS IS PIONEERING THE USE OF THE MICROGRAVITY ENVIRONMENT ON THE INTERNATIONAL SPACE STATION (ISS) FOR MANUFACTURING AND PRODUCT DEVELOPMENT. MIS HAS LEVERAGED NASA SBIR SUPPORT TO CREATE THE FIRST POLYMER ADDITIVE MANUFACTURING MACHINES IN SPACE, DEVELOP A HYBRID ADDITIVE-SUBTRACTIVE METAL MANUFACTURING TECHNOLOGY, AND INVESTIGATE THE CREATION OF LARGE SINGLE-CRYSTAL INDUSTRIAL MATERIALS IN MICROGRAVITY. THE NEXT STEP IN THE INDUSTRIALIZATION OF LEO IS THE FORMULATION OF BASE MATERIALS, SUCH AS SPECIALTY GLASSES, THAT CAN BE REFINED INTO HIGHER VALUE PRODUCTS IN MICROGRAVITY. THE GLASS ALLOY MANUFACTURING MACHINE (GAMMA) IS AN EXPERIMENTAL SYSTEM DESIGNED TO INVESTIGATE HOW THESE MATERIALS FORM WITHOUT THE EFFECTS OF GRAVITY-INDUCED FLOWS AND INFORM PROCESS IMPROVEMENTS FOR COMMERCIAL PRODUCT DEVELOPMENT. WHILE FOCUSED AROUND CREATING FLUORIDE GLASS PREFORMS, THE SYSTEM CAN ALSO BE USED TO MELT A HOST OF GLASS COMPOSITIONS, EXPERIMENT WITH DIFFERENT DOPANTS, AND START THE PROCESS OF CREATING LARGER AND HIGHER QUALITY GLASSES ABOARD THE ISS. THE INITIAL SYSTEM DEVELOPMENT FOCUSES ON REMELTING GLASS MATERIALS ORIGINALLY CREATED ON THE GROUND AND QUANTIFYING DIFFERENCES WITH GROUND CONTROL EXPERIMENTS. HOWEVER, MIS PLANS TRADE STUDIES TO FIND MORE COMPLEX GLASS EXPERIMENTS, SUCH AS PROCESSING THE CONSTITUENT POWDERS INTO SAMPLES, CONTAINERLESS PROCESSING, VARYING GRAVITY LEVELS, AND OTHER EXPERIMENTS WHICH CAN ONLY BE PERFORMED ON THE ISS PLATFORM. | $124K |
| Jul 23, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2057 | 541715 | MADE IN SPACE, INC. (MIS) PROPOSES THE CONSTRUCTION OF LARGE BASELINE STRUCTURES, 15 METERS OR GREATER, FOR INFRARED SPACE INTERFEROMETRY MISSIONS BY AUTONOMOUS IN-SPACE MANUFACTURING AND ASSEMBLY. THIS ENABLES THE DEPLOYMENT OF LARGE PRIMARY TRUSSES UNCONSTRAINED BY LAUNCH LOAD OR VOLUME RESTRICTIONS THAT MEET SCIENCE REQUIREMENTS FOR THE HIGH ANGULAR RESOLUTIONS (LESS THAN 0.3 ARCSECONDS) NECESSARY TO DETECT PLANETS NEAR BRIGHT STARS AND MEASURE INDIVIDUAL OBJECTS IN STAR CLUSTERS. IN THIS PHASE I EFFORT, MIS INVESTIGATES THE MASS, PERFORMANCE, AND MISSION PLANNING BENEFITS OF IN-SPACE MANUFACTURING FOR STRUCTURALLY-CONNECTED INTERFEROMETERS (SCI). MIS IS THE LEADING DEVELOPER OF MANUFACTURING TECHNOLOGIES IN THE SPACE ENVIRONMENT. UTILIZING TECHNOLOGIES DERIVED FROM ARCHINAUT, A NASA TIPPING POINT 2015 AWARD WINNER, LARGE INFRASTRUCTURE CAN BE MANUFACTURED ON ORBIT AND ENABLE A MULTITUDE OF