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Award ID | Description | Recipient | Total Value | Awarding Agency | Funding Agency | Set Aside | NAICS | PSC | Award Date | Start Date | End Date | |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| IGF::OT::IGF TASK TITLE: 8-FOOT HIGH TEMPERATURE TUNNEL (8 HTT) MIXER LINER AND MACH 5 HIGH DYNAMIC PRESSURE THERMAL ANALYSIS 1.0 INTRODUCTION/BACKGROUND:PLANNED FUTURE TESTING IN THE NASA LANGLEY 8 HTT REQUIRES OPERATION OF THE EXISTING FACILITY MIXER AND MACH 5 HIGH DYNAMIC PRESSURE (M5HIQ) NOZZLE AT TEMPERATURE LEVELS EXCEEDING THE DESIGN VALUE FOR THAT HARDWARE. THE 8 HTT MIXER IS THE LOW VELOCITY REGION IMMEDIATELY UPSTREAM OF THE M5HIQ NOZZLE. INSIDE THE FACILITY MIXER, DILUTION AIR AND HOT FLOW FROM THE FACILITY COMBUSTOR ARE MIXED TOGETHER TO FORM THE ENTRANCE FLOW TO THE M5HIQ NOZZLE. FOR A NOMINAL MACH 5 TEST, THE MIXED FLOW TEMPERATURE IS APPROXIMATELY 2150 RANKINE. THE FACILITY HAS CONDUCTED NUMEROUS TESTS AT THIS NOMINAL MACH 5 CONDITION AND IS CAPABLE OF DELIVERING STEADY OPERATIONAL CONDITIONS FOR PERIOD OF 100 SECONDS WITHOUT EXCEEDING HIGH TEMPERATURE INTERLOCKS INSTALLED AT KEY LOCATIONS ON THE MIXER LINER AND M5HIQ NOZZLE. FUTURE CUSTOMERS HAVE IDENTIFIED TEST REQUIREMENTS AT CONDITIONS SIMULATING FLIGHT AT MACH 5.5. THIS SIMULATION REQUIRES THAT BOTH THE MIXER LINER AND THE EXISTING MACH 5 NOZZLE BE OPERATED AT TEMPERATURES THAT EXCEED THE DESIGN VALUE. IT IS KNOWN THAT EXCEEDING THE DESIGN TEMPERATURE IS ACCEPTABLE AS LONG AS THE RUN TIME IS SHORTENED SO THAT RED-LINE TEMPERATURE LIMITS ARE NOT VIOLATED DURING A TEST RUN. HOWEVER, THE ALLOWABLE RUN DURATION IS NOT KNOWN. THE ALLOWABLE RUN TIME DURATION AT TEMPERATURES EXCEEDING THE NOMINAL DESIGN VALUE MUST BE KNOWN SO THAT FUTURE FACILITY USERS CAN DETERMINE HOW MANY RUNS ARE REQUIRED FOR THEM TO COMPLETE THEIR REQUIRED TEST MATRIX. 2.0SCOPE&OBJECTIVE(S):2.1THE SCOPE OF THIS TASK ORDER IS TO CONDUCT AN ANALYTICAL STUDY TO DETERMINE THE ALLOWABLE RUN TIME (SECONDS) FOR THE MIXER AND THE M5HIQ NOZZLE AT STAGNATION TEMPERATURE LEVELS EXCEEDING THE NOMINAL DESIGN LEVEL AT NOZZLE INLET STAGNATION PRESSURE LEVELS PROVIDED AS GOVERNMENT FURNISHED INFORMATION (GFI) UNDER THIS TASK ORDER. 2.2 THE OBJECTIVES OF THIS TASK ORDER ARE TO: 2.2.1 ANALYTICALLY DETERMINE THE ALLOWABLE RUN TIME FOR THE EXISTING 8HTT MIXER AND M5HIQ NOZZLE AT TWO CONDITIONS EXCEEDING THE NOMINAL DESIGN TEMPERATURE LEVEL. 2.2.2 IDENTIFY THE LIMITING FACTOR ON RUN TIME FOR EACH MACH CONDITION AND INVESTIGATE DESIGN MODIFICATIONS THAT WOULD EXTEND THE RUN TIME LIMITS. 3.0DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 MIXER LINER AND M5HIQ TRANSIENT THERMAL ANALYSIS: (DELIVERABLE ITEM 4.3) 3.1.1 THE CONTRACTOR SHALL CONSTRUCT A SINGLE TRANSIENT THERMAL MODEL OF THE MIXER AND M5HIQ NOZZLE. THE THERMAL MODEL SHALL BE CONSTRUCTED FROM MIXER LINER AND M5HIQ HARDWARE GEOMETRY AND MATERIAL INFORMATION FURNISHED BY THE GOVERNMENT (GFI 5.1). 