Federal Contractor Profile
Paragon Space Development Corporation
$44M obligated·75 awards·2 agencies·6 NAICS
Federal Contracts
Showing contracts 101–128 of 128 total. Sorted by action date, most recent first. Excludes $0 modifications.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Sep 25, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC17C0021 | 541712 | IGF::OT::IGFPARAGON SPACE DEVELOPMENT CORPORATION AND OUR PARTNER RESEARCH INSTITUTION TEXAS TECH UNIVERSITY (TTU) PROPOSE TO CONTINUE DEVELOPMENT OF A SPACECRAFT HABITAT WASTEWATER RECYCLING SYSTEM THAT INTEGRATES 1) A TTU MEMBRANE AERATED BIOLOGICAL REACTOR (MABR), 2) NAFION MEMBRANE WATER PURIFICATION (NWP) DISTILLATION TECHNOLOGY, AND 3) GAS-PHASE TRACE CONTAMINANT REMOVAL (GTCR) TO REALIZE A LOW-MASS, LOW-VOLUME, CLOSEDLOOP, SUSTAINABLE, AND ULTRA-RELIABLE WATER RECYCLING AND PURIFICATION SYSTEM. IT IS THE COUPLING OF THESE WELL DEVELOPED AND UNDERSTOOD PROCESSES THAT IS NOVEL AND OFFERS A SIGNIFICANT ADVANTAGE OVER STATE OF THE ART (SOA) SPACECRAFT WATER PROCESSING SYSTEMS. THE INTEGRATED WATER RECOVERY ASSEMBLY (IRA) WILL REDUCE CONSUMABLE CONSUMPTION BY REMOVING THE NEED FOR HAZARDOUS CHEMICAL PRETREAT AND MAY ELIMINATE THE NEED FOR AQUEOUSPHASE TREATMENT NOW USED TO REACH POTABLE STANDARDS. IT WILL ALSO SIGNIFICANTLY REDUCE WASTE GENERATION AND INCREASE MATERIAL RECYCLING BY CONVERTING CARBON, HYDROGEN, AND NITROGEN SPECIES INTO USEFUL PRODUCTS SUCH AS H2O, N2, AND CO2. IRA WILL BE LESS COMPLEX, REQUIRE FEWER CONSUMABLES, BE MORE ROBUST, AND MORE SUSTAINABLE THAN SOA SYSTEMS. IRA SHOULD PRODUCE A CONCENTRATED AND DRIED SOLID WASTE STREAM THAT IS ALWAYS CONTAINED AND CONSISTS OF SALTS AND RESIDUAL ORGANIC MATTER. MABR AND NWP HAVE DEVELOPED AS INDEPENDENT SUBSYSTEMS FOR HUMAN SPACEFLIGHT WASTEWATER PROCESSING BUT THEIR UNIQUE ATTRIBUTES HAVE NOT BEEN OPTIMIZED TO FUNCTION TOGETHER AS AN INTEGRATED WASTEWATER RECYCLING SYSTEM. NEITHER IS INDIVIDUALLY CAPABLE OF PRODUCING POTABLE WATER, BUT COMBINED WITH MATURE GTCR TECHNOLOGY, WE PROPOSE THAT IRA REPRESENTS A SIGNIFICANT ADVANCEMENT OVER SOA OF THE ART SPACECRAFT WASTEWATER PROCESSING SYSTEMS. IN SUMMARY, THE INNOVATION WE PROPOSE IS TO COMBINE AND OPTIMIZE ALL THREE STAGES INTO A NOVEL INTEGRATED SYSTEM CAPABLE OF PROCESSING HABITATION WASTEWATER AND PRODUCING CLEAN WATER FOR ALL HABITAT NEEDS. | $750K |
| Sep 23, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | 80NSSC17P1707 | 541712 | IGF::OT::IGF DEVELOPMENT OF 3 FLEXIBLE MLI BLANKETS (SMART) | $13K |
| Sep 18, 2017 | Department of DefenseNSWC DAHLGREN | N0017817C0016 | 541712 | IGF::OT::IGF SBIR PHASE II AWARD TOPIC N152-099 | $105K |
| Sep 12, 2017 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $500K |
| Jun 8, 2017 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $500K |