MISSIONS. OPTIMAST IS A SELF-CONTAINED, SCALABLE MACHINE FOR PRODUCING MICROGRAVITY-OPTIMIZED LINEAR STRUCTURES ON-ORBIT, DEVELOPED AS A PRODUCT APPLICATION OF THE ARCHINAUT TECHNOLOGIES. MIS HAS DEVELOPED OPTIMAST TO A TRL-6 WITH SUCCESSFUL THERMAL VACUUM TESTING OF EXTENDED STRUCTURE MANUFACTURING IN 2017. ADAPTING THE MIS OPTIMAST TECHNOLOGY TO PRODUCE LONG BASELINE STRUCTURES WITH LOW THERMAL EXPANSION MATERIALS ENABLES SIMULTANEOUS STRUCTURAL FABRICATION AND POSITIONING OF THE OPTICAL SUBSYSTEMS TO THE REQUIRED ABSOLUTE (STATIC) AND DYNAMIC (THERMAL DEFLECTION AND OSCILLATION) TOLERANCES. AN OPTIMAST-SCI BASELINE STRUCTURE THUS PROVIDES SUPERIOR ABSOLUTE POSITION CONTROL OVER TRADITIONAL DEPLOYABLE STRUCTURES AT MUCH LOWER COST, MASS, AND INTEGRATION COMPLEXITY AND ELIMINATES THE PARASITIC MASS FROM HINGE MECHANISMS AND TRAVERSE RAILS. | $125K |
| Jul 23, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2194 | 541715 | NASA HAS OUTLINED A BOLD VISION FOR FUTURE EXPLORATION ON THE MOON AND MARS. STRUCTURAL HEALTH MONITORING (SHM) PROVIDES NUMEROUS BENEFITS TO THESE FUTURE MISSIONS, INCLUDING INCREASED RELIABILITY, REDUCED MAINTENANCE COST, AND INCREASED MISSION SAFETY. STRUCTURAL HEALTH MONITORING (SHM) PROVIDES NUMEROUS BENEFITS TO FUTURE NASA MISSIONS, INCLUDING INCREASED RELIABILITY, REDUCED MAINTENANCE COST, AND INCREASED MISSION SAFETY. MADE IN SPACE (MIS) HAS DEVELOPED A SUITE OF STRUCTURAL-HEALTH AWARE FAULT-TOLERANT ENGINEERED TO RESPOND (SAFER) MATERIALS THROUGH AN ACTIVE PHASE I STTR PROJECT TO PROVIDE SHM CAPABILITIES. MIS HAS SUCCESSFULLY DEMONSTRATED THE SAFER MATERIALS THROUGH LAB TESTING. THE NEXT STEP IN THE DEVELOPMENT OF THESE MATERIALS IS A DEMO IN SPACE, INCLUDING EXPOSURE TO THE LEO ENVIRONMENT AS WELL AS EXPOSURE TO STIMULI REPRESENTING LOADING CASES. MISSE-FF PROVIDES A PLATFORM FOR IN-SPACE CHARACTERIZATION OF THE SAFER MATERIALS. MIS HAS DEVELOPED AN INNOVATIVE SPACE EXPOSURE FOR STRUCTURAL-HEALTH AWARE MATERIALS EXPERIMENT (SESAME) TO EXPOSE THE SAFER MATERIALS TO THE COMBINED EFFECTS OF THE LEO ENVIRONMENT AND CYCLIC LOADING. SESAME IS AN ACTIVE EXPERIMENT INTENDED TO INTEGRATE WITH THE SAMPLE DECK OF THE STANDARD MISSE SAMPLE CARRIER. SESAME IS AN INNOVATIVE MISSE-FF PAYLOAD FOR EXPOSING AND TESTING CANDIDATE MATERIALS FOR STRUCTURAL HEALTH MONITORING ON FUTURE SPACE EXPLORATION MISSIONS. SESAME USES STANDARD MISSE-FF POWER AND DATA INTERFACES TO SIMPLIFY INTEGRATION OF THE ACTIVE EXPERIMENT INTO EXISTING