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Plasma Processes, LLC

$35M obligated·57 awards·2 agencies·7 NAICS
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Federal Contracts

Showing contracts 51–78 of 78 total. Sorted by action date, most recent first. Excludes $0 modifications.

DateAgencyPIIDNAICSDescriptionAmount
Oct 19, 2018Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7708541712IGF::OT::IGF 7708 PHASE II RESEARCH&DEVELOPMENT$499K
Aug 1, 2018National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER80NSSC18P2157541715NIOBIUM ALLOY (C-103) REACTION CONTROL SYSTEM (RCS) CHAMBERS HAVE BEEN USED ON NUMEROUS NASA PROGRAMS. HOWEVER AT ELEVATED TEMPERATURES, THE STRENGTH OF C-103 DECREASES SIGNIFICANTLY. HIGHER STRENGTH NIOBIUM ALLOYS HAVE BEEN DEVELOPED, BUT THESE ALLOYS LACK THE FORMABILITY OF C-103. RECENTLY, ADDITIVE MANUFACTURE (AM) OF NIOBIUM AND C-103 HAS BEEN DEMONSTRATED USING POWDER BED ELECTRON BEAM MELTING (EBM). A PRIMARY ADVANTAGE OF AM PROCESSING IS ITS ABILITY TO PRODUCE COMPLEX COMPONENTS TO NET SHAPE ALONG WITH THE INCORPORATION OF UNIQUE FEATURES. HOWEVER, EBM-AM PROCESSING OF NIOBIUM AND C-103 RESULTS IN ELONGATED, COLUMNAR GRAINS, WHICH REDUCE MECHANICAL PROPERTIES AS COMPARED TO A COLD WORKED MATERIAL. THEREFORE, THE POTENTIAL EXISTS TO DEVELOP AND FABRICATE A HIGHER STRENGTH NIOBIUM ALLOY BY TAKING ADVANTAGE OF THE NET-SHAPE FORMING CAPABILITY OF AM PROCESSING AND CIRCUMVENT THE LACK OF FORMABILITY OF SUCH HIGH STRENGTH ALLOYS. TO DEMONSTRATE THE FEASIBILITY OF EBM-AM PROCESSING HIGH STRENGTH NIOBIUM ALLOYS, A PARAMETERS-CHARACTERIZATION-PROPERTIES STUDY WILL BE CONDUCTED DURING PHASE I. DURING PHASE II, THE EBM-AM PROCESSING OF HIGH STRENGTH NIOBIUM ALLOYS WILL BE OPTIMIZED AND EXTENSIVE MATERIALS PROPERTIES TESTING WILL BE CONDUCTED. THE MOST PROMISING RESULTS WILL THEN BE USED TO PRODUCE A HIGH STRENGTH NIOBIUM ALLOY RCS CHAMBER.$125K
Jul 27, 2018National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER80NSSC18P1973541715THE DEVELOPMENT OF NEW HYPERSONIC CAPABILITIES IS IMPORTANT FOR THE UNITED STATES. IN THE NEAR-TERM, APPLICATION OF HYPERSONIC RESEARCH AND TECHNOLOGIES IS LIKELY TO BE ON ENHANCED DEFENSE SYSTEMS, BUT THIS COULD EVENTUALLY EXPAND TO INCLUDE IMPROVED ACCESS TO SPACE CAPABILITIES THAT WOULD DIRECTLY BENEFIT NASA. HYPERSONIC VEHICLE NOSE TIPS AND LEADING EDGES REQUIRE HIGH THERMAL SHOCK RESISTANCE COMBINED WITH BENDING STRENGTH AT A HIGH ANGLE OF ATTACK. DUE TO THEIR HIGH SPECIFIC MODULUS, HIGH FRACTURE TOUGHNESS AND THERMAL CONDUCTIVITY, GOOD THERMAL SHOCK RESISTANCE, AND EXCELLENT HIGH TEMPERATURE STRENGTH, ADVANCED CARBON/CARBON (C/C) COMPOSITES ARE CONSIDERED AS STRUCTURAL MATERIALS FOR