Celsius Holdings, Inc.

AWARD OF CONTRACT FOR ALL MATERIAL AND SERVICES TO SUPPORT SYSTEM DEVELOPMENT AND DEMONSTRATION PHASE THROUGH PRELIMINARY DESIGN REVIEW FOR THE THREE CAPABILITIES (DISMOUNTED, MOUNTED, AND FIXED SITE) OF THE JOINT COUNTER RADIO CONTROLLED IMPROVISED EXPLOSIVE DEVICE (RCIED) ELECTRONIC WARFARE (JCREW) 3.3 SYSTEM OF SYSTEMS 71 DEGREES CELSIUS AMBIENT TEMPERATURE.

LIFE CYCLE SUSTAINMENT & FIELDING OF AN/SPS-77 (VARIANTS) RADARS, USMC AN/TPS-80 G/ATOR, CELSIUS TECH RADAR & CRYPTRONIC SITE 200 FIRE CONTROL RADAR AND OTHER SAAB SENSOR SYSTEMS

IGF::OT::IGF MASS SPECTROMETER FOR PLANETARY EXPLORATION (MASPEX) TECHNOLOGY DEVELOPMENT 5 MULTI-BOUNCE TIME-OF-FLIGHT (MBTOF) SENSOR DEVELOPMENT 5.1 FLIGHT SOURCE DESIGN DEVELOPMENT THE CONTRACTOR SHALL IMPROVE UPON THE EXISTING ION STORAGE SOURCE, MOVING TOWARDS A FLIGHT-LIKE CONFIGURATION. MODIFICATIONS WILL BE MADE TO IMPROVE TIME FOCUSING AND TRANSMISSION OF THE ION SOURCE. TO IMPROVE TRANSMISSION, ION STORAGE WILL BE OPTIMIZED FOR LOWER EXTRACTION FREQUENCIES, (1-2 KHZ FROM ITS CURRENT 5 KHZ DESIGN). TO IMPROVE TIME FOCUSING, SOURCE CAPACITANCE WILL BE REDUCED AND ELECTRODE SHAPE AND POSITIONING WILL BE OPTIMIZED FOR SHARPER TIME FOCUSING. THE SOURCE SHALL BE MODIFIED TO INTERFACE DIRECTLY WITH THE GAS INLET SYSTEM (GIS), AND TO PREVENT POTENTIAL CONTAMINATION AND MEMORY EFFECTS. SOURCE HEATERS WILL BE FITTED AND SPECIAL INERT COATINGS ON THE SOURCE ELECTRODES, TO REDUCE BREAKDOWN OF LABILE COMPOUNDS ON THE SURFACES, SHALL BE TESTED. 5.1.1 ION OPTICAL SIMULATION AND OPTIMIZATION ION OPTICAL SIMULATIONS SHALL BE CARRIED OUT USING IN-HOUSE DEVELOPED SIMPLEX OPTIMIZERS TO IMPROVE THE TIME FOCUSING CHARACTERISTICS OF THE ION SOURCE AS WELL AS ION TRANSMISSION. THESE SIMULATIONS SHALL INCLUDE GRID SCATTERING EFFECTS, REALISTIC PULSER RISE-TIMES AND SPACE-CHARGE LIMITING EFFECTS. 5.1.2 REDUCTION OF THE ION SOURCE CAPACITANCE THE CONTRACTOR SHALL STUDY WAYS OF REDUCING INTERNAL AND STRAY CAPACITANCE OF THE PULSING ELEMENTS. THE REDUCED CAPACITANCE WILL IMPROVE THE EXTRACTION RISE-TIME AND REDUCE THE PULSER POWER REQUIREMENT. THESE CHANGES SHALL BE INCORPORATED INTO THE NEW SOURCE DESIGN. THE CAPACITANCE OF THE NEW SOURCE SHALL BE TESTED WITH A VECTOR IMPEDANCE METER AT THE APPROPRIATE FREQUENCY EXPECTED DURING ION EXTRACTION. 5.1.3 ION SOURCE GRID STUDY TO IMPROVE ION STORAGE THE CONTRACTOR SHALL ACCURATELY DEFINE GRID TRANSMISSIONS IN ORDER TO REDUCE FIELD PENETRATION FROM STATIC HIGH VOLTAGE ELECTRODES NEAR THE ION SOURCE VOLUME. A SIMULATION STUDY WILL BE FOLLOWED BY EXPERIMENTAL LABORATORY TESTS OF THE EFFECTS OF VARIOUS GRID TRANSMISSIONS ON THE ION STORAGE, BEAM TRANSMISSION AND TIME FOCUSING. 5.1.4 SOURCE HEATERS TO REDUCE COMPOUND MEMORY EFFECTS, SOURCE HEATERS SHALL BE DEVELOPED AND INTEGRATED, CAPABLE OF ACHIEVING AT LEAST 150 DEGREE CELSIUS SOURCE TEMPERATURES. THIS TASK WILL USE RESISTIVE METAL PATTERNED ON A CERAMIC SUBSTRATE. THE CERAMIC SUBSTRATE WILL HAVE SUFFICIENT GALVANIC ISOLATION TO ALLOW THE PATTERNED HEATER TO OPERATE NEAR EARTH GROUND WHILE THE ELECTRODES ARE PULSED TO HIGH VOLTAGE. 5.1.5 ION SOURCE COATINGS EPNER TECHNOLOGIES SHALL BE COMMISSIONED TO COAT THE ION SOURCE ELECTRODES AND GRIDS WITH EPNERAS PROPRIETARY LASER GOLD COATING TO REDUCE PATCH CHARGING AND TO REDUCE THE POTENTIAL FOR TARGET COMPOUND REACTIONS OCCURRING ON THE SURFACES OF THE BARE TITANIUM. 5.2 MBTOF VIBRATION TEST. THE CONTRACTOR SHALL INTEND TO INCREASE THE TECHNICAL READINESS LEVEL (TRL) FOR THE MBTOF-III MASS SPECTROMETER AS A COMPLETE INSTRUMENT, INCLUDING THE STRONGBACK AND ITS MOUNT, THE REFLECTRONS, THE SOURCE, AND THE RUGGEDIZED STRAIN GAGE ELECTRONICS (SGE) DETECTOR. 5.2.1 DETECTOR MOUNT DEVELOPMENT A DETECTOR MOUNT SUITABLE FOR FLIGHT SHALL BE DEVELOPED FOR THE MBTOF-III AND THE RUGGEDIZED DETECTOR. THIS MOUNT WILL BE OPTIMIZED FOR STIFFNESS AND MASS EFFICIENCY USING FINITE ELEMENT ANALYSIS IN ORDER TO REDUCE STRESS LEVELS ON THE REFLECTRON ASSEMBLY AND THE DETECTOR. IT WILL ALSO BE DESIGNED TO MAINTAIN ALIGNMENT DURING VIBRATION TESTING.