ISS INFRASTRUCTURE. SPACE EXPOSURE IS CRITICAL FOR FURTHER DEVELOPMENT OF CANDIDATE STRUCTURAL HEALTH MONITORING MATERIALS THAT WILL BE USED IN FUTURE MISSIONS. THE MATERIALS BEING PROPOSED FOR SESAME TESTING HAVE UNIQUE MATERIAL PROPERTIES THAT MAY BE AFFECTED BY SPACE EXPOSURE. FULLY CHARACTERIZING THE EFFECT OF SPACE EXPOSURE WILL HELP MANUFACTURERS AND DESIGNERS BETTER USE THESE SMART MATERIALS FOR GREATER IMPACT ON FUTURE SPACE FLIGHT MISSIONS. | $125K |
| Jul 23, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2197 | 541715 | BASED ON LESSONS LEARNED FROM PREVIOUSLY-FUNDED SBIR WORK FOR DARPA ON IN-SPACE ROBOTIC RECONFIGURATION AND UTILIZATION OF EXISTING FLIGHT-RATED STRUCTURES, MADE IN SPACE, INC. (MIS) PROPOSES THE APEIRON SPACE INTEGRATION SYSTEM TO MEET NASA REQUIREMENTS FOR A MODULAR ASSEMBLY AND INTEGRATION ARCHITECTURE THAT ENABLES THE ROUTINE EXPANSION, UPGRADE, AND REFURBISHMENT OF PERSISTENT ROBOTIC PLATFORMS IN LOW EARTH ORBIT (LEO) AT THE MODULE AND SUBMODULE LEVEL. APEIRON UTILIZES A COMMON ADAPTER PORT, AUTONOMOUS ROBOTIC INTEGRATION AND PAYLOAD HOSTING, AND A SUB-MODULE PALLET SYSTEM TO CREATE RECONFIGURABLE LONG-DURATION SPACE PLATFORMS FROM MODULES THAT FIT WITHIN EXISTING LAUNCH VEHICLE ENVELOPES. BY USING FORM FACTORS COMPATIBLE WITH EXISTING LAUNCH ARCHITECTURES AND AVAILABLE AUTONOMOUS ASSEMBLY TECHNOLOGY, THE APEIRON SPACE INTEGRATION SYSTEM ENABLES A WIDE VARIETY OF PLATFORM CONFIGURATIONS TO BE COST-EFFECTIVELY AND RAPIDLY DEPLOYED BY A VARIETY OF EXISTING LAUNCH VEHICLES. FOR EXAMPLE, APEIRON CAN CREATE A LEO SMALL PAYLOAD STATION FROM THE EXCESS CAPACITY ON A SINGLE EELV FLIGHT. FLIGHTS CARRYING ESPA RINGS LAUNCH ON AVERAGE EVERY TWO MONTHS. THE APEIRON SYSTEM IS CAPABLE OF SEEDING SMALL PAYLOAD STATIONS IN EVERY ORBIT THESE FLIGHTS REACH. THIS ENABLES RAPID AND COST-EFFECTIVE CONSTRUCTION AND COMMISSIONING OF AUTONOMOUS PERSISTENT PLATFORMS IN LEO FROM MASS THAT WOULD OTHERWISE BE DISCARDED, ENABLING A WIDE VARIETY OF REMOTE SENSING, SCIENCE, AND COMMUNICATIONS PAYLOADS TO BE FLOWN AT A MUCH LOWER COST. | $125K |
| Jul 20, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P1969 | 541715 | IN RESPONSE TO NASA S NEED FOR A COMPACT, LOW-COST AND AUTONOMOUS DEPLOYABLE SOLAR ARRAY SYSTEM TO SUPPORT MARTIAN SURFACE EXPLORATION, ROCCOR PROPOSES TO ENHANCE THE MARS COMPACT TELESCOPING SURFACE ARRAY (CTSA) BASELINE DESIGN BY INCORPORATING AN ARTICULATING SOLAR PANEL ENERGY SYSTEM (ASPEN). THE