3.1.2 THE CONTRACTOR SHALL UTILIZE THE TRANSIENT THERMAL MODEL DEVELOPED IN SOW TASK 3.1.1 TO CONDUCT TRANSIENT THERMAL ANALYSES AT TWO DIFFERENT CONDITIONS SPECIFIED BY THE NASA TECH POC. THE TWO DIFFERENT ANALYSIS CONDITIONS PROVIDED BY THE GOVERNMENT (GFI 5.2) WILL CONSIST OF THE MIXER STAGNATION PRESSURE, THE MIXER STAGNATION TEMPERATURE, AND THE TOTAL FLOW RATE THROUGH THE MIXER AND M5HIQ NOZZLE. THE CONDITIONS PROVIDED AS GFI 5.2 WILL BE REPRESENTATIVE OF FLIGHT SIMULATION AT MACH 5.3 AND MACH 5.5. THE TRANSIENT THERMAL ANALYSIS SHALL BE UTILIZED BY THE CONTRACTOR TO PREDICT THE TIME REQUIRED FOR THE MIXER AND / OR M5HIQ NOZZLE TO EXCEED RED-LINE TEMPERATURE LIMITS AT THE TWO FLIGHT SIMULATION CONDITIONS. 3.1.3 THE CONTRACTOR SHALL IDENTIFY THE AXIAL LOCATIONS IN THE MIXER / NOZZLE ASSEMBLY WHERE THE TEMPERATURE EXCEEDS MATERIAL LIMITS. APPROACHES TO MITIGATE THE LIMITING CONDITION SHALL BE IDENTIFIED AND PRESENTED AS PART OF THE FINAL PRESENTATION. 3.0 PLANNEDPRESENTATIONS/MEETINGS/TELECONS: THE CONTRACTOR SHALL PARTICIPATE IN AND/OR TRAVEL TO THE PR | ATK SPACE SYSTEMS LLC | $1,430,731 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Aug 13, 2015 | Aug 13, 2015 | Oct 12, 2016 | ||
| IGF::OT::IGF STATEMENT OF WORK. TASK: 8-FOOT HIGH TEMPERATURE TUNNEL MIXER LINER AND MACH 5 HIGH DYNAMIC PRESSURE THERMAL ANALYSIS. 1.0 INTRODUCTION/BACKGROUND: PLANNED FUTURE TESTING IN THE NASA LANGLEY 8 HTT REQUIRES OPERATION OF THE EXISTING FACILITY MIXER AND MACH 5 HIGH DYNAMIC PRESSURE (M5HIQ) NOZZLE AT TEMPERATURE LEVELS EXCEEDING THE DESIGN VALUE FOR THAT HARDWARE. THE 8 HTT MIXER IS THE LOW VELOCITY REGION IMMEDIATELY UPSTREAM OF THE M5HIQ NOZZLE. INSIDE THE FACILITY MIXER, DILUTION AIR AND HOT FLOW FROM THE FACILITY COMBUSTOR ARE MIXED TOGETHER TO FORM THE ENTRANCE FLOW TO THE M5HIQ NOZZLE. FOR A NOMINAL MACH 5 TEST, THE MIXED FLOW TEMPERATURE IS APPROXIMATELY 2150 RANKINE. THE FACILITY HAS CONDUCTED NUMEROUS TESTS AT THIS NOMINAL MACH 5 CONDITION AND IS CAPABLE OF DELIVERING STEADY OPERATIONAL CONDITIONS FOR PERIOD OF 100 SECONDS WITHOUT EXCEEDING HIGH TEMPERATURE INTERLOCKS INSTALLED AT KEY LOCATIONS ON THE MIXER LINER AND M5HIQ NOZZLE. FUTURE CUSTOMERS HAVE IDENTIFIED TEST REQUIREMENTS AT CONDITIONS SIMULATING FLIGHT AT MACH 5.5. THIS SIMULATION REQUIRES THAT BOTH THE MIXER LINER AND THE EXISTING MACH 5 NOZZLE BE OPERATED AT TEMPERATURES THAT EXCEED THE DESIGN VALUE. IT IS KNOWN THAT EXCEEDING THE DESIGN TEMPERATURE IS ACCEPTABLE AS LONG AS THE RUN TIME IS SHORTENED SO THAT RED-LINE TEMPERATURE LIMITS ARE NOT VIOLATED DURING A TEST RUN. HOWEVER, THE ALLOWABLE RUN DURATION IS NOT KNOWN. THE ALLOWABLE RUN TIME DURATION AT TEMPERATURES EXCEEDING THE NOMINAL DESIGN VALUE MUST BE KNOWN SO THAT FUTURE FACILITY USERS CAN DETERMINE HOW MANY RUNS ARE REQUIRED FOR THEM TO COMPLETE THEIR REQUIRED TEST MATRIX. 