| Jun 7, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CM42P | 541712 | IGF::OT::IGF TOPIC H3.01 CAPTURES THE NEED FOR ROBUST, MULTIPURPOSE DEPLOYABLE STRUCTURES WITH HIGH PACKING EFFICIENCIES FOR NEXT GENERATION ORBITAL HABITATS. MULTIPLE LAUNCH AND PAYLOAD PROVIDERS HAVE EXPRESSED INTEREST IN REPURPOSING PRESSURE VESSELS AS ON-ORBIT HABITATS AND REQUIRE OUTFITTING FOR SECONDARY STRUCTURE, FLOORS AND DIVIDERS, ECLS DUCTING, THERMAL CONTROL ACCOMMODATION, RADIATION SHIELDING, WIRING, LIGHTING ETC. TO MAKE THE VOLUME FUNCTIONAL. THE PROPOSED INNOVATION USES MULTI-FUNCTIONAL, INTELLIGENT FABRICS IN A TENSIONED MEMBRANE ARCHITECTURE THAT CAN BE DEPLOYED BY MEANS OF (A) PRESSURIZED ANNULUS ENVELOPE THAT WHEN INFLATED, EXPANDS AGAINST THE HABITAT HULL TO ANCHOR THE STRUCTURE WHILE (B) MULTIPURPOSE TELESCOPING TUBES AT THE CORE OF THE HABITAT EXPAND IN THE AXIAL DIRECTION ACROSS THE OPPOSING BULKHEADS TO INDEX THE ANNULUS PRESSURE VESSELS. TENSIONED MEMBRANE STRUCTURES EXHIBIT THE HIGHEST SPECIFIC STIFFNESS OF ANY KNOWN STRUCTURE AND CAN PRODUCE SIGNIFICANT WEIGHT SAVINGS OVER HYBRID STRUCTURAL DESIGNS. INFLATABLE STRUCTURES PACKAGE WELL AND CAN SIGNIFICANTLY REDUCE STOWED VOLUME REQUIREMENTS AND DAMPEN LAUNCH VIBRO-ACOUSTICS. AN INFLATABLE HABITAT STRUCTURE CAN MOST EFFECTIVELY ADDRESS PACKAGING, DEPLOYMENT, DAMAGE TOLERANCE, EASE OF REPAIR AND IN-FLIGHT MAINTENANCE. WITH LIGHTWEIGHT RIGGING, THESE SECONDARY STRUCTURES WILL BE DESIGNED TO BE FULLY REPOSITIONABLE, CREATING A MODULAR APPROACH TO HABITAT OUTFITTING. THE PARAGON/TRLA TEAM WILL DEVELOP A DESIGN THAT PACKAGES EFFICIENTLY, DEPLOYS REPEATABILITY, AND PROVIDES VALUABLE CAPABILITIES INCLUDING A.) MINIMUM MASS, DESIGN SIMPLICITY, MINIMAL PARTS COUNT, B.) A STRUCTURE WHICH FOLDS EFFICIENTLY DEPLOYMENT REPEATABILITY C.) SECONDARY SOFT GOODS FABRICATED WHICH ARE INTEGRATED DURING BUILD-UP YIELDING MINIMAL GROUND HANDLING LOADS, AND D.) FLOORING, WALLS, ECLS AIR FLOW DUCTS, TCS FLUID LOOPS, LIGHTING, ELECTRICAL/DATA LINES, AND RADIATION PROTECTION STRUCTURES ALL INTEGRATED IN UNISON DURING BUILDUP. | $125K |
| Jun 5, 2017 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX17CJ27P | 541712 | IGF::OT::IGF NASA TECHNOLOGY ROADMAP AREA 14 OUTLINES A TURN DOWN GOAL OF 6 TO 1 BY A THERMAL CONTROL SYSTEM OPERATING AT THE SCALE OF KILOWATTS OF HEAT REMOVAL. THESE THERMAL CONTROL SYSTEMS MUST BE DESIGNED TO PERFORM THIS TURN-DOWN AND TURN-UP WITHIN A REQUIRED TIME FRAME RELIABLY AND PREDICTABLY. PARAGON S INNOVATION WILL ACHIEVE THIS WITH LOWER WEIGHT, LESS COMPLEXITY, AND REDUCED COSTS, ALL WHILE MAINTAINING A HIGHLY FLEXIBLE DESIGN. THE CONTROLLED STAGNATION RADIATOR OFFERS THE IDEAL COMBINATION OF MAXIMIZED RADIATOR PERFORMANCE AT HIGH HEAT LOADS AND A HIGH TURNDOWN RATIO VIA CONTROLLED, DETERMINATE STAGNATION AT LOW HEAT LOADS. BY PLACING ONE OR MORE PASSIVE PRESSURE EQUALIZATION DEVICES ON SOME OF THE RADIATOR FLUID TUBES, THAT PORTION OF THE RADIATOR BECOMES MORE RESISTANT TO STALL, AND THOSE TUBES WITHOUT THE INNOVATION WILL BE THE FIRST TO STAGNATE. IN EFFECT, THIS SYSTEM PROVIDES CONTROLLED STAGNATION BY ADDING LOCAL STAGNATION RESISTANCE, RATHER THAN BY ADDING MECHANICAL SYSTEMS WHICH INCREASE COMPLEXITY AND MASS, OR FLOW IMBALANCE WHICH IMPACT DESIGN LOAD PERFORMANCE. SINCE THE IMPLEMENTATION OF THE INNOVATION HAS NO IMPACT TO THE FLOW DISTRIBUTION IN THE DESIGN LOAD CASE THE RADIATOR CAN BOTH BE OPTIMIZED FOR FULL FLOW PERFORMANCE AND BE DESIGNED TO EXHIBIT DETERMINATE PERFORMANCE IN DEEP STAGNATION FOR HIGH TURNDOWN AND INTERMEDIATE LOADS, AS IS REQUIRED OF