MARS CTSA WAS ESTABLISHED IN 2017 AS THE CULMINATION OF AN EXTENSIVE TRADE PERFORMED AT NASA S LANGLEY RESEARCH CENTER WITH THE GOAL TO SUPPORT HUMAN MARS EXPLORATION. THE ASPEN SYSTEM INCLUDES PV CELLS BONDED TO A THIN MEMBRANE THAT IS Z-FOLDED WHILE STOWED, AND PULLED OUT / TENSIONED WHEN DEPLOYED. THE ASPEN SYSTEM REPLACES TRADITIONAL MEMBRANE PV BLANKETS WITH LIGHTWEIGHT PANELS THAT CAN BE ARTICULATED IN UNISON MUCH LIKE VENETIAN BLINDS. THIS PRESENCE OF ARTICULATION AND RESULTING GAPS BETWEEN SUBSTRATES OFFER UNIQUE ADVANTAGES FOR OPERATION ON THE MARTIAN SURFACE: 1) REDUCED CELL DENSITY LEADING TO INCREASED PERFORMANCE IN COST, W/KG AND KW/M3, 2) IMPLEMENTATION OF ARRAY POROSITY AND ARTICULATION CONTROL TO REDUCE INTERACTION WITH MARTIAN WIND AND MITIGATE DUST COLLECTION, AND 3) MODULAR DESIGN THAT ENABLES MASS PRODUCTION AND EASE OF REPLACEMENT. | $123K |
| Jul 20, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2161 | 541715 | TO ENABLE THE USE OF KILOWATT CLASS FISSION POWER SYSTEMS FOR SURFACE MISSIONS TO THE MOON AND MARS ROCCOR PROPOSES THE DEVELOPMENT OF A FLAT, TITANIUM/WATER HEAT PIPE WITH AN INTEGRATED DEPLOYABLE COMPOSITE RADIATOR. THE PROPOSED DESIGN LEVERAGES ROCCOR S EXPERIENCE IN HIGH STRAIN COMPOSITE DEPLOYABLE STRUCTURES AND TWO-PHASE THERMAL MANAGEMENT PRODUCTS FOR SPACECRAFT APPLICATIONS. HEAT PIPES CURRENTLY PROVIDE A HIGHLY CONDUCTIVE PASSIVE HEAT TRANSFER SOLUTION, BUT TRADITIONAL HEAT PIPES ARE CUMBERSOME TO INTERFACE TO THE STIRLING ENGINE AND RADIATOR PANELS AND DIFFICULT TO BEND TO PROPER CONFIGURATIONS. WHILE THE CURRENT STATE-OF-ART IS ABLE TO HANDLE THE HEAT LOAD, NASA HAS IDENTIFIED DEPLOYABILITY AND THERMAL INTERFACES AS FOCUS AREAS FOR FUTURE THERMAL RADIATORS. ROCCOR PROPOSES TO UTILIZE THEIR FLEXCOOL THIN FLAT HEAT PIPES COUPLED WITH ROCOOL FLEXIBLE CONDUCTIVE MATERIALS (K>1,000 W/M-K), AND WITH ENOUGH STRAIN ENERGY TO PASSIVELY DEPLOY A NOVEL INTEGRATED KILOPOWER RADIATOR. ROCCOR S THIN, FLAT FLEXCOOL HEAT PIPES CAN INTERFACE TO FLAT SURFACE WITH LOW THERMAL RESISTANCE, PROVIDE IMPROVED RADIATOR FIN EFFICIENCY, AND ARE SIMPLE TO BEND. FLEXCOOL WILL ALSO BE COUPLED WITH ROCOOL HIGHLY CONDUCTIVE (K>1,000 W/M-K) FLEXIBLE BLANKET MATERIALS THAT USES PROPRIETARY PROCESSES TO LAMINATE PYROLYTIC GRAPHITE INTO A COMPOSITE RADIATOR MATERIAL THE OVERARCHING PHASE I OBJECTIVE IS TO DEMONSTRATE THE TECHNICAL FEASIBILITY OF THE PROPOSED HEAT PIPE/RADIATOR, AND CONDUCT A PRELIMINARY DESIGN-ANALYSIS-FABRICATION LOOP FOR A 200-WATT PANEL CAPABLE OF MEETING THE REQUIREMENTS FOR SUNPOWER S CURRENT 80W STIRLING ENGINE TECHNOLOGY. THE MATURATION OF THIS TECHNOLOGY WOULD ENABLE THE USE OF FISSION POWER SYSTEMS LARGER THAN 1 KWE WHICH WOULD ENHANCE CURRENT MISSION CAPABILITIES. | $122K |