CRYOGENIC ENCAPSULATING LAUNCH SHROUD AND INSULATED UPPER STAGE (CELSIUS) TO ENABLE EFFICIENT AND SAFE TRANSPORTATION INTO AND THROUGH SPACE

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.

CLIN 0001: LONG LENGTH 8" H1944-8 PLY FLOATER HOSE - QTY: 2 EACH EACH CONSISTS OF: DIMENSIONS: 8" X 600'. ELECTRICALLY: DISCONTINUOUS. ANSI 150 WN RF. TEXTILE LONG LENGTH HOSE. SOFT WALL. INSIDE DIA. 205 MM, OUTSIDE DIA. 233 MM, WEIGHT IN AIR EMPTY 12.3KG/M, WEIGHT IN AIR FULL OF WATER 46.1KG/M, WORKING PRESSURE OF 250 PSI OR HIGHER, TEST PRESSURE 450 PSI, BURST PRESSURE 1200 PSI, AROMATIC RESISTANCE UP TO 50%, FLUID TEMPERATURE RANGE -29 TO +92 DEGREES CELSIUS, FLOW VELOCITY UP TO 21 M/S. EACH ASSEMBLY INCLUDES ALL NECESSARY FITTINGS, 8" TOWING SLIT CLAMPS, 8" COUPLINGS, BALL VALVES, 8" TOWING CLAMPS, 8" SEAL O-RINGS, 8" SEAL BACK-UP RINGS, 8" PIG CATCHER ASSEMBLY, 8" CAMLOCK ADAPTORS W/VALVES AND 8" TOWING CLAMP HANDLING HARNESS. USED TO UNLOAD FUEL FROM TANKER SHIP. HOSES ARE ATTACHED TO THE PUMP MANIFOLD ON THE TANKER AND CONNECTED TO FIXED 2 X 10" RECEIVING PIPELINES ON THE PIER. TANKER THEN PUMPS FUEL ASHORE AT A RATE OF 4,200 GPM TO THE BULK STORAGE TANKS WHILE THE HOSES FLOAT ON THE WATER. AT UNLOAD COMPLETION, HOSES ARE PIGGED AND RETRIEVED ONTO THE REELS. THIS CLIN SHOULD INCLUDE SHIPPING AND HANDLING TO DESTINATION ROYAL ARCTIC LINE, DAP AALBORG, DENMARK. (DELIVERY EXPECTED 24 WKS AFTER RECEIPT OF ORDER). CLIN 0002: LONG LENGTH 8" H1944-8 PLY FLOATER HOSE - QTY: 2 EACH EACH CONSISTS OF: DIMENSIONS: 8" X 15'. ELECTRICALLY: DISCONTINUOUS. ANSI 150 WN RF. TEXTILE LONG LENGTH HOSE. SOFT WALL. INSIDE DIA. 205 MM, OUTSIDE DIA. 233 MM, WEIGHT IN AIR EMPTY 12.3KG/M, WEIGHT IN AIR FULL OF WATER 46.1KG/M, WORKING PRESSURE OF 250 PSI OR HIGHER, TEST PRESSURE 450 PSI, BURST PRESSURE 1200 PSI, AROMATIC RESISTANCE UP TO 50%, FLUID TEMPERATURE RANGE -29 TO +92 DEGREES CELSIUS, FLOW VELOCITY UP TO 21 M/S. EACH ASSEMBLY INCLUDES ALL NECESSARY FITTINGS, 8" TOWING SLIT CLAMPS, 8" COUPLINGS, BALL VALVES, 8" TOWING CLAMPS, 8" SEAL O-RINGS, 8" SEAL BACK-UP RINGS, 8" CAMLOCK ADAPTORS WITH VALVES AND 8" TOWING CLAMP HANDLING HARNESS. USED TO UNLOAD FUEL FROM TANKER SHIP. HOSES ARE ATTACHED TO THE PUMP MANIFOLD ON THE TANKER AND CONNECTED TO FIXED 2 X 10" RECEIVING PIPELINES ON THE PIER. TANKER THEN PUMP FUEL ASHORE AT A RATE OF 4,200 GPM TO THE BULK STORAGE TANKS WHILE THE HOSES FLOAT ON THE WATER. AT UNLOAD COMPLETION, HOSES ARE PIGGED AND RETRIEVED ONTO THE REELS. THIS CLIN SHOULD INCLUDE SHIPPING AND HANDLING TO DESTINATION ROYAL ARCTIC LINE, DAP AALBORG, DENMARK.