MODERN SPACECRAFT THERMAL CONTROL SYSTEM DESIGN. THIS IMPROVEMENT UPON THE STATE OF THE ART IS EXPECTED TO MATURE STAGNATION TECHNOLOGY BY GIVING THE SYSTEM GREATLY IMPROVED PERFORMANCE DETERMINACIES WHICH WILL ALLOW THE SOLUTION TO BE BASELINED FOR USE IN NEXT GENERATION SPACECRAFT AND OPTIMIZED FOR ANY APPLICATION WITH MINIMIZED DESIGN CYCLE, TESTING, COST AND SCHEDULE IMPACT. THE INNOVATION CONCEPT IS ALSO HIGHLY COMPATIBLE WITH PARAGON S XRAD RADIATOR MANUFACTURING TECHNIQUE, MEANING THAT ANY SIZE AND ASPECT RATIO OF RADIATOR PANEL CAN BE EASILY MANUFACTURED WITHOUT THE NEED FOR COMPLEX TOOLING. | $125K |
| May 30, 2017 | Department of DefenseNSWC DAHLGREN | N0017817C0016 | 541712 | IGF::OT::IGF SBIR PHASE II AWARD TOPIC N152-099 | $75K |
| May 18, 2017 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $1.0M |
| Apr 26, 2017 | Department of DefenseNSWC DAHLGREN | N0017817C0016 | 541712 | IGF::OT::IGF SBIR PHASE II AWARD TOPIC N152-099 | $200K |
| Mar 29, 2017 | Department of DefenseNSWC DAHLGREN | N0017817C0016 | 541712 | IGF::OT::IGF SBIR PHASE II AWARD TOPIC N152-099 | $100K |
| Mar 20, 2017 | Department of DefenseHQUSSOCOM | H9222217P0047 | 541712 | IGF::OT::IGF SBIR PHASE I USSOCOM TOPIC 4 | $149K |
| Mar 13, 2017 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $500K |
| Feb 22, 2017 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG14LN47D | 336419 | IGF::OT::IGF SMALL BUSINESS SET-ASIDE, 63 OFFERS PLACE OF PERFORMANCE: VENDOR SITE FABRICATION OF COMMERCIAL SERVICES AND SUPPLIES FOR GODDARD SPACE FLIGHT CENTER THE ADVANCED MANUFACTURING BRANCH (AMB) IS RESPONSIBLE FOR MAINTAINING A COMPLETE MANUFACTURING FACILITY TO MEET THE CENTER'S RESEARCH AND DEVELOPMENT REQUIREMENTS AND ASSIST IN THE FABRICATION OF HARDWARE REQUIREMENTS FROM MULTIPLE NASA PROJECT MISSIONS. THIS FACILITY INCLUDES CONVENTIONAL MACHINING EQUIPMENT, NUMERICALLY CONTROLLED (NC) MACHINING CENTERS, SHEET METAL AND WELDING FABRICATION EQUIPMENT AND REMOTELY LOCATED STAFF SHOPS. VENDORS SHALL PROVIDE FABRICATION SERVICES AND SUPPLIES TO THE MANUFACTURING ENGINEERING GROUP IN THEIR RESPECTIVE AREAS OF EXPERTISE FOR THE DEVELOPMENT OF INSTRUMENTS AND SPACE FLIGHT AND NON-SPACEFLIGHT HARDWARE INTERCHANGEABLE PIECE PARTS. VENDORS WILL MANUFACTURE PER ENGINEERING DRAWINGS WITH AEROSPACE INDUSTRY TOLERANCES AND PROVIDE FABRICATION CAPABILITIES IN ACCORDANCE WITH THE STATEMENT OF WORK. TO FABRICATE CLOSE TOLERANCE AEROSPACE INSTRUMENTS AND SPACE FLIGHT GRADE PARTS, IN VARIOUS MATERIALS SUCH AS (BUT NOT LIMITED TO) ALUMINUM, TITANIUM, HIGH STRENGTH STEEL AND NICKEL ALLOY, ENGINEERING PLASTICS, AND COMPOSITES BASED ON INDUSTRY ENGINEERING DRAWINGS, PROVIDED IN ELECTRONIC FORMAT, TO INDUSTRY STANDARD TOLERANCES AND SPECIFICATIONS. PARTS MAY RANGE IN COMPLEXITY FROM VERY SIMPLE TO VERY COMPLEX, WITH QUANTITIES. EACH DISCIPLINE IS FURTHER DIVIDED INTO SUBCATEGORIES BASED ON THE EXPECTED SIZE OF FABRICATED PARTS. THE FABRICATIONS OF PRODUCTS OR SERVICES PROPOSED AS "SPACEFLIGHT" ARE REQUIRED TO BE, ISO 900I OR AS9100 COMPLAINT, ITEMS PROPOSED AS "NON-FLIGHT" WILL NOT REQUIRE RESPONDENTS TO BE ISO 9001 OR AS9100 COMPLIANT. OFFERS SHALL INDICATE IF THEY ARE ISO 9001 OR AS9100 COMPLAINT AND PROVIDE SUPPORTING DOCUMENTATION. | $12K |
