Marshall Space Flight Center Awarded Contracts - Machine Learning | Federal Compass

Marshall Space Flight Center Awarded Contracts - Machine Learning

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80MSFC18C0007 - NASA/MSFC IS SEEKING IMPLEMENTATION OF TROPICAL CYCLONE INTENSITY ESTIMATION SERVICES AND WEB INTERFACE. THE PRIMARY GOAL OF THIS EFFORT IS TO: (A) DEVELOP REST SERVICES FOR INTENSITY ESTIMATION USING TROPICAL CYCLONE INTENSITY ESTIMATION DEVELOPED BY NASA/MSFC, (B) DEVELOP VISUAL INTERFACE (MAP) TO SHOW CURRENT WIND SPEED ESTIMATION, AND (C) DEVELOP OGC STANDARD SERVICES TO OBTAIN WIND SPEED INFORMATION. THESE DEVELOPMENTS WILL PROVIDE ACCURATE FORECASTS OF TROPICAL CYCLONE INTENSITIES TO NASA/MSFC'S OPERATIONAL PARTNERS.
Definitive Contract - 541715 Research and Development in the Physical, Engineering, and Life Sciences
Contractor
NEW RIGHTS GROUP, INC.
Contracting Agency/Office
National Aeronautics and Space Administration»Marshall Space Flight Center
Effective date
11/02/2017
Obligated Amount
$3M
NNM10AA22C - PHASE III SBIR: RADIALLY SEGMENTED LAUNCH VEHICLE OXYGEN / METHANE TECHNOLOGY MATURATION PROGRAM THE CONTRACTOR'S EFFORT DESCRIBED IN THE PROPOSAL INVOLVES FOUR MAJOR TASKS. THESE TASKS ARE: 1. CATALYTICALLY INITIATED COMBUSTOR DEVELOPMENT. THE CATALYTICALLY INITIATED COMBUSTOR (CIC) CONCEPT WAS CONCEIVED BY KT ENGINEERING UNDER AND INDEPENDENT RESEARCH AND DEVELOPMENT (IR&D) PROGRAM AND REFINED UNDER SBIR PHASE II CONTRACT F29601-02-C-0010 WITH AFRL AND NASA SBIR PHASE III CONTRACT NNM09AA33C. THE PROPOSED TASK I ACTIVITIES, WITHIN THIS NASA SBIR PHASE III PROGRAM, WILL CONTINUE TO RETIRE TECHNICAL RISK ASSOCIATED WITH CONCEPT AND RAISE THE NASA TRL. THE EFFORT WILL REFINE THE CIC DESIGN TO ADDITIONAL SEA LEVEL TESTING USING GASEOUS PROPELLANTS. THIS ADDITIONAL TESTING IS REQUIRED TO DEMONSTRATE CIC OPERATION UNDER HIGH FLOW, HIGH CHAMBER PRESSURE CONDITIONS INCLUDING THE USE OF ABLATIVE CHAMBERS IN CONJUNCTION WITH HIGHER MIXTURE RATIOS TO REDUCE RISK ASSOCIATED WITH THE USE OF THE CIC IN A REACTION CONTROL SYSTEM APPLICATION. 2. HIGHLY RELIABLE, ROCKET ENGINE INJECTOR FABRICATION. KT ENGINEERING INVESTIGATED THE USE OF INVESTMENT CASTING TO PRODUCE A NEAR-NET INJECTOR BODY FOR A LO2/LCH4 ROCKET ENGINE UNDER SBIR PHASE II CONTRACT F29601-02-C-0010 WITH AFRL. THE FOCUS OF THIS EFFORT WAS TO SIGNIFICANTLY LOWER RECURRING COST BY REDUCING MACHINING TIME AND RAW MATERIAL REQUIREMENTS. HOWEVER, THE AFRL EFFORT ALSO IDENTIFIED THE NEED FOR A STRUCTURED ENGINEERING INVESTIGATION TO IDENTIFY THE OPTIMAL