ATMOSPHERIC ENTRY VEHICLES. C/C COMPOSITES HAVE DENSITIES IN THE RANGE 1.6 2.0 GM/CM3, MUCH LOWER THAN THOSE OF METALS AND CERAMICS, AND CAN SIGNIFICANTLY REDUCE HYPERSONIC VEHICLE COMPONENT WEIGHT. DURING REENTRY INTO THE ATMOSPHERE, A VEHICLE NOSE TIP AND LEADING EDGES CAN ENCOUNTER EXTREME CONVECTIVE AND RADIATIVE HEATING LOADS WITH THE VERY HIGH TEMPERATURES. UNFORTUNATELY, C/C COMPOSITES START TO RAPIDLY OXIDIZE ABOVE 700 WHICH RESTRICTS THEIR ENGINEERING APPLICATIONS IN AIR. MULTIPLE CONCEPTS OF OXIDATION RESISTANT COATINGS ARE CURRENTLY IN DEVELOPMENT FOR CARBON/CARBON COMPOSITE PROTECTION. MOST OF THE COATINGS ARE BASED ON SILICON CARBIDE IN COMBINATION WITH DIFFERENT REFRACTORY COMPOUNDS. THERMAL ANALYSES INDICATE THAT PORTIONS OF THE C/C HORIZONTAL CONTROL SURFACE AND NOSE LEADING EDGE OF THE MACH 10 VEHICLE WILL EXPERIENCE TEMPERATURES APPRMISSILES, MISSILE DEFENSE INTERCEPTORS.OACHING 2200 C, EXCEEDING EVEN THE SINGLE USE TEMPERATURE LIMIT OF THE SIC COATED CARBON/CARBON. AN OXIDATION PROTECTION SYSTEM IS PROPOSED FOR C/C HOT STRUCTURES THAT IS SIC FREE AND ABLE TO MEET THESE HIGH TEMPERATURE REQUIREMENTS BY USING OXYGEN BARRIER AND REFRACTORY OXIDE COATINGS.$125K
Jul 26, 2018Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7904541712::IGF::OT::IGF SBIR PHASE III$1.0M
May 15, 2018Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIVN6833518C0377541715IGF::OT::IGF$125K
Mar 29, 2018Department of DefensePAE STRATEGIC SYSTEMS PROGRAMSN0003016C0227541712BASE YEAR - PHASE II IGF::OT::IGF$250K
Mar 28, 2018Department of DefenseOFFICE OF NAVAL RESEARCHN0001415C0050541712IGF::CT::IGF DEVELOPMENT AND OPTIMIZATION OF HIGH TEMPERATURE MATERIALS AND MANUFACTURING TECHNIQUES.$200K
Nov 6, 2017Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014718C7227541715SBIR/STTR PHASE I RESEARCH&DEVELOPMENT - HIGHLY VECTORABLE, MULTI-PULSE ROCKET MOTOR NOZZLE TO ENHANCE MANEUVERABILITY OF ADVANCED INTERCEPTORS$100K
Nov 1, 2017Department of DefenseOFFICE OF NAVAL RESEARCHN0001415C0050541712IGF::CT::IGF DEVELOPMENT AND OPTIMIZATION OF HIGH TEMPERATURE MATERIALS AND MANUFACTURING TECHNIQUES.$233K
Sep 29, 2017National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTER80NSSC17C0092541712IGF::OT::IGF MOST IN SPACE CHEMICAL PROPULSION SYSTEMS USE HYDRAZINE AS THE PROPELLANT. HYDRAZINE IS HIGHLY TOXIC AND DANGEROUSLY UNSTABLE. TWO NON TOXIC MONOPROPELLANTS AF M315E AND LMP 103S HAVE BEEN DEVELOPED WITH HIGHER ENERGY DENSITY THAN HYDRAZINE. THESE NONTOXIC MONOPROPELLANTS HAVE SIGNIFICANTLY HIGHER COMBUSTION TEMPERATURES THAN HYDRAZINE. ON A NASA SBIR, SUITABLE COMBUSTION CHAMBERS WERE DEVELOPED FOR BOTH MONOPROPELLANTS AND SUCCESSFULLY TESTED FOR 1N AND 22N THRUST WITH THE NON TOXIC MONOPROPELLANT AF M315E. 1N SIZE, NON TOXIC, MONOPROPELLANT THRUSTERS HAVE NOW FLOWN ON COMMERCIAL SATELLITES WITH LMP 103S IN COMMERCIAL PARTNER ECAPS PROPULSION SYSTEM TRL9 AND OTHER THRUSTERS WILL FLY ON THE GREEN PROPELLANT INFUSION MISSION WITH AF M315E IN COMMERCIAL PARTNER AEROJET ROCKETDYNES PROPULSION SYSTEM TRL8 IN 2017. 