| Jan 30, 2017 | National Aeronautics and Space AdministrationNASA GODDARD SPACE FLIGHT CENTER | NNG14LN47D | 336419 | IGF::OT::IGF SMALL BUSINESS SET-ASIDE, 63 OFFERS PLACE OF PERFORMANCE: VENDOR SITE FABRICATION OF COMMERCIAL SERVICES AND SUPPLIES FOR GODDARD SPACE FLIGHT CENTER THE ADVANCED MANUFACTURING BRANCH (AMB) IS RESPONSIBLE FOR MAINTAINING A COMPLETE MANUFACTURING FACILITY TO MEET THE CENTER'S RESEARCH AND DEVELOPMENT REQUIREMENTS AND ASSIST IN THE FABRICATION OF HARDWARE REQUIREMENTS FROM MULTIPLE NASA PROJECT MISSIONS. THIS FACILITY INCLUDES CONVENTIONAL MACHINING EQUIPMENT, NUMERICALLY CONTROLLED (NC) MACHINING CENTERS, SHEET METAL AND WELDING FABRICATION EQUIPMENT AND REMOTELY LOCATED STAFF SHOPS. VENDORS SHALL PROVIDE FABRICATION SERVICES AND SUPPLIES TO THE MANUFACTURING ENGINEERING GROUP IN THEIR RESPECTIVE AREAS OF EXPERTISE FOR THE DEVELOPMENT OF INSTRUMENTS AND SPACE FLIGHT AND NON-SPACEFLIGHT HARDWARE INTERCHANGEABLE PIECE PARTS. VENDORS WILL MANUFACTURE PER ENGINEERING DRAWINGS WITH AEROSPACE INDUSTRY TOLERANCES AND PROVIDE FABRICATION CAPABILITIES IN ACCORDANCE WITH THE STATEMENT OF WORK. TO FABRICATE CLOSE TOLERANCE AEROSPACE INSTRUMENTS AND SPACE FLIGHT GRADE PARTS, IN VARIOUS MATERIALS SUCH AS (BUT NOT LIMITED TO) ALUMINUM, TITANIUM, HIGH STRENGTH STEEL AND NICKEL ALLOY, ENGINEERING PLASTICS, AND COMPOSITES BASED ON INDUSTRY ENGINEERING DRAWINGS, PROVIDED IN ELECTRONIC FORMAT, TO INDUSTRY STANDARD TOLERANCES AND SPECIFICATIONS. PARTS MAY RANGE IN COMPLEXITY FROM VERY SIMPLE TO VERY COMPLEX, WITH QUANTITIES. EACH DISCIPLINE IS FURTHER DIVIDED INTO SUBCATEGORIES BASED ON THE EXPECTED SIZE OF FABRICATED PARTS. THE FABRICATIONS OF PRODUCTS OR SERVICES PROPOSED AS "SPACEFLIGHT" ARE REQUIRED TO BE, ISO 900I OR AS9100 COMPLAINT, ITEMS PROPOSED AS "NON-FLIGHT" WILL NOT REQUIRE RESPONDENTS TO BE ISO 9001 OR AS9100 COMPLIANT. OFFERS SHALL INDICATE IF THEY ARE ISO 9001 OR AS9100 COMPLAINT AND PROVIDE SUPPORTING DOCUMENTATION. | $6K |
| Dec 14, 2016 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $1.0M |
| Dec 6, 2016 | Department of DefenseOFFICE OF NAVAL RESEARCH | N0001417P2015 | 541712 | SBIRSOL2016.2 IGF::CT::IGF | $80K |
| Sep 20, 2016 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $400K |
| Aug 16, 2016 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $400K |
| Aug 1, 2016 | Department of DefenseNAVSEA HQ | N0002416P4500 | 541712 | IGF::OT::IGF STATUS REPORT | $69K |
| Jun 28, 2016 | National Aeronautics and Space AdministrationNASA HEADQUARTERS | NNH16CL01C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE TECHNOLOGY MATURATION (TA 207) OBJECTIVE IS TO RECOVER GREATER THAN 98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). THIS CONTRACT IS FOR THE DEVELOPMENT OF IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR FOR FLIGHT DEMONSTRATION ON THE INTERNATIONAL SPACE STATION (ISS). REQUIREMENTS FOR THE BRINE PROCESSOR WILL BE BASELINED BY NASA AND AGREED TO BY THE CONTRACTOR UNDER THE PHASE III SBIR NNX16CJ02C. AN ISS FLIGHT DEMONSTRATION IS NEEDED TO VALIDATE AND FULLY CHARACTERIZE BRINE PROCESSOR SYSTEM PERFORMANCE IN A