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Award ID | Description | Recipient | Total Value | Awarding Agency | Funding Agency | Set Aside | NAICS | PSC | Award Date | Start Date | End Date | |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| LOW COST ENHANCED CONDUCTIVITY C-C FOR REUSABLE HOT STRUCTURE AND LEADING EDGE APPLICATIONS | ALLCOMP INC. | $124,994 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541715Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Aug 28, 2020 | Aug 28, 2020 | Mar 1, 2021 | ||
| NANO ENHANCED 4000 AOF CMC FOR MULTIPLE USE APPLICATIONS" | ALLCOMP INC. | $749,295 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541715Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Aug 14, 2019 | Aug 14, 2019 | Oct 30, 2021 | ||
| IMPROVED CARBON/CARBON COATINGS FOR DURABILITY IN HIGH HEAT FLUX ENVIRONMENTS | ALLCOMP INC. | $128,798 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541715Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Jul 8, 2019 | Jul 9, 2019 | Apr 3, 2020 | ||
| DEVELOPMENT AND DEMONSTRATION OF SUPPORTABLE AND MANUFACTURABLE LOW OBSERVABLE TECHNOLOGIES (DDSMLOT) TO 0012 | ALLCOMP INC. | $534,370 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541715Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Jun 13, 2019 | Jun 13, 2019 | Oct 29, 2021 | ||
| THERE IS AN URGENT NEED TO DEVELOP LOW-COST, DAMAGE TOLERANT, REUSABLE AND LIGHTWEIGHT HOT STRUCTURE TECHNOLOGY APPLICABLE TO ATMOSPHERIC ENTRY VEHICLES, EXPOSED TO EXTREME TEMPERATURES BETWEEN 1000 C TO 2200 C. ADVANCED CARBON-CARBONS (C-C) AND CARBON FIBER REINFORCED CERAMIC MATRIX COMPOSITES (CMC) ARE THE MOST PROMISING AND POSSIBLY THE MOST AFFORDABLE LIGHT-WEIGHT MATERIAL CANDIDATES FOR THESE IDENTIFIED APPLICATIONS. SINCE MID-1980S, MANY ADVANCEMENTS, INCLUDING BUT NOT LIMITED TO (1) INTERNAL INHIBITION USING GLASS FORMING PARTICULATES (2) OXIDATION RESISTANT CERAMIC MATRICES AND (3) ADVANCED COATING SYSTEMS, HAVE DEMONSTRATED AND HAVE SIGNIFICANTLY IMPROVED THE PERFORMANCES OF CARBON FIBER REINFORCED COMPOSITES UNDER OXIDATIVE ENVIRONMENT AT HIGH TEMPERATURE. UNFORTUNATELY, NONE OF THESE SOTA CMCS EVEN WITH THE ADVANCED AND EXPENSIVE COATING SYSTEM ARE INHERENTLY OXIDATIVE RESISTANT WITH PROVEN RELIABILITY AND THEREFORE ARE NOT CAPABLE TO MEET THE CHALLENGES REQUIRED BY MULTIPLE USAGE APPLICATIONS. IN PHASE I, ALLCOMP PROPOSES TO DEMONSTRATE THE FEASIBILITY OF INHERENTLY OXIDATION RESISTANT C-C AND C-SIC COMPOSITES CAPABLE TO OPERATE BETWEEN 1000 C TO 2200 C BY FINE-TUNING OUR INNOVATIVE NANO-SCALED GLASS FORMING AND INTERNAL INHIBITION TECHNOLOGIES USING SCALABLE AND PRODUCTION-READY PROCESSES. ONCE PROVEN, COUPLED WITH ADVANCED ADHERENT AND CRACK FREE EXTERNAL COATING SYSTEMS CURRENTLY BEING DEVELOPED AT ALLCOMP, THIS NEW CLASS OF CMCS WILL ENABLE HOT STRUCTURES MEETING THE CHALLENGES OF MULTIPLE USES APPLICATIONS UP TO 2000 C (4000 F) WITH SIGNIFICANTLY IMPROVED RELIABILITY AT REDUCED RISKS. | ALLCOMP INC. | $124,824 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541715Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Jul 27, 2018 | Jul 27, 2018 | Feb 15, 2019 | ||