| Jul 20, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2199 | 541715 | IN RESPONSE TO NASA S NEED FOR LONG-DURATION, LOW-MASS IN-SPACE MODULAR CONSTRUCTION COMPONENTS, ROCCOR PROPOSES TO DEVELOP STRUCTURAL JOINTS DESIGNED FOR RAPID IN-SPACE ASSEMBLY (ISA) AND STRUCTURAL MODULARITY. TRUSSES BUILT OF REPEATING UNIT-CELL/MODULAR ELEMENTS CAN BE ASSEMBLED BY CONNECTING MULTIPLE MODULES TO INTERCONNECTING JOINTS. IMPLEMENTED WITH EMBEDDED CONDUCTORS FOR CONNECTION VERIFICATION, POWER AND DATA TRANSMISSION, THE PROPOSED INVENTION UTILIZES NEAR ZERO CTE COMPOSITE TUBES WITH SNAP-FIT CONNECTORS AND A FLEXIBLE JOINT FOR QUICK, REPEATABLE CONSTRUCTION AND RECONFIGURATION OF TRUSSES IN SPACE. THE CONCENPT, FLEXIBLE I NTERCONNECTING NODES FOR IN-SPACE STRUCTURAL ASSEMBLY (FINESS), WILL ADVANCE ISA OPPORTUNITIES THROUGH INNOVATIVE FEATURES SUCH AS: 1) ASSEMBLY CONNECTIONS AT LOW-WEIGHT, LOW COST, AND MINIMAL PART-COUNT, 2) DEVELOPING RIGID PLUG-AND-PLAY JOINTS FOR CONNECTING MODULES IN VARIOUS ARRANGEMENTS, 3) INTEGRATING CONDUCTIVE ELEMENTS FOR A FULLY CONNECTED STRUCTURE WITH JOINT CONNECTION VERIFICATION, AND 4) NEAR ZERO THERMAL EXPANSION IN CARBON FIBER TUBES AND CONNECTING FIXTURES. THE PRINCIPAL OBJECTIVE FOR THE PHASE I PROJECT IS TO CONDUCT A PRELIMINARY DESIGN-ANALYSIS-FABRICATION-TEST LOOP FOR AN ELECTRICALLY INTEGRATED MODULAR TRUSS JOINT. THE PROJECT WILL CLEARLY IDENTIFY ENGINEERING RISKS THAT MUST BE ADDRESSED TO ENSURE ACCEPTABLE PERFORMANCE ON-ORBIT AND IN GRAVITY LOADED ENVIRONMENTS. DETAILED MECHANICAL AND ELECTRICAL DESIGN WILL BE PERFORMED INCLUDING INVESTIGATION OF ATTAINABLE TRUSS GEOMETRIES, REPEATABLE PLUGAND- PLAY 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 THE MODULAR JOINTS. FURTHERMORE, ELEMENTS OF THE CONCEPT WILL BE PROTOTYPED TO TEST AREAS SUCH AS MODULAR ASSEMBLY AND ELECTRICAL CONTINUITY ACROSS JOINTS. | $124K |