RELEVANT ENVIRONMENT FOR FUTURE EXPLORATION MISSIONS. THE RELEVANT ENVIRONMENT IN THIS CASE INCLUDES BOTH MICRO-GRAVITY AND LONG-DURATION EXPOSURE TO MICRO-G CREW-PRODUCED BRINE VIA THE URINE PROCESSOR. THE BRINE PROCESSOR WILL BE FLOWN AS A CLASS 1E PIECE OF HARDWARE. TASKS INCLUDE 1) COMPLETE TECHNOLOGY MATURATION OF KEY COMPONENT SUBSYSTEMS OF THE IWP FROM THE PHASE III SBIR INCLUDING BLADDER HEAT SEALING, LOW-PROFILE SIDE-MOUNTED FILL PORT, DETRUSOR AND SYSTEM COMPATIBILITY WITH INADVERTENT EXPOSURE TO 14.7 PSIG DURING BRINE FILL; 2) SYSTEM DESIGN CYCLE INCLUDING HEATER AND ENERGY MANAGEMENT TRADE; 3) INTEGRATED SYSTEM AND COMPONENT PRELIMINARY DESIGN; 4) INTEGRATED SYSTEM AND COMPONENT FINAL DESIGN AND REVIEW; 5) MANUFACTURING OF ONE COMPLETE IWP ASSEMBLY, 42 BLADDERS (18 FOR QUALIFICATION TESTING AND 24 FOR FLIGHT), ONE NON-OPERATING TRAINING UNIT WITH SPARES; 6) PROTOFLIGHT QUALIFICATION TESTING AND BLADDER ACCEPTANCE TESTING; 7) HARDWARE ACCEPTANCE REVIEW AND DELIVERY OF A BRINE PROCESSOR AND ASSOCIATED CONSUMABLES, FOR AN ISS TECHNOLOGY DEMONSTRATION; 8) POST-DELIVERY AND ON-ORBIT SUPPORT WHICH INCLUDES GENERATION OF OPERATIONS AND MAINTENANCE HANDBOOK FOR USE BY NASA IN SUPPORT OF CREW TRAINING AND THE DEVELOPMENT OF ON-ORBIT OPERATIONS AND MAINTENANCE, CREW TRAINING SUPPORT, AND ON-ORBIT OPERATIONS SUPPORT AND SUPPORT WITH NASA ON-ORBIT ANOMALY RESOLUTION AND GENERATION OF AN ON-ORBIT TEST REPORT WITH LESSONS LEARNED AND RECOMMENDATIONS FOR IMPROVEMENTS. | $400K |
| Jun 13, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CM07C | 541712 | IGF::OT::IGF THE CRYOGENIC ENCAPSULATING LAUNCH SHROUD AND INSULATED UPPER STAGE (CELSIUS) INNOVATIVE LAYERED SYSTEM COMBINES FUNCTIONS OF MULTI-LAYER INSULATION (MLI), MICRO-METEOROID AND ORBITAL DEBRIS (MMOD) PROTECTION, AND FAIRING FUNCTIONS (EXPOSURE TO FREE STREAM) INTO A DETERMINISTIC SOFT-GOODS SYSTEM THAT PROVIDES FAR GREATER PERFORMANCE FOR FAR LESS MASS THAN THE EQUIVALENT STATE OF THE ART (SOTA) SYSTEMS PERFORMING THE SAME FUNCTIONS. CELSIUS PROVIDES NEARLY PERFECT RADIATION DOMINATED THERMAL PERFORMANCE. A 5 LAYER SYSTEM MLI/MMOD SYSTEM LIMITS HEAT LOAD TO A CRYOGEN TO<0.5 W/M ^2 AND GIVES>95% PROBABILITY OF NO PENETRATION FOR A TWO YEAR MISSION IN LOW EARTH ORBIT AND IS READILY SCALABLE TO OTHER MISSION TYPES. THE SYSTEM IS APPLICABLE TO LARGE STRUCTURES, INCLUDING CRYOGENIC TANKS. FURTHERMORE CELSIUS IS ROBUST ENOUGH TO TOLERATE THE VIBRATIONS, LOAD, DYNAMIC PRESSURES, AND HEATING OF THE LAUNCH ASCENT ENVIRONMENT ALLOWING IT TO PROTECT NEARLY ANY PORTION OF THE LAUNCH STACK UP TO AND INCLUDING SERVING AS A COMPLETE LAUNCH FAIRING. OUR PHASE II EFFORT MATURES THE CONCEPT THROUGH ANALYSIS, DESIGN, SUBSCALE TEST AND VALIDATION ACTIVITIES; INCLUDING SIMULATION OF THE HIGHEST RISK AREAS OF FREE-STREAM EXPOSER AND VIBRATION AT LAUNCH FOLLOWED BY SYSTEM DEPLOYMENT WHILE AT CRYOGENIC COLD-SOAK. THIS EFFORT SIGNIFICANTLY IMPROVES THE TRL OF THE SYSTEM AND WE EXIT PHASE II WITH COMPLETE VALIDATION AND HAVING COMPLETED A PRELIMINARY DESIGN CYCLE IN SUPPORT OF TECHNOLOGY INSERTION ONTO THE CELSIUS HAS APPLICATION TO NASA AS AN INSULATION SOLUTION FOR THE EXPOSED HYDROGEN TANK BARREL SECTION ON