22N SIZE THRUSTERS WERE TESTED IN THE SBIR PHASE I TRL5, AND INITIAL MANUFACTURING HAS STARTED ON THE 5N SIZE TRL4. THE CCRPP PROJECT IS NEEDED TO INCREASE THE TECHNOLOGY MATURITY INCREASE THE MRL ON 1N AND THE TRL MRL ON 5N AND 22N AND REDUCE RECURRING FABRICATION COSTS. MANUFACTURING IMPROVEMENTS ARE PROPOSED TO REDUCE MANUFACTURING FLOW TIME BY 50. THE PROPOSED COST REDUCTIONS AND MATURIZATION ARE NEEDED FOR THE SBIR TECHNOLOGY TO BE WIDELY COMMERCIALIZED.$415K
Sep 27, 2017Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014714C7031541712IGF::OT::IGF SBIR PHASE II RESEARCH&DEV - THERMAL ISOLATION OF SOLID ROCKET MOTOR EXIT CONE AND NOZZLE$496K
Sep 19, 2017Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7904541712::IGF::OT::IGF SBIR PHASE III$1.1M
Jun 27, 2017Department of DefenseFA9101 AEDC PKP PROCRMNT BRFA910115C0003541712IGF::OT::IGF PLASMA PROCESSES$225K
Jun 20, 2017Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014717C7319541712IGF::OT::IGF SBIR/STTR PHASE II R&D$997K
May 9, 2017National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX17CM04C541712IGF::OT::IGF ONE OF THE BIGGEST OBSTACLES PREVENTING THE WIDESPREAD IMPLEMENTATION OF SMALL SATELLITES IS THE PROCESS OF ACTUALLY GETTING THEM INTO SPACE. CURRENT METHODS INCLUDE HITCHING RIDES AS SECONDARY PAYLOADS. ALTHOUGH THIS INITIATIVE HAS PROVIDED SIGNIFICANT NEW LAUNCH CAPACITY FOR CUBESAT-CLASS SPACECRAFT, IT IS NOT WITHOUT ISSUES, MOST SPECIFICALLY LIMITED ORBITS AND ORBITAL LIFETIME. MANY MISSIONS NEED HIGHER ORBITS TO PERFORM THEIR MISSIONS; AND LOWER ORBITS ARE SUBJECT TO ATMOSPHERIC DRAG THAT MAY CAUSE PREMATURE REENTRY. SAFE AND AFFORDABLE MINIATURIZED PROPULSION CAN OVERCOME THESE LIMITING FACTORS AND IS A HIGH-VISIBILITY CAPABILITY SOUGHT BY THE CUBESAT COMMUNITY. EVEN BASIC CAPABILITIES TO PUSH IN ONE DIRECTION WILL ALLOW NANOSATS TO REMAIN IN ORBIT LONGER, OR ALLOW A SATELLITE PLACED INTO LOW-EARTH ORBIT TO PROPEL ITSELF TO A HIGHER OR MORE CIRCULAR ORBIT. IN PHASE I, PLASMA PROCESSES DESIGNED, FABRICATED AND DELIVERED TO NASA A MINIATURIZED PROPULSION SYSTEM COMPATIBLE WITH NON-TOXIC HAN- AND ADN-BASED GREEN MONOPROPELLANTS FOR SMALL SPACECRAFT PROPULSION. IN PHASE II, THE GREEN PROPELLANT THRUSTERS WILL BE TESTED WILL BOTH MONOPROPELLANTS FOR PRESSURE FED AND PUMP FED 1U PROPULSION MODULES. THE USE OF ADVANCED, NON-TOXIC PROPELLANTS WILL INCREASE MISSION CAPABILITIES INCLUDING LONGER MISSION DURATIONS, ADDITIONAL MANEUVERABILITY, INCREASED SCIENTIFIC PAYLOAD SPACE, AND SIMPLIFIED LAUNCH PROCESSING. ADDING PROPULSION WILL ALSO ENABLE DE-ORBITING OF THE SATELLITE AFTER COMPLETION OF THE MISSION.$750K