| NASA FUTURE MISSIONS PLACE STRINGENT REQUIREMENTS ON HIGH TEMPERATURE AND LIGHT-WEIGHT MATERIALS.THIS PROPOSAL ADDRESSES SOME OF THE MOST CHALLENGING MATERIALS ISSUES WITH RESPECT TO HOT STRUCTURES, VERY HIGH TEMPERATURE, UP TO 4500 DEGREES F, APPLICATIONS. THE VERY SUCCESSFUL NASA LED X-43A HYPERSONIC FLIGHT PROVED THE ABILITY TO USE STATE OF THE ART (SOTA) 2D C-C WITH OXIDATION COATING SYSTEM. HOWEVER, CURRENT MATERIAL SYSTEMS CAN ONLY OFFER LIMITED TEMPERATURE CAPABILITY (<3000 F) AND MOSTLY FOR SINGLE USE APPLICATION. IN PHASE I, TWO INNOVATIVE TECHNOLOGIES, UNDERCOAT AND FGM MULTI-LAYER COATS, WERE DEVELOPED AND SCREENED. THEY WERE FURTHER INTEGRATED INTO TWO SOTA C-C COMPOSITES. OXIDATION PROTECTED C-C SAMPLES WERE TORCH TESTED AT 3500 F/ 30 MINUTES, AT 4200 F/ 2 MINUTES UP TO 10 CYCLES, AND AT 3000 F/COOL/ 4000 F CYCLES SHOWING VERY PROMISING RESULTS. THE COMBINED EFFECTS OF THE UNDERCOAT AND FGM SPRAY COATS PROVIDE REPEATABLE PERFORMANCE BY CREATING A GLASS FORMING, CONFORMING AND ADHERENT EXTERNAL COATING TO PROTECT THE C-C FROM BEING OXIDIZED. THE OVERALL OBJECTIVE OF THE PROPOSED P-II IS TO FURTHER DEVELOP AND OPTIMIZE A ROBUST, TAILORABLE, AND AFFORDABLE OXIDATION PROTECTION SYSTEM FOR C-C TPS AND C-C HOT STRUCTURE BY INTEGRATING OUR UNDERCOAT AND FGM MULTI-LAYER SPRAY COAT TECHNOLOGIES INTO AT LEAST TWO GRADES C-C COMPOSITES (T300 AND P30 2D C-C) MEETING HIGHER TEMPERATURE PERFORMANCE UP TO 4500 F AND MULTI-USE APPLICATIONS. WORK PLAN INCLUDES 12 TASKS OVER 24 MONTH GROUPED INTO 5 CATEGORIES. ONCE FURTHER OPTIMIZED AND VALIDATED UNDER PHASE II, THESE TECHNOLOGIES CAN EASILY BE INTEGRATED INTO SOTA C-C USING CURRENT MANUFACTURING FACILITIES. THE RESULTING OXIDATION PROTECTED C-C COULD BE TAILORABLE, AFFORDABLE, AND EASILY SCALED UP FOR LARGE COMPONENTS OR STRUCTURE REQUIRED IN FUTURE NASA, DOD AND COMMERCIAL SPACE APPLICATIONS. | ALLCOMP INC. | $746,151 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541715Research and Development in the Physical, Engineering, and Life Sciences (except Nanotechnology and Biotechnology) | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Apr 30, 2018 | Apr 30, 2018 | Sep 25, 2020 | ||
| NON-METALLIC FABRICATED MATERIALS | ALLCOMP INC. | $7,399 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 326130Laminated Plastics Plate, Sheet (except Packaging), and Shape Manufacturing | 9390MISCELLANEOUS FABRICATED NONMETALLIC MATERIALS | Apr 30, 2018 | Apr 30, 2018 | May 27, 2018 | ||