THE SLS EXPLORATION UPPER STAGE (EUS). CELSIUS CAN, FOR MINIMAL MASS PROVIDE ASCENT-TO-ORBIT PROTECTION FOR THE BARREL SECTION AND EXCELLENT LONG TERM THERMAL AND MMOD PROTECTION. CELSIUS WILL GREATLY EXTEND THE EUS ON-ORBIT LIFE PROVIDING NASA IMPROVED MISSION FLEXIBILITY FOR EXPLORATION MISSIONS. CELSIUS ALSO HAS FUTURE APPLICATION FOR ORBITAL PROPELLANT DEPOTS, HABITATS, AND AS A COMPLETE LAUNCH FAIRING SOLUTION. IN THIS ROLE, CELSIUS MAY BE AN ENABLING TECHNOLOGY THAT PROVIDES A SINGLE SOLUTION TO THE GROUND-TO-ORBIT AND LONG TERM ONORBIT STORAGE OF CRYOGENIC PROPELLANTS. WITH CELSIUS THERE IS NEVER A MOMENT WHEN THE CRYOGENIC SYSTEM IS UNPROTECTED, NOR IS TRANSFER NEEDED. THE CELSIUS FAIRING AND INSULATION SYSTEM IS CARRIED DIRECTLY TO ORBIT AND REMAINS TO PROTECT THE CRYOGEN SYSTEM FROM THE DURATION OF ITS USEFUL LIFE. CELSIUS IS BEING INVESTIGATED FOR GROUND APPLICATIONS FOR IMPROVED CRYOGENIC INSULATION. THIS IS A PARTICULARLY LARGE COST FOR NASA, THE UNITED STATES AIR FORCE, AND COMMERCIAL LAUNCH PROVIDERS WHO MUST MAINTAIN FACILITIES AND PRODUCE OR DELIVER CRYOGENIC PROPELLANTS IN LARGE QUANTITIES IN SOME OF THE WARMEST AND MOST HUMID REGIONS OF THE COUNTRY. | $748K |
| Jun 6, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CJ18P | 541712 | IGF::OT::IGF PARAGON SPACE DEVELOPMENT CORPORATION AND OUR PARTNER RESEARCH INSTITUTION TEXAS TECH UNIVERSITY (TTU) PROPOSE TO DEVELOP A SPACECRAFT HABITAT WASTEWATER RECYCLING SYSTEM THAT INTEGRATES 1) THE TTU MEMBRANE AERATED BIOLOGICAL REACTOR (MABR), 2) NAFION MEMBRANE WATER PURIFICATION (NWP) DISTILLATION TECHNOLOGY, AND 3) GAS-PHASE TRACE CONTAMINANT REMOVAL TO REALIZE A LOW-MASS, LOW-VOLUME, CLOSED-LOOP, SUSTAINABLE, AND ULTRA-RELIABLE WATER RECYCLING AND PURIFICATION SYSTEM. IT IS THE COUPLING OF THESE THREE WELL DEVELOPED AND UNDERSTOOD PROCESSES THAT IS NOVEL AND OFFERS A SIGNIFICANT ADVANTAGE OVER STATE OF THE ART (SOA) SPACECRAFT WATER PROCESSING SYSTEMS. THE INTEGRATED WATER RECOVERY ASSEMBLY (IRA) WILL REDUCE CONSUMABLE CONSUMPTION BY REMOVING THE NEED FOR HAZARDOUS CHEMICAL PRETREAT AND LIKELY ELIMINATE THE NEED FOR AQUEOUS-PHASE TREATMENT NOW USED TO REACH POTABLE STANDARDS. IT WILL ALSO SIGNIFICANTLY REDUCE WASTE GENERATION AND INCREASE MATERIAL RECYCLING BY CONVERTING CARBON, HYDROGEN, AND NITROGEN SPECIES INTO USEFUL PRODUCTS SUCH AS H2O, N2, AND CO2. IRA WILL BE LESS COMPLEX, REQUIRE FEWER CONSUMABLES, BE MORE ROBUST, AND MORE SUSTAINABLE THAN SOA SYSTEMS. IRA WILL ALSO PRODUCE A CONCENTRATED AND DRIED SOLID WASTE STREAM THAT IS ALWAYS CONTAINED AND THAT WILL CONSIST OF SALTS AND RESIDUAL ORGANIC MATTER. MABR AND NWP HAVE DEVELOPED AS INDEPENDENT SUBCOMPONENTS FOR HUMAN SPACEFLIGHT WASTEWATER PROCESSING BUT THEIR UNIQUE ATTRIBUTES HAVE NOT BEEN OPTIMIZED TO FUNCTION TOGETHER AS AN INTEGRATED WASTEWATER RECYCLING SYSTEM. NEITHER IS INDIVIDUALLY CAPABLE OF PRODUCING POTABLE WATER, BUT COMBINED WITH GAS PHASE TRACE CONTAMINANT CONTROL, WE PROPOSE THAT IRA REPRESENTS A SIGNIFICANT ADVANCEMENT OVER SOA OF THE ART SPACECRAFT WASTEWATER PROCESSING SYSTEMS. IN SUMMARY, THE INNOVATION WE PROPOSE IS TO COMBINE AND OPTIMIZE ALL THREE STAGES INTO A NOVEL INTEGRATED SYSTEM CAPABLE OF PROCESSING HABITATION WASTEWATER AND PRODUCING CLEAN WATER FOR ALL HABITAT NEEDS. | $125K |