| Jul 18, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18P2116 | 541715 | THIS BODY OF RESEARCH FOCUSES ON DEVELOPING FUNDAMENTAL ENGINEERING QUALIFICATION METHODS FOR THIN-PLY HIGH STRAIN COMPOSITES (TPHSCS). ROCCOR WILL COLLABORATE WITH NASA AND DR. KWOK OF THE UNIVERSITY OF CENTRAL FLORIDA TO DEVELOP AND VALIDATE A ROBUST FRAMEWORK FOR ENGINEERING THE VISCOELASTIC BEHAVIOR OF HIGHLY STRAINED THIN-PLY COMPOSITES. THE MATERIAL SYSTEMS STUDIED WILL BE HIGHLY FOCUSED ON THE MATRIX CONTRIBUTIONS TO THIN PLY COMPOSITE STRUCTURES, WHERE THE FIBERS UTILIZED WILL BE IM7 AND THE LAYUP TYPE WILL BE SPREAD-TOW PLAIN WEAVE WITH A MAXIMUM OF 80 GRAMS PER SQUARE METER. THE ULTIMATE GOAL OF THIS RESEARCH IS TO DEVELOP A ROBUST ANALYSIS AND PREDICTION METHOD WHICH IS MATRIX AGNOSTIC, HOWEVER WITH THE TIMEFRAME OF A PHASE ONE CONTRACT THE INITIAL STUDY WILL ONLY UTILIZE PATZ MATERIALS TECHNOLOGIES F7 (PMT-F7) TOUGHENED, HIGH TEMPERATURE, EPOXY RESIN. PERFORMANCE TASKS OF THIS PROGRAM INCLUDE NEAT-RESIN TEST, COLUMN-BEND TEST, AND DIAMETRICAL COMPRESSION TESTING. EACH TEST WILL AID IN THE DEVELOPMENT OF ROBUST ANALYTICAL METHODS AS WELL AS MATERIAL ALLOWABLE DATABASES MADE AVAILABLE TO THE PUBLIC. FURTHER INVESTIGATION IN A PHASE TWO EFFORT WOULD VALIDATE THE FRAMEWORK AND PUBLISH TEST DATA FOR A REPRESENTATIVE SAMPLE OF SPACE-FLIGHT-GRADE RESIN TYPES INCLUDING AT LEAST ONE OTHER EPOXY, CYANATE ESTER, THERMOPLASTIC (E.G. PEEK, PEKK), AND AT LEAST ONE SYSTEM WITH A NANO-FILLER. | $125K |
| Jun 21, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865018C9221 | 541715 | HIGH POWER SOLAR ARRAY FOR SMALL SATELLITES | $1.5M |
| Jun 20, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0173 | 541715 | IN RESPONSE TO NASA S NEED FOR 1,000M2-10,000M2 CLASS SOLAR SAILS FOR FUTURE EXPLORATION MISSIONS, ROCCOR IS DEVELOPING THE COMPOSITE TRUSSED TRAC (T-TRAC) BOOM SYSTEM. LIKE THE ORIGINAL TRAC BOOM TO BE FLIGHT VALIDATED ON THE UPCOMING NEA (NEAR-EARTH ASTEROID) SCOUT MISSION (MCNUTT, ET AL [2014]), T-TRAC HAS A TRIANGULAR CROSS-SECTION THAT FLATTENS AND ROLLS AROUND A SPOOL FOR PACKAGING. UNLIKE THE ORIGINAL TRAC, T-TRAC IS APPLICABLE TO MUCH LARGER SCALE SAIL SYSTEMS. THE PROPOSED T-TRAC BOOM IS ADVANCING 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 GEOMETRIC MODIFICATION AND CLOSING. PRELIMINARY ANALYSES INDICATE THESE STEPS WILL ACHIEVE MORE THAN A 5X INCREASE IN TRAC BOOM STRUCTURAL MASS EFFICIENCY OVER RECENTLY DEVELOPED HIGH STRAIN COMPOSITE (HSC) TRAC BOOMS, WHILE MAINTAINING AN EXTREMELY COMPACT ROLL STOWED CONFIGURATION THAT LEVERAGES THE SOLAR SAIL MECHANICAL DESIGN HERITAGE ESTABLISHED WITH THE RECENT NANOSAIL D (ALHORN, ET AL [2011]) AND UPCOMING NEA SCOUT TRAC-DEPLOYED SAIL SYSTEMS. THE OVERARCHING PHASE II OBJECTIVE