Apr 19, 2017National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX17CC13C541712IGF::OT::IGF NUCLEAR THERMAL PROPULSION (NTP) HAS BEEN IDENTIFIED AS A CRITICAL TECHNOLOGY NEEDED FOR HUMAN MISSIONS TO MARS AND BEYOND DUE TO ITS INCREASED SPECIFIC IMPULSE (ISP) AS COMPARED TO TRADITIONAL CHEMICAL PROPULSION SYSTEMS. RECENTLY, THE GAME CHANGING DEVELOPMENT (GCD) PROGRAM, WHICH IS A PARTNERSHIP BETWEEN NASA, DOE, AND INDUSTRY, WAS INITIATED TO EVALUATE THE FEASIBILITY OF A LOW ENRICHED URANIUM (LEU) NTP SYSTEM. A CRITICAL ASPECT OF NTP IS TO DEVELOP A ROBUST, STABLE FUEL. ONE OF THE FUEL CONFIGURATIONS CURRENTLY BEING EVALUATED IS A W-UO2 CERMET. FABRICATION OF FULL-SIZE CERMET ELEMENTS (>20?) HAS PROVEN TO BE DIFFICULT. AS A RESULT, THE USE OF CERMET SEGMENTS TO PRODUCE A FULL-SIZE FUEL ELEMENT IS OF INTEREST. HOWEVER, TECHNIQUES FOR JOINING THE SEGMENTS ARE NEEDED. DURING PHASE I, DIFFUSION BONDING TECHNIQUES WERE DEVELOPED FOR PRODUCING FUEL ELEMENTS FROM CERMET SEGMENTS. MICROSCOPIC EXAMINATION AND PRELIMINARY PROPERTIES TESTING SHOWED EXCELLENT JOINTS WERE FORMED. FOR EXAMPLE, QUANTITATIVE TENSILE TESTING OF W SAMPLES PRODUCED AT 1500C HIP WITH A NB INTERFACIAL COATING SHOWED THE FAILURES WERE IN THE BULK W AND NOT AT THE NB-W INTERFACES. THEREFORE, THE STRENGTH OF THE JOINTS WERE GREATER THAN THE STRENGTH OF THE BULK W MATERIAL. USING THE MOST PROMISING FABRICATION METHODS, A 6.3' LONG SIMULATED CERMET FUEL ELEMENT COMPRISED OF TWENTY-FIVE 0.25' THICK SEGMENTS WAS PRODUCED TO DEMONSTRATE PROOF-OF-CONCEPT. DURING THE PHASE II INVESTIGATION, THE HIP DIFFUSION BONDING PROCESS WILL BE OPTIMIZED FOR MAKING W CERMET BASED FUEL ELEMENTS. THIS WILL BE ACCOMPLISHED BY PERFORMING A PROCESS PARAMETER-CHARACTERIZATION-PROPERTIES STUDY. THE OPTIMIZED FABRICATION METHODS WILL THEN BE USED TO MAKE PROTOTYPE FUEL ELEMENTS WITH W CLADDINGS AND SUBSCALE FUEL ELEMENTS FOR DELIVERY TO NASA FOR HOT HYDROGEN TESTING$750K
Jan 31, 2017National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTERNNM16AB62P5417121N IRIDIUM/RHENIUM COMBUSTION CHAMBER 0.1N IRIDIUM/RHENIUM THRUSTER 0.1 N THRUSTER HEATER/THERMAL STANDOFF TECHNICAL$90K
Jan 30, 2017Department of DefenseOFFICE OF NAVAL RESEARCHN0001415C0050541712IGF::CT::IGF DEVELOPMENT AND OPTIMIZATION OF HIGH TEMPERATURE MATERIALS AND MANUFACTURING TECHNIQUES.$228K
Sep 30, 2016Department of DefensePAE STRATEGIC SYSTEMS PROGRAMSN0003016C0227541712BASE YEAR - PHASE II IGF::OT::IGF$500K