| May 12, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CJ21P | 541712 | IGF::OT::IGF PARAGON SPACE DEVELOPMENT CORPORATION AND THIN RED LINE AEROSPACE (TRLA) PROPOSE A UNIQUE SOLUTION THAT THERMALLY ISOLATES THE UPPER STAGE ROCKET FROM A PAYLOAD ON ORBIT WHILE STILL PROVIDING ADEQUATE STRUCTURAL CONNECTION FOR ORBITAL MANEUVERS. CRYOGENIC FLUIDS SUCH AS LH2 AND LOX ARE IDEAL UPPER STAGE PROPELLANTS BECAUSE OF THEIR HIGH SPECIFIC IMPULSE. UNFORTUNATELY, THE HIGH THERMAL CONDUCTIVITY OF THE ADAPTER AND PAYLOAD INTERFACE OR BETWEEN THE O2 AND H2 TANKS THEMSELVES ALLOWS SIGNIFICANT HEAT TRANSFER BETWEEN THE SECTIONS, ULTIMATELY OPENING A RELIEF VALVE THAT VENTS THE PROPELLANT TO SPACE. ONCE VENTED, THE PROPELLANT IS LOST FOREVER RESULTING IN A LIMITED ON-ORBIT USEFUL LIFE FOR CRYOGENIC UPPER STAGES. THE PROPOSED SOLUTION PROVIDES AN INSULATIVE STRUCTURAL CONNECTION BETWEEN THE PAYLOAD AND THE UPPER STAGE UTILIZING AN INFLATABLE ANNULUS WITH PERFORMANCE ATTRIBUTES FROM TRLA'S ULTRA HIGH PERFORMANCE VESSEL (UHPV) TECHNOLOGY THAT PROVIDES AN INFLATABLE STRUCTURE WITH FULLY DETERMINATE LOAD PATHS AND THE HIGHEST SPECIFIC STRENGTH AND STIFFNESS OF ANY SOFT-GOODS ARCHITECTURE. BY USING THE EXISTING PAYLOAD ADAPTER TECHNOLOGY AND SEPARATION SYSTEMS FOR THE ASCENT, THE LONG HERITAGE AND RELIABILITY OF THESE SYSTEMS ARE MAINTAINED. ONCE ON ORBIT, THE PRIMARY STRUCTURAL CONNECTION BETWEEN PAYLOAD AND ADAPTER SEPARATE AS NORMAL WHILE THE INFLATABLE STRUCTURE IS DEPLOYED. THE PRESSURIZED FABRIC RING ACTS AS A THERMAL INSULATOR SIGNIFICANTLY REDUCING THE UNDESIRED HEAT LEAK WHILE STILL PROVIDING STRUCTURAL CHARACTERISTICS AT 0.2 G'S OF SUSTAINED COMPRESSIVE LOADS FOR STATION KEEPING, ATTITUDE CONTROL AND TELEMETRY. THE INNOVATION WILL ULTIMATELY ALLOW CRYOGENIC PROPELLANTS STORED IN AN ON-ORBIT DEPOT TO HAVE A LONGER STORAGE LIFE WHILE STILL UTILIZING THE SERVICES OF AN ATTACHED UPPER STAGE. ADDITIONALLY, IT WILL ALLOW AN UPPER STAGE WITH A CONVENTIONAL PAYLOAD TO LOITER FOR LONGER PERIODS IN LEO BEFORE TOO MUCH PROPELLANT BOILS OFF. | $125K |
| Feb 18, 2016 | National Aeronautics and Space AdministrationGODDARD SPACE FLIGHT CENTER | NNG14LN47D | 336419 | IGF::OT::IGF SMALL BUSINESS SET-ASIDE, 63 OFFERS PLACE OF PERFORMANCE: VENDOR SITE FABRICATION OF COMMERCIAL SERVICES AND SUPPLIES FOR GODDARD SPACE FLIGHT CENTER THE ADVANCED MANUFACTURING BRANCH (AMB) IS RESPONSIBLE FOR MAINTAINING A COMPLETE MANUFACTURING FACILITY TO MEET THE CENTER'S RESEARCH AND DEVELOPMENT REQUIREMENTS AND ASSIST IN THE FABRICATION OF HARDWARE REQUIREMENTS FROM MULTIPLE NASA PROJECT MISSIONS. THIS FACILITY INCLUDES CONVENTIONAL MACHINING EQUIPMENT, NUMERICALLY CONTROLLED (NC) MACHINING CENTERS, SHEET METAL AND WELDING FABRICATION EQUIPMENT AND REMOTELY LOCATED STAFF SHOPS. VENDORS SHALL PROVIDE FABRICATION SERVICES AND SUPPLIES TO THE MANUFACTURING ENGINEERING GROUP IN THEIR RESPECTIVE AREAS OF EXPERTISE FOR THE DEVELOPMENT OF INSTRUMENTS AND SPACE FLIGHT AND NON-SPACEFLIGHT HARDWARE INTERCHANGEABLE PIECE PARTS. VENDORS WILL MANUFACTURE PER ENGINEERING DRAWINGS WITH AEROSPACE INDUSTRY