| IGF::OT::IGF THIS PROPOSAL ADDRESSES SOME OF THE MOST CHALLENGING MATERIALS ISSUES WITH RESPECT TO HOT STRUCTURES, VERY HIGH TEMPERATURE, UP TO 4000 DEGREES F, APPLICATIONS. THE VERY SUCCESSFUL, RECORD BREAKING, NASA LED X-43A HYPERSONIC FLIGHT PROVED THE ABILITY TO USE STATE OF THE ART (SOTA) MATERIAL/COATING SYSTEM FOR SHORT DURATION, SINGLE MISSION, AND VERY HIGH TEMPERATURE APPLICATIONS. THE ISSUES ASSOCIATED WITH THE LEADING EDGES ARE QUITE DIFFERENT FROM THE HOT STRUCTURES ISSUES WHERE TRANSVERSE PROPERTIES ARE VERY CRITICAL AND THE LONGER DURATION TIME WITH MUCH WIDER TEMPERATURE DISTRIBUTION CAN BE EXPECTED. ALSO THE SHEAR COMPONENT SIZE MAKES THE APPLICATION OF CVD BASED COATINGS IMPRACTICAL. ALLCOMP PROPOSES AN EXTREMELY INNOVATIVE SOLUTION TO THIS PROBLEM BY USING FUNCTIONALLY GRADED (FGM) PIP COATINGS TO ALLEVIATE INTERFACIAL SHEAR STRESSES AND GREATLY REDUCE TRANSVERSE THERMAL CRACKING, WHICH HISTORICALLY HAVE PLAGUED CERAMIC COATINGS APPLIED TO VERY LOW THERMAL EXPANSION COEFFICIENT 2-D AND 2.5 D C-C COMPOSITE SUBSTRATES. THE SUCCESS OF THIS PHASE I WILL TOTALLY OPEN NEW AVENUES IN THE AREA OF HIGH TEMPERATURE MATERIALS. THAT, IN TURN, WILL ENABLE NASA DESIGNERS TO IMPLEMENT HOT STRUCTURE SOLUTION IN LIEU OF PARASITIC PASSIVE INSULATION SYSTEM, RESULTING IN SIGNIFICANT WEIGHT REDUCTION IN FUTURE NASA SPACE EXPLORATION VEHICLES, AS WELL AS A PLETHORA OF OTHER APPLICATIONS. | ALLCOMP INC. | $124,935 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Jun 8, 2017 | Jun 9, 2017 | Dec 8, 2017 | ||
| IGF::OT::IGF THERE IS A CLEAR NEED TO ADVANCE THE STATE-OF-THE-ART CARBON-CARBON COATED NOZZLE EXTENSIONS (NE) BEYOND THE ENGINE/MISSION PERFORMANCE CURRENTLY ESTABLISHED BY HERAKLES TECHNOLOGY, WHICH IS INTRINSICALLY LIMITED TO ABOUT 3000 F. THE WELL-ESTABLISHED SIC-BASED (CVD, PACK CEMENTATION) TECHNOLOGIES CURRENTLY AVAILABLE ALSO HAVE UPPER TEMPERATURE LIMITS AROUND 3000 F, IMPOSING STRINGENT LIMITATIONS ON INCREASED PERFORMANCE AND SYSTEM LEVEL CHANGES (I.E. HOTTER PROPELLANT) FOR FUTURE NASA MISSIONS. IN ADDITION, THE INTRINSIC CTE MISMATCH BETWEEN C-C SUBSTRATE AND REFRACTORY CARBIDES/OXIDES FURTHER LIMITS THE USE OF MANY OTHER CLASSICAL COATING TECHNOLOGIES. THE SUCCESSFUL PHASE I RESULTS ESTABLISHED THE FEASIBILITY OF OVERCOMING THESE LIMITATIONS THROUGH THE USE OF A NOVEL, FUNCTIONALLY GRADED (FGM) COATING TECHNOLOGY. THE PROPOSED PHASE II BUILDS ON THE SUCCESS OF THE PHASE I PROGRAM AND CLEARLY INCREASES ITS TRL BY OFFERING SUBSCALE COMPONENT TESTING AT REPRESENTATIVE ENGINE CONDITIONS. A SUCCESSFUL PHASE II PROGRAM WILL CLEARLY OFFER A NEW DIMENSION IN THE NOZZLE