IS TO FURTHER DEVELOP AND MATURE THE T-TRAC TECHNOLOGY SUCH THAT IT CAN BE CONSIDERED FOR NASA S FUTURE MID-SIZED SOLAR SAIL MISSIONS. MULTI-SCALE MICRO-MECHANICS, LAMINATE, CROSS-SECTION, AND FULL SECTION ANALYSES WILL BE PERFORMED TO OPTIMIZE LAMINATE ARCHITECTURE AND TRAC GEOMETRY. THE PHASE II EFFORT WILL CULMINATE IN THE DESIGN, PRODUCTION AND DEMONSTRATION OF A FOUR-BOOM T-TRAC DEPLOYMENT SYSTEM. | $755K |
| Jun 14, 2018 | Department of DefenseDEF ADVANCED RESEARCH PROJECTS AGCY | HR001118C0108 | 541715 | HALO SYSTEM FUNCTIONAL DEVELOPMENT STUDY | $247K |
| Jun 7, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC018F0178 | 541712 | TO#6 AMF- INDUSTRIAL CRYSTAL | $731K |
| Jun 7, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC018F0179 | 541712 | TO#7 AMP - TURBINE CERAMIC | $741K |
| Jun 7, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC018F0180 | 541712 | TO#7 AMP - TURBINE CERAMIC | $740K |
| Jun 5, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0092 | 541715 | MADE IN SPACE, INC. (MIS) PROPOSES THE DEVELOPMENT, TO A CRITICAL DESIGN LEVEL, 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 EXPANDS UTILIZATION OF THE ISS INTO NEW PRODUCT AREAS NOT PREVIOUSLY INVESTIGATED. INTENDED APPLICATIONS INCLUDE NONLINEAR OPTICAL SINGLE CRYSTALS AND OTHER RELATIVELY LARGE MATERIAL FORMULATIONS, SUCH AS BULK SINGLE-CRYSTAL THIN FILMS AND HIGH TEMPERATURE OPTICAL FIBER. THIS IS A CRITICAL NEXT STEP IN THE DEVELOPMENT OF LOW EARTH ORBIT AS AN ECONOMIC DEVELOPMENT ZONE. ICF USES THE INTERNATIONAL SPACE STATION (ISS) NATIONAL LAB AS A PROVING GROUND AND UTILIZES THE SAME VALUE PROPOSITION AS THE FORTHCOMING MADE IN SPACE FIBER (MIS FIBER) DEMONSTRATION OF MANUFACTURING A PRODUCT IN SPACE WITH ECONOMICALLY-SIGNIFICANT INTRINSIC VALUE ON THE GROUND. | $750K |
| May 30, 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) | $700K |
| May 30, 2018 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC18C0123 | 541715 | 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 -U VOLUME. 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. 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 PROGRAM IS DEVELOPMENT AND PROTO-FLIGHT VALIDATION OF A SHROC BOOM SYSTEM FOR A WIDE RANGE OF FUTURE HELIOPHYSICS MISSIONS. | $754K |
| May 24, 2018 | National Aeronautics and Space AdministrationNASA JOHNSON SPACE CENTER | 80JSC018F0164 | 541712 | HRP VALVE PUNCTURE TOOL | $6K |
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