(DELIVERY EXPECTED 24 WKS AFTER RECEIPT OF ORDER). CLIN 0003: SERIES "628" HOSE REEL&LEVEL WINDS - QTY: 1 EACH THIS CLIN CONSISTS OF TWO (2) EACH SERIES "628" HOSE REELS AND TWO (2) EACH SERIES "628" LEVEL WINDS. THE HOSE REEL REQUIRES SPOOLING TO CONTROL THE LAY OF THE HOSE ON AND OFF THE REEL DRUM. SPOOLING UNIT DOESN'T HAVE TO BE INTEGRATED. A 3-PHASE, 60 HZ HYDRAULIC POWER UNIT (HPU) IS NEEDED AND COULD BE INTEGRATED ONTO REEL, ONE HPU PER REEL. ALL FITMENT IN ACCORDANCE WITH HOSES IN CLIN 0001 AND 0002. EQUIPMENT MUST BE 60 HERTZ 120/208 VOLT. THIS CLIN SHOULD INCLUDE SHIPPING AND HANDLING TO DESTINATION ROYAL ARCTIC LINE, DAP AALBORG, DENMARK. (DELIVERY EXPECTED 24 WKS AFTER RECEIPT OF ORDER).

2800 C (CELSIUS) GRAPHITIZATION FURNACE

FUTURE SPACE EXPLORATION MISSIONS PRESENT SIGNIFICANT NEW CHALLENGES TO CREW HEALTH CARE CAPABILITIES, PARTICULARLY IN THE EFFICIENT UTILIZATION OF ON-BOARD OXYGEN RESOURCES. THE INTERNATIONAL SPACE STATION AND FUTURE EXPLORATION VEHICLES REQUIRE A LIGHT WEIGHT, COMPACT, PORTABLE OXYGEN CONCENTRATOR TECHNOLOGY (OCT) THAT CAN PROVIDE MEDICAL GRADE OXYGEN FROM THE AMBIENT CABIN AIR. CURRENT OCTS ARE HEAVY, BULKY, HAVE A NARROW OPERATING TEMPERATURE RANGE (AMBIENT TO 40 DEGREE CELSIUS), AND REQUIRE 15 TO 30 MINUTES START-UP TIME TO REACH THEIR FULL OPERATING CAPACITY. LYNNTECH'S PROPOSED ELECTROCHEMICAL OCT SOLVES THESE ISSUES BY OPERATING THE OCT WITH A CATHODE-AIR VAPOR FEED, UNLIKE CONVENTIONAL ELECTROCHEMICAL OCTS WHICH REQUIRE A LIQUID WATER FEED. THIS IS POSSIBLE DUE TO THE USE OF IN-HOUSE DEVELOPED PROPRIETARY NANOCOMPOSITE PROTON EXCHANGE MEMBRANE AND CATALYST TECHNOLOGIES. CATHODE-AIR VAPOR FEED OPERATION ELIMINATES THE NEED FOR A BULKY ON-BOARD WATER SUPPLY, SIGNIFICANTLY REDUCES THE COMPLEXITY OF THE BALANCE-OF-PLANT, AND GREATLY INCREASES THE SYSTEM EFFICIENCY. OCT WILL BE A QUARTER THE SIZE AND WEIGHT OF CONVENTIONAL OCTS, BE CAPABLE OF INSTANT START-UP, AND HAVE A WIDE OPERATING TEMPERATURE RANGE. LYNNTECH WILL DEVELOP A PHASE II PROTOTYPE THAT IS CAPABLE OF DELIVERING 4 SLPM OF 60% OXYGEN AND DELIVER IT TO NASA FOR FURTHER TESTING.