EXTENSIONS BY OFFERING DIFFERENT COATING SYSTEMS FOR MULTI-CYCLE CAPABILITY AT TEMPERATURES FROM 3000 F UP TO 4000 F. THE EXPECTED ABILITY OF THE COATING TO SURVIVE SUCH AN AGGRESSIVE TESTING COMBINED WITH THE SUFFICIENT RETENTION OF MECHANICAL PROPERTIES OFFERS A DIRECT PATH FOR A PHASE III WITH MANY OF THE COMMERCIAL SPACE PAYLOAD COMPANIES. THE OVERALL APPROACH IS BASED UPON A MULTI-PIECE C-C NE CONCEPT, WHICH FOCUSES THE REQUIREMENTS FOR HIGH TEMPERATURE OXIDATION PROTECTION TO SMALLER DIAMETERS OF THE NOZZLE EXTENSION (E.G. A CONE), ALLOWING THE CVD COATING TECHNOLOGY TO REMAIN WITHIN CURRENT SOTA CVD CAPABILITIES. LARGER DIAMETER SEGMENTS, WHICH ARE EXPOSED TO LOWER TEMPERATURES, WILL UTILIZE NON-CVD LOWER COST TECHNOLOGY WHICH IS WELL SUITED FOR LARGE DIAMETER COMPONENTS. THE DIRECT BENEFIT TO NASA IS UNDISPUTED WITH DIRECT APPLICABILITY TO SEVERAL PLANNED FUTURE MISSIONS, INCLUDING THE VERY CHALLENG | ALLCOMP INC. | $749,311 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | May 31, 2017 | May 31, 2017 | May 30, 2019 | ||
| IGF::OT::IGF QUALIFY ALLCOMP 2D C-C CC2A FOR EXPENDABLE HYPERSONIC | ALLCOMP INC. | $8,093,764 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Feb 7, 2017 | Feb 7, 2017 | Jun 3, 2022 | ||
| IGF::OT::IGF - INNOVATIVE MATERIALS CONCEPTS FOR HYPERSONIC SYSTEMS | ALLCOMP INC. | $749,420 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Jun 15, 2016 | Jun 16, 2016 | Sep 30, 2018 | ||
| IGF::OT::IGF THIS PROPOSAL ADDRESSES SOME OF THE MOST CHALLENGING MATERIALS ISSUES WITH RESPECT TO MULTI-MISSION, VERY HIGH TEMPERATURE, UP TO 4000?F, APPLICATIONS. THE VERY SUCCESSFUL, RECORD BREAKING, NASA LED X-43A HYPERSONIC FLIGHT PROVED THE ABILITY TO USE STATE OF THE ART (SOTA) MATERIAL/COATING SYSTEM FOR SHORT DURATION, SINGLE MISSION, AND VERY HIGH TEMPERATURE APPLICATIONS. THE TRANSITION INTO MULTI-MISSION APPLICATIONS REQUIRES A TOTAL PARADIGM SHIFT. ALLCOMP PROPOSES AN EXTREMELY INNOVATIVE SOLUTION TO THIS PROBLEM BY USING FUNCTIONALLY GRADED (FGM) CVD COATINGS TO ALLEVIATE INTERFACIAL SHEAR STRESSES AND GREATLY REDUCE TRANSVERSE THERMAL CRACKING, WHICH HISTORICALLY HAVE PLAGUED CERAMIC COATINGS APPLIED TO VERY LOW THERMAL EXPANSION COEFFICIENT 2-D C-C COMPOSITE SUBSTRATES. THE SUCCESS OF THIS PHASE I WILL TOTALLY OPEN NEW AVENUES IN THE AREA OF HIGH TEMPERATURE MATERIALS. THAT, IN TURN, WILL ENABLE NASA DESIGNERS TO IMPLEMENT HOT STRUCTURE SOLUTION IN LIEU OF PARASITIC PASSIVE INSULATION SYSTEM, RESULTING IN SIGNIFICANT WEIGHT REDUCTION IN FUTURE NASA SPACE EXPLORATION VEHICLES, AS WELL AS A PLETHORA OF OTHER APPLICATIONS. | ALLCOMP INC. | $124,907 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Jun 1, 2016 | Jun 10, 2016 | Dec 9, 2016 | ||