METHODS FOR PRODUCING THE DISPOSABLE MOLDS, REMOVING THE CERAMIC CRES USED TO CREATE THE INTERNAL RING MANIFOLDS, AND NON-DESTRUCTIVE EVALUATION OF THE CONTRACT NNM09AA33C THROUGH THE DEVELOPMENT OF DESIGNS, TOOLS, MANUFACTURING PROCESSES, AND THE CASTING OF SIMPLIFIED INJECTOR PROCESS PATHFINDERS. THE RESULTS FROM THE NASA SBIR PHASE III CONTINUE TO INDICATE THAT AN INTEGRAL-FACE, CAST INJECTOR IS FEASIBLE. THE PROPOSED TASK 2 ACTIVITY IS THE NEXT LOGICAL STEP TO REDUCE RISK ASSOCIATED WITH THIS TECHNOLOGY BY DEMONSTRATING ITS UTILITY ON A MORE COMPLEX INJECTOR PROTOTYPE THAT MORE CLOSELY REPRESENTS THE SIZE, SHAPE, AND GEOMETRY OF A FLIGHT WEIGHT INJECTOR. 3. PRESSURIZATION SYSTEM DEMONSTRATION. THE RSVL USES AN INNOVATIVE, DISTRIBUTED PRESSURIZATION SYSTEM TO PROVIDE INERT GAS FOR PURGES, VALVE ACTUATION, AND TANK PRESSURIZATION DURING FLIGHT. THE APPROACH PROMISES TO BE MORE RELIABLE, LESS COSTLY, AND HIGHER PERFORMING THAN A CONVENTIONAL BLOW-DOWN PRESSURIZATION SYSTEM FOR A PRESSURE-FED VEHICLE. UNDER THROUGH RIGOROUS ENGINEERING MODELING AND LIMITED BENCH-TOP TESTING. THE NEXT LOGICAL STEP, TASK 3 OF THIS PROPOSAL, IS TO INCREASE THE RRL AND VALIDATE THE APPROACH THROUGH COMPONENT AND SYSTEM LEVEL DEVELOPMENT AT PRESSURES AND FLOW RATES CONSISTENT WITH THE REQUIREMENTS FOR THE RSLV. 4. ENGINE MODULE TESTING. EXPERIENCE HAS SHOWN THAT PROPULSION SYSTEMS COMPONENTS MUST ULTIMATELY BE INTEGRATED INTO A COMPLETE ENGINE SYSTEM AND RIGOROUSLY TESTED UNDER ALL ANTICIPATED SERVICE ENVIRONMENTS AND CONDITIONS. KT ENGINEERING HAS DEVELOPED AND DEMONSTRATED A NUMBER OF COMPONENT TECHNOLOGIES APPLICABLE TO THE RSLV PROPULSION SYSTEM. THE NEXT CRITICAL STEP IS TO DEMONSTRATE THESE TECHNOLOGIES INTEGRATED INTO AN OPERATIONAL ENGINE MODULE. KT ENGINEERING DEVELOPED THE DESIGN FOR A FLIGHT WEIGHT RSLV ENGINE MODULE UNDER SBIR PHASE III CONTRACT FA9453-08-C-0171 WITH AFRL. A PROTOTYPE ENGINE MODULE WAS PARTIALLY FABRICATED, INTEGRATED, AND TESTED BEFORE THE CONTRACT ENDED. UNDER TASK 4 OF THIS PROPOSAL, KT ENGINEERING WILL COMPLETE THE ENGINE MODULE, INTEGRATE THE UPDATED CATALYTIC IGNITER AND RCS THRUSTER DESIGNS, UPGRADE THE INJECTOR, PRESSURIZATION AND FEED SYSTEMS BASED ON LESSONS LEARNED, AND PERFORM TESTING OF THE ENGINE ON A MODULAR TEST.
Definitive Contract - 541330 Engineering Services
Contractor
KT ENGINEERING CORPORATION
Contracting Agency/Office
National Aeronautics and Space Administration»Marshall Space Flight Center
Effective date
05/19/2010
Obligated Amount
$1,000k

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