Jul 13, 2016Department of DefenseOFFICE OF NAVAL RESEARCHN0001416P1035541712SBIRSOL2016.1 IGF::CT::IGF$80K
Jul 13, 2016Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7904541712::IGF::OT::IGF SBIR PHASE III$4.7M
Jun 8, 2016National Aeronautics and Space AdministrationNASA MARSHALL SPACE FLIGHT CENTERNNM16AB62P5417121N IRIDIUM/RHENIUM COMBUSTION CHAMBER 0.1N IRIDIUM/RHENIUM THRUSTER 0.1 N THRUSTER HEATER/THERMAL STANDOFF TECHNICAL$55K
Jun 8, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CM11C541712IGF::OT::IGF THE ORION LAUNCH ABORT SYSTEM (LAS) UTILIZES ATTITUDE CONTROL MOTORS (ACM) WITH ADVANCED CERAMIC COMPOSITE COMPONENTS THAT FUNCTION AS A VALVE CONTROL SYSTEM TO ALLOW FOR SAFE MANEUVERABILITY AWAY FROM DANGER. THIS SYSTEM IS MADE STEERABLE DUE TO THE VALVE CONTROLLED THRUSTERS WHICH UTILIZE ADVANCED CERAMIC PINTLES MADE OF 4D C/C-SIC THAT ARE ATTACHED TO METALLIC STRUCTURES AND ACTUATED. DURING THE PHASE I EFFORT, AN INNOVATIVE TECHNIQUE TO JOIN METALLICS WITH THE ADVANCED CERAMIC COMPOSITES WAS DEMONSTRATED. DETAILED CHARACTERIZATION CONFIRMED THE DEPOSITED METAL (INCONEL 625) PRODUCED DURING THIS INVESTIGATION HAD GOOD ADHERENCE TO CC/ SIC PINTLES AND NO INTERFACIAL REACTIONS OCCURRED DURING DEPOSITION OR ELEVATED TEMPERATURE EXPOSURE. IN PHASE II, THE JOINING INTERFACE WILL BE OPTIMIZED AND PINTLE ASSEMBLES WILL BE PRODUCED FOR HOT FIRE TESTING WITH ORBITAL ATK. ADDITIONAL CMC MATERIALS AND COMPONENTS WILL ALSO BE DEVELOPED.$750K
Jun 7, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CM30P541712IGF::OT::IGF ONE OF THE BIGGEST OBSTACLES PREVENTING THE WIDESPREAD IMPLEMENTATION OF SMALL SATELLITES IS THE PROCESS OF ACTUALLY GETTING THEM INTO SPACE. CURRENT METHODS INCLUDE HITCHING RIDES AS SECONDARY PAYLOADS. ALTHOUGH THIS INITIATIVE HAS PROVIDED SIGNIFICANT NEW LAUNCH CAPACITY FOR CUBESAT-CLASS SPACECRAFT, IT IS NOT WITHOUT ISSUES, MOST SPECIFICALLY LIMITED ORBITS AND ORBITAL LIFETIME. MANY MISSIONS NEED HIGHER ORBITS TO PERFORM THEIR MISSIONS; AND LOWER ORBITS ARE SUBJECT TO ATMOSPHERIC DRAG THAT MAY CAUSE PREMATURE REENTRY. SAFE AND AFFORDABLE MINIATURIZED PROPULSION CAN OVERCOME THESE LIMITING FACTORS AND IS A HIGH-VISIBILITY CAPABILITY SOUGHT BY THE CUBESAT COMMUNITY. EVEN BASIC CAPABILITIES TO PUSH IN ONE DIRECTION WILL ALLOW NANOSATS TO REMAIN IN ORBIT LONGER, OR ALLOW A SATELLITE PLACED INTO LOW-EARTH ORBIT TO NUDGE ITSELF TO A HIGHER GEOSTATIONARY ORBIT. IN SUPPORT OF THIS TECHNOLOGICAL NEED, PLASMA PROCESSES WILL DESIGN, FABRICATE AND DEMONSTRATE COMBUSTION OF A MINIATURIZED PROPULSION SYSTEM COMPATIBLE WITH NON-TOXIC HAN- AND ADN-BASED GREEN MONOPROPELLANTS FOR SMALL SPACECRAFT PROPULSION. THE USE OF ADVANCED, NON-TOXIC PROPELLANTS CAN INCREASE MISSION CAPABILITIES INCLUDING LONGER MISSION DURATIONS, ADDITIONAL MANEUVERABILITY, INCREASED SCIENTIFIC PAYLOAD SPACE, AND SIMPLIFIED LAUNCH PROCESSING. ADDING PROPULSION WILL ALSO ENABLE DE-ORBITING OF THE SATELLITE AFTER COMPLETION OF THE MISSION.$125K