TOLERANCES AND PROVIDE FABRICATION CAPABILITIES IN ACCORDANCE WITH THE STATEMENT OF WORK. TO FABRICATE CLOSE TOLERANCE AEROSPACE INSTRUMENTS AND SPACE FLIGHT GRADE PARTS, IN VARIOUS MATERIALS SUCH AS (BUT NOT LIMITED TO) ALUMINUM, TITANIUM, HIGH STRENGTH STEEL AND NICKEL ALLOY, ENGINEERING PLASTICS, AND COMPOSITES BASED ON INDUSTRY ENGINEERING DRAWINGS, PROVIDED IN ELECTRONIC FORMAT, TO INDUSTRY STANDARD TOLERANCES AND SPECIFICATIONS. PARTS MAY RANGE IN COMPLEXITY FROM VERY SIMPLE TO VERY COMPLEX, WITH QUANTITIES. EACH DISCIPLINE IS FURTHER DIVIDED INTO SUBCATEGORIES BASED ON THE EXPECTED SIZE OF FABRICATED PARTS. THE FABRICATIONS OF PRODUCTS OR SERVICES PROPOSED AS "SPACEFLIGHT" ARE REQUIRED TO BE, ISO 900I OR AS9100 COMPLAINT, ITEMS PROPOSED AS "NON-FLIGHT" WILL NOT REQUIRE RESPONDENTS TO BE ISO 9001 OR AS9100 COMPLIANT. OFFERS SHALL INDICATE IF THEY ARE ISO 9001 OR AS9100 COMPLAINT AND PROVIDE SUPPORTING DOCUMENTATION. | $5K |
| Feb 17, 2016 | National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER | NNX16CJ02C | 541712 | IGF::OT::IGF RECOVERY OF POTABLE WATER FROM WASTEWATER IS ESSENTIAL TO THE SUCCESS OF LONG-DURATION HUMAN SPACEFLIGHT. FOR HUMAN MISSIONS TO MARS, THE NASA GOAL IS TO RECOVER>98 PERCENT OF THE WATER FROM WASTEWATER SOURCES (URINE, HUMIDITY CONDENSATE, ETC.). PRESENTLY THE ISS IS ABLE TO RECOVER 75 PERCENT OF WATER FROM THESE SOURCES. TO REACH AGENCY GOALS, THE DEVELOPMENT OF A BRINE PROCESSOR IS REQUIRED. THIS SBIR CONTINUES DEVELOPMENT OF THE IONOMER-MEMBRANE WATER PROCESSOR (IWP) BRINE PROCESSOR. | $370K |
| Nov 17, 2015 | Department of DefenseNAVSEA HQ | N0002416P4500 | 541712 | IGF::OT::IGF STATUS REPORT | $80K |
| Nov 3, 2015 | National Aeronautics and Space AdministrationGODDARD SPACE FLIGHT CENTER | NNG14LN46D | 336419 | IGF::OT::IGF COMPREHENSIVE FABRICATION NEEDS FOR SPACEFLIGHT HARDWARE PARTS, INSTRUMENT COMPONENTS, STRUCTURES, FIXTURES, ASSEMBLY TOOLS, SPACE VEHICLE PARTS, ETC.; ASSEMBLY OF FABRICATED ITEMS AND ALL REQUIRED DOCUMENTATION. THE CONTRACTOR SHALL MANUFACTURE, ASSEMBLE, AND PREPARE DOCUMENTATION FOR SPACEFLIGHT AND NON-FLIGHT PARTS IN SUPPORT OF THE MANUFACTURING ENGINEERING GROUP AND GSFC PROJECTS. THE CONTRACTOR SHALL PROVIDE THE REQUIRED PERSONNEL, FACILITIES, AND MATERIALS, UNLESS OTHERWISE PROVIDED BY THE GOVERNMENT, TO ACCOMPLISH THE ISSUED DELIVERY ORDERS. THE CONTRACTOR SHALL PROVIDE EMERGENCY REPAIR OR MODIFICATION IN SUPPORT OF REJECTED OR DEFECTIVE CRITICAL ITEMS; THIS INCLUDES PERFORMING REPAIR OR MODIFICATION AND RETURNING TO GSFC WITHIN A NEGOTIATED TIME FRAME PER DELIVERY ORDER. THE CONTRACTOR SHALL FACILITATE TECHNICAL INTERCHANGE MEETINGS AT THE CONTRACTOR S FABRICATION FACILITY FOR DESIGN INTERPRETATION FOR WORK IN PROGRESS AND CONTRACTOR/END-USER COLLABORATION FOR CRITICAL ITEMS WITHIN A NEGOTIATED TIME FRAME PER DELIVERY ORDER. CRITICAL ITEMS ARE DEFINED AS THOSE SPACEFLIGHT AND GROUND SUPPORT ITEMS HAVING A SIGNIFICANT IMPACT ON TEST SCHEDULES, ASSEMBLY SCHEDULES, OR SHIPPING SCHEDULES AFFECTING LAUNCH SCHEDULES. APPROXIMATELY 40% OF THE WORK TO BE PERFORMED ON THIS CONTRACT WILL BE CONSIDERED CRITICAL. | $1K |
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