| ::IGF::OT::IGF SBIIR PHASE II RESEARCH&DEVELOPMENT | ALLCOMP INC. | $1,499,447 | MISSILE DEFENSE AGENCY (MDA) | MISSILE DEFENSE AGENCY (MDA) | — | 541712 | AC22NATIONAL DEFENSE R&D SERVICES; ATOMIC ENERGY DEFENSE ACTIVITIES; APPLIED RESEARCH | May 31, 2016 | May 31, 2016 | Dec 31, 2020 | ||
| QUALIFICATION OF NEEDLED C-SIC BASED STRUCTURAL INSULATOR MATERIALS FOR SOLID ROCKET MOTOR DACS: THE NEED FOR A DOMESTICALLY-SOURCED STRUCTURAL COMPOSITE MATERIAL MORE THERMALLY STABLE THAN THE STATE-OF-THE-ART PHENOLIC COMPOSITES HAS BEEN IDENTIFIED AS A KEY ENABLING TECHNOLOGY THAT WILL ADD BETTER CONTROL AUTHORITY TO PINTLE-BASED DIVERT AND ACS THRUSTERS. BY ESTABLISHING A U.S. SUPPLIER OF THIS TYPE OF MATERIAL, BETTER SOURCE CONTROL AND QUALITY CONTROL OF COMPONENTS CAN BE ACHIEVED. IN ADDITION, STRONG STRUCTURAL INSULATORS POSSESSING THERMALLY INSULATIVE, INNATE EROSION RESISTANT PROPERTIES AND THE ABILITY TO BE MADE INTO MULTI-FUNCTIONAL PARTS WILL REDUCE PART COUNT, VOLUME, WEIGHT, AND COST (UP TO 50% REDUCTION). THE CORE C-SIC STRUCTURAL INSULATOR TECHNOLOGY PROPOSED FOR THIS MDA RAPID INNOVATION FUND (RIF) PROGRAM HAS BEEN PROVEN UNDER MDA-FUNDED SBIR PROGRAMS AT ALLCOMP AS WELL AS UNDER THE MDA FUNDED CKV PROGRAM AT BOTH AEROJET ROCKETDYNE AND ATK. THROUGH THIS RIF PROGRAM, ALLCOMP AIMS TO QUALIFY THE MOST RECENT VARIATION OF NEEDLED-PREFORM BASED STRUCTURAL INSULATOR MATERIAL, AS WELL AS ITS PROCESSING METHODOLOGY, IN A TWO YEAR FAST-PACED TESTING PROGRAM PRODUCING A MATERIAL SYSTEM WITH OPTIMUM THERMO-ELASTIC AND STRENGTH PROPERTIES. VALIDATION OF MANUFACTURABILITY WILL BE CONDUCTED THROUGH FULL MATERIAL CHARACTERIZATION TESTING OF MULTIPLE LOTS TO BRING THIS MATERIAL TOWARDS QUALIFICATION ACCEPTANCE AND INCLUSION IN UPCOMING BALLISTIC MISSILE DEFENSE SYSTEM APPLICATIONS SUCH AS SM-3 CKV AND EVOLVED IIA, AND MORE BROADLY, FOR OTHER INITIATIVES, LIKE THE AIRBORNE WEAPON LAYER DACS.. IGF::OT::IGF | ALLCOMP INC. | $2,799,712 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | MISSILE DEFENSE AGENCY (MDA) | — | 541712 | AC22NATIONAL DEFENSE R&D SERVICES; ATOMIC ENERGY DEFENSE ACTIVITIES; APPLIED RESEARCH | Jul 28, 2015 | Jul 28, 2015 | Jan 5, 2019 | ||
| IGF::OT::IGF SBIR I - AFFORDABLE C-SIC COMPOSITES FOR HYPERSONIC STRUCTURAL TPS APPLICATIONS | ALLCOMP INC. | $149,870 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC11NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; BASIC RESEARCH | Jun 19, 2015 | Jun 19, 2015 | Mar 21, 2016 | ||