May 31, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CC84P541712IGF::OT::IGF NUCLEAR THERMAL PROPULSION (NTP) HAS BEEN IDENTIFIED AS A CRITICAL TECHNOLOGY NEEDED FOR HUMAN MISSIONS TO MARS DUE TO ITS INCREASED SPECIFIC IMPULSE (ISP) AS COMPARED TO TRADITIONAL CHEMICAL PROPULSION SYSTEMS. A CRITICAL ASPECT OF THE PROGRAM IS TO DEVELOP A ROBUST, STABLE NUCLEAR FUEL. ONE OF THE NUCLEAR FUEL CONFIGURATIONS CURRENTLY BEING EVALUATED IS A CERMET-BASED MATERIAL COMPRISED OF URANIUM DIOXIDE (UO2) PARTICLES ENCASED IN A TUNGSTEN MATRIX (W). RECENTLY, HOT ISOSTATIC PRESSURE (HIP) AND SPARK PLASMA SINTERING (SPS) PROCESSING TECHNIQUES HAVE BEEN EVALUATED FOR PRODUCING W CERMET-BASED FUEL ELEMENTS FROM POWDER FEEDSTOCKS. ALTHOUGH BOTH TECHNIQUES HAVE BEEN USED SUCCESSFULLY TO PRODUCE W CERMET FUEL SEGMENTS, THE FABRICATION OF FULL-SIZE W CERMET ELEMENTS (>20) HAS PROVEN TO BE DIFFICULT. AS A RESULT, THE USE OF W CERMET SEGMENTS TO PRODUCE A FULL-SIZE W CERMET FUEL ELEMENT IS OF INTEREST. HOWEVER, TECHNIQUES FOR JOINING THE SEGMENTS ARE NEEDED THAT WILL NOT LOWER THE USE TEMPERATURE, DAMAGE THE UO2 PARTICLES, OR COMPROMISE THE NUCLEAR PERFORMANCE OF THE FUEL. FOR THESE REASONS, JOINING OF THE SEGMENTS USING BRAZE OR WELD TECHNIQUES IS NOT DESIRED. THEREFORE, DIFFUSION BONDING TECHNIQUES WILL BE DEVELOPED DURING THIS INVESTIGATION FOR PRODUCING FULL-SIZE NUCLEAR FUEL RODS FROM W CERMET SEGMENTS. TO PROMOTE DIFFUSION DURING SOLID STATE BONDING, DIFFERENT REFRACTORY METAL INTERFACIAL COATINGS WILL BE EVALUATED.$125K
May 24, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CL37P541712IGF::OT::IGF THIS EFFORT INVOLVES THE COATING OF TEST SPECIMENS THAT SHALL BE EVALUATED AND CHARACTERIZED USING ARC HEATER TESTING METHODS. THE TEST SPECIMENS SHALL BE REPRESENTATIVE OF HYPERSONIC VEHICLE SHARP LEADING EDGES. THE TEST SPECIMENS SHALL BE LIGHTWEIGHT C/C (CARBON/CARBON) AND COATED WITH A MULTI-LAYER COATING SYSTEM. THE MULTI-LAYER COATING SHALL CONSIST OF A THIN LAYER OF METAL WITH A RARE EARTH OXIDE COATING DEFINING THE OUTERMOST LAYER, WITH POTENTIAL FOR AN ADDITIONAL EMISSIVITY COATING IN THE OUTERMOST LAYER.$100K
May 6, 2016Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014716C7708541712IGF::OT::IGF 7708 PHASE II RESEARCH&DEVELOPMENT$1000K
Mar 30, 2016Department of DefenseFA9101 AEDC PKP PROCRMNT BRFA910115C0003541712IGF::OT::IGF PLASMA PROCESSES$366K

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