IGF::OT::IGF UNDER THIS EFFORT, BOEING WILL TEAM WITH THE NANOFABRICATION GROUP AT THE CALIFORNIA INSTITUTE OF TECHNOLOGY TO PERFORM THE FOLLOWING EFFORTS RELATIVE TO RESEARCH AND DEVELOPMENT FIELD EMISSION VACUUM ELECTRONIC DEVICES FOR OPERATION ABOVE 500 DEGREES CELSIUS. (1) DEMONSTRATE NANOTRIDE DEVICES BASED ON FIELD EMISSION VACUUM (FEV) ELECTRONICS TECHNOLOGY; (2) DESIGN AND FABRICATE SMALL INTEGRATED CIRCUIT (OSCILLATOR FOR FREQUENCIES CORRESPONDING TO S-BAND, 2GHZ); (3) VERIFY THE OPERATION OF DEVICES AND OSCILLATOR CIRCUIT AT 500 C IN VACUUM, FOR OVER 1,500 HOURS (60 DAYS). MOST SEMICONDUCTOR DEVICES OPERATE UP TO 250 C. RECENT ADVANCES IN CARBIDE AND NITRIDE SEMICONDUCTORS HOLD PROMISE FOR HIGHER TEMPERATURES, YET ARE ASSOCIATED WITH HIGH R&D COSTS. THERE IS A NEED FOR TECHNOLOGY WITH THE SIMPLICITY OF VACUUM TUBES AND WITH MICRON SIZES. THIS CONTRACT IS FOR THE DEVELOPMENT AND FABRICATION OF FIELD EMISSION VACUUM (FEV) DEVICES AND AN OSCILLATOR CIRCUIT FOR 2 GHX (S-BAND). IMPLEMENTATION WILL BE COMPLIMENTED BY THEORETICAL/SIMULATION ANALYSIS OF THE PATH TO X-BAND. ADDITIONALLY, THE EFFORT WILL INCLUDE THE FOLLOWING (1) DEVELOPMENT OF A DEVICE MODEL FOR HSPICE CIRCUIT SIMULATIONS; AND (2) SIMULATION USING FIRST-PRINCIPLES MODELING TOOLS, OF METAL MIGRATION FOR TUNGSTEN AND DERIVATIVES AT HIGH TEMPERATURES.

SILICON CARBIDE (SIC) AND OTHER WIDE BAND-GAP SEMICONDUCTORS OFFER GREAT PROMISE OF HIGH POWER RATING, HIGH OPERATING TEMPERATURE, SIMPLE THERMAL MANAGEMENT, AND ULTRA-HIGH POWER DENSITY FOR BOTH SPACE AND COMMERCIAL POWER ELECTRONIC SYSTEMS. HOWEVER, THIS GREAT POTENTIAL IS SERIOUSLY LIMITED BY THE LACK OF RELIABLE HIGH TEMPERATURE DEVICE PACKAGING TECHNOLOGY. THE OBJECTIVE OF THIS PROPOSED RESEARCH IS TO DEVELOP A ULTRA-COMPACT, HYBRID POWER MODULE PACKAGING TECHNOLOGY BASED ON THE USE OF DOUBLE LEADFRAMES AND DIRECT LEADFRAME-TO-CHIP TRANSIENT LIQUID PHASE (TLP) BONDING THAT ALLOWS DEVICE OPERATION UP TO 450 DEGREES CELSIUS. THE UNIQUE ADVANTAGES OF THIS INNOVATIVE SOLUTION INCLUDE VERY HIGH CURRENT CARRYING CAPABILITY, LOW PACKAGE PARASITIC IMPEDANCE, LOW THERMO-MECHANICAL STRESS AT HIGH TEMPERATURES, DOUBLE-SIDE COOLING, AND MODULARITY FOR EASY SYSTEM-LEVEL INTEGRATION. THE NEW POWER MODULE WILL HAVE A VERY SMALL FORM FACTOR WITH 3-5X REDUCTION IN SIZE AND WEIGHT FROM THE PRIOR ART, AND CAPABLE OF OPERATING FROM 450C TO -125C