| IGF::OT::IGF UNDER THE PHASE II PROGRAM WE PLAN TO FOCUS OUR ACTIVITIES AIMING TOWARD DEVELOPING COST EFFECTIVE ROBUST CSIC COMPOSITES FOR HOT STRUCTURE APPLICATIONS. TO THIS END PROCESS OPTIMIZATION AND REFINEMENT FOLLOWED BY MATERIALS PROPERTY GENERATION WILL BE THE MAIN FOCUS OF THE PROGRAM. TO FURTHER REDUCE THE OVERALL RISKS AND RAISE TRL ASSOCIATED WITH THIS MATERIAL AND TECHNOLOGY DEVELOPMENT L GENERIC SUB ELEMENT WILL BE IDENTIFIED BUILT AND TESTED. WE PLAN TO WORK WITH THE NASA TPOC AS WELL AS DR. SURAJ RAWAL OF LOCKHEED ASTRONAUTICS AND DR BRIAN SULLIVAN OF MRD TO IDENTIFY DESIGN AND FABRICATE THIS BUILDING BLOCK ARTICLE FOR LIMITED TESTING AT LOCKHEED DENVER. | ALLCOMP INC. | $749,732 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Jun 16, 2015 | Jun 17, 2015 | Jun 16, 2017 | ||
| IGF::OT::IGF - SBIR PHASE II EFFORT ENTITLED "MANUFACTURING AND STRENGTH IMPROVEMENT FOR THICK CARBON-CARBON LAMINATES" | ALLCOMP INC. | $1,498,915 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE ARMY | — | 541712 | AJ41 | Jan 6, 2015 | Jan 6, 2015 | Oct 5, 2018 | ||
| SBIR PHASE I RESEARCH&DEVELOPMENT. PROPOSAL #: B142-020-0387, TITLE: LOW COST 3-D (MULTI-D) CARBON-CARBON FOR MISSILE APPLICATIONS. IGF::OT::IGF | ALLCOMP INC. | $124,992 | MISSILE DEFENSE AGENCY (MDA) | MISSILE DEFENSE AGENCY (MDA) | — | 541712 | AC22NATIONAL DEFENSE R&D SERVICES; ATOMIC ENERGY DEFENSE ACTIVITIES; APPLIED RESEARCH | Dec 19, 2014 | Dec 22, 2014 | Jul 21, 2015 | ||
| IGF::OT::IGF COMPOSITE TEST PANEL DENSIFIED USING CHEMICAL VAPOR INFILTRATION (CVI) PROCESS | ALLCOMP INC. | $35,000 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | R413 | Aug 15, 2014 | Aug 15, 2014 | Apr 10, 2015 | ||
| IGF::OT::IGF VERY EXTENSIVE R&D EFFORTS OVER THE PAST SEVERAL DECADES RESULTED IN SEVERAL CLASSES OF HIGH TEMPERATURE COMPOSITES OFFERING POTENTIAL FOR FUTURE HYPERSONIC VEHICLES HOT STRUCTURES. OF PARTICULAR INTEREST IS A HYBRID CARBON/SIC MATRIX COMPOSITE UTILIZING CARBON FIBER. THIS CLASS OF COMPOSITE, WHICH UTILIZES PHENOLIC PREPREG TO FORM THE INITIAL COMPOSITE STRUCTURE, LENDS ITSELF TO THE FABRICATION OF LARGE VERY COMPLEX STRUCTURES. TYPICALLY, THESE COMPOSITES ARE DENSIFIED VIA PIP PROCESSING. HOWEVER, THERE ARE DEFICIENCIES IN THIS MATERIAL SYSTEM. THE NATURE OF PIP PROCESSING RESULTS IN AN APPRECIABLE AMOUNT OF OPEN POROSITY, REQUIRING A CVD SIC EXTERNAL COATING FOR OXIDATION PROTECTION. THE APPLICATION OF CVD SIC TO LARGE STRUCTURES IS QUITE LIMITED DUE TO COST FACTORS. ALSO, SINCE THE COMPOSITES ARE FABRICATED USING 2D FABRIC, THE TRANSVERSE MECHANICAL PROPERTIES ARE TYPICALLY LOW. THIS PROPOSAL OFFERS A HIGHLY INNOVATIVE APPROACH TO ALLEVIATE THE ABOVE MENTIONED SHORTCOMINGS. FIRST, IT UTILIZES NANOTECHNOLOGY AT THE COMPOSITE MOLDING STAGE, ENABLING ENHANCED IN PLANE AND TRANSVERSE MECHANICAL PROPERTIES. SECONDLY, IT OFFERS A HIGHLY UNIQUE, NON CVD EXTERNAL COATING TECHNOLOGY. IT ENABLES THE FABRICATION OF LARGE, COMPLEX PARTS WITH GREATLY REDUCED MANUFACTURING COST WHEN COMPARED WITH CONVENTIONAL CVD SIC. | ALLCOMP INC. | $124,953 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | May 22, 2014 | Jun 20, 2014 | Dec 19, 2014 | ||
| IGF::OT::IGF FUTURE NASA HYPERSONIC VEHICLES OFFER A POTENTIAL TO INCORPORATE ADVANCED CERAMIC MATRIX COMPOSITES (CMC). THE KEY CHARACTERISTICS INCLUDE EXCELLENT MECHANICAL PROPERTIES, EXCELLENT THERMAL SHOCK RESISTANCE AND ABILITY TO SURVIVE CYCLIC OXIDATION ENVIRONMENTS. AMONG THE CMC COMPOSITES CARBON FIBER-SIC MATRIX COMPOSITES OFFER EXCELLENT HIGH TEMPERATURE CAPABILITIES. THE HIGHEST SPECIFIC STRENGTH C-SIC COMPOSITES ARE FABRICATED VIA CONVENTIONAL CHEMICAL VAPOR INFILTRATION (CVI) SIC METHOD. THERE ARE SEVERAL LIMITATIONS TO SOTA CVI SIC TECHNOLOGY. FIRST, FIXTURING IS REQUIRED DURING THE PROCESSING. SECONDLY, TRANSVERSE MECHANICAL PROPERTIES ARE QUITE OFTEN DESIGN LIMITING CRITERIA, THIRDLY MANUFACTURING TIMES ARE VERY LONG AND FOURTH THE FABRICATION OF VERY LARGE PARTS IS LIMITED DUE TO HUGE CAPITAL INVESTMENTS REQUIRED FOR VERY LARGE EQUIPMENT NEEDED TO OPERATE AT VERY LOW PRESSURE. THIS PROPOSAL ADDRESSES ALL THE ABOVE STATED LIMITATIONS OF CLASSICAL CVI. FIRST IT OFFERS UNIQUE 3-D PREFORM CAPABLE OF INCREASING TRANSVERSE PROPERTIES WITH MINIMUM DEGENERATION OF THE IN PLANE PROPERTIES. SECONDLY THE PROPOSED PROCESSING ELIMINATES THE NEED OF FIXTURING. THIRDLY, MODIFIED CVI SIC SIGNIFICANTLY REDUCES PROCESSING TIME. AND FOURTH, PHASE II WILL EXTEND TO INCORPORATE EXTREMELY NOVEL ATMOSPHERIC PRESSURE CVI SIC, OFFERING A PARADIGM SHIFT IN CVI SIC BY ALLOWING TO UTILIZE CONVENTIONAL, LOW COST ATMOSPHERIC PRESSURE FURNACES ROUTINELY USED IN HEAT TREATING APPLICATIONS. | ALLCOMP INC. | $97,316 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | May 12, 2014 | Jun 20, 2014 | Dec 19, 2014 | ||
| LEADING EDGE TEST COUPONS | ALLCOMP INC. | $14,592 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 327999All Other Miscellaneous Nonmetallic Mineral Product Manufacturing | 9390MISCELLANEOUS FABRICATED NONMETALLIC MATERIALS | Apr 11, 2014 | Apr 11, 2014 | Apr 30, 2015 | ||
| HIGH CONDUCTIVITY CARBON/CARBON PLATE | ALLCOMP INC. | $14,592 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 327999All Other Miscellaneous Nonmetallic Mineral Product Manufacturing | 9390MISCELLANEOUS FABRICATED NONMETALLIC MATERIALS | Mar 26, 2014 | Mar 26, 2014 | Jul 28, 2014 | ||
| PROGRESS REPORT N132-146 | ALLCOMP INC. | $149,890 | DEPT OF THE NAVY | DEPT OF THE NAVY | — | 541712 | AC61 | Feb 11, 2014 | Feb 11, 2014 | Feb 10, 2015 | ||
| IGF::OT::IGF - 13.3 SBIR PHASE I "AFFORDABLE AND RELIABLE C-C COMPOSITES FOR THICK LOAD-BEARING HOT STRUCTURE" | ALLCOMP INC. | $149,801 | DEPT OF THE ARMY | DEFENSE ADVANCED RESEARCH PROJECTS AGENCY (DARPA) | — | 541712 | AJ41 | Jan 27, 2014 | Jan 31, 2014 | Jan 31, 2015 |