2.0 SCOPE&OBJECTIVE(S): 2.1 THE SCOPE OF THIS TASK ORDER IS TO CONDUCT AN ANALYTICAL STUDY TO DETERMINE THE ALLOWABLE RUN TIME (SECONDS) FOR THE MIXER AND THE M5HIQ NOZZLE AT STAGNATION TEMPERATURE LEVELS EXCEEDING THE NOMINAL DESIGN LEVEL AT NOZZLE INLET STAGNATION PRESSURE LEVELS PROVIDED AS GOVERNMENT FURNISHED INFORMATION (GFI) UNDER THIS TASK ORDER. 2.2 THE OBJECTIVES OF THIS TASK ORDER ARE TO: 2.2.1 ANALYTICALLY DETERMINE THE ALLOWABLE RUN TIME FOR THE EXISTING 8 HTT MIXER AND M5HIQ NOZZLE AT TWO CONDITIONS EXCEEDING THE NOMINAL DESIGN TEMPERATURE LEVEL. 2.2.2 IDENTIFY THE LIMITING FACTOR ON RUN TIME FOR EACH MACH CONDITION AND INVESTIGATE DESIGN MODIFICATIONS THAT WOULD EXTEND THE RUN TIME LIMITS. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 MIXER LINER AND M5HIQ TRANSIENT THERMAL ANALYSIS: (DELIVERABLE ITEM 4.3) 3.1.1 THE CONTRACTOR SHALL CONSTRUCT A SINGLE TRANSIENT THERMAL MODEL OF THE MIXER AND M5HIQ NOZZLE. THE THERMAL MODEL SHALL BE CONSTRUCTED FROM MIXER LINER AND M5HIQ HARDWARE GEOMETRY AND MATERIAL INFORMATION FURNISHED BY THE GOVERNMENT (GFI 5.1). 3.1.2 THE CONTRACTOR SHALL UTILIZE THE TRANSIENT THERMAL MODEL DEVELOPED IN SOW TASK 3.1.1 TO CONDUCT TRANSIENT THERMAL ANALYSES AT TWO DIFFERENT CONDITIONS SPECIFIED BY THE NASA TECH POC. THE TWO DIFFERENT ANALYSIS CONDITIONS PROVIDED BY THE GOVERNMENT (GFI 5.2) WILL CONSIST OF THE MIXER STAGNATION PRESSURE, THE MIXER STAGNATION TEMPERATURE, AND THE TOTAL FLOW RATE THROUGH THE MIXER AND M5HIQ NOZZLE. THE CONDITIONS PROVIDED AS GFI 5.2 WILL BE REPRESENTATIVE OF FLIGHT SIMULATION AT MACH 5.3 AND MACH 5.5. THE TRANSIENT THERMAL ANALYSIS SHALL BE UTILIZED BY THE CONTRACTOR TO PREDICT THE TIME REQUIRED FOR THE MIXER AND / OR M5HIQ NOZZLE TO EXCEED RED-LINE TEMPERATURE LIMITS AT THE TWO FLIGHT SIMULATION CONDITIONS. 3.1.3 THE CONTRACTOR SHALL IDENTIFY THE AXIAL LOCATIONS IN THE MIXER / NOZZLE ASSEMBLY WHERE THE TEMPERATURE EXCEEDS MATERIAL LIMITS. APPROACHES TO MITIGATE THE LIMITING CONDITION SHALL BE IDENTIFIED AND PRESENTED AS PART OF THE FINAL PRESENTATION. | ATK SPACE SYSTEMS LLC | $101,290 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Oct 20, 2014 | Oct 20, 2014 | Apr 30, 2015 | ||
| IGF::OT::IGF NEWPORT ANALYZING RADIO FREQUENCIES R&D EFFORT | ATK SPACE SYSTEMS LLC | $968,766 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE ARMY | — | 541330Engineering Services | AC61 | Jul 25, 2014 | Jul 25, 2014 | Sep 30, 2015 | ||
| IGF::OT::IGF DIAGPHRAGM TANK RENTAL BETWEEN 01/17/2014 AND 08/06/2014. | ATK SPACE SYSTEMS LLC | $5,200 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541330Engineering Services | W043LEASE OR RENTAL OF EQUIPMENT- PUMPS AND COMPRESSORS | Dec 19, 2013 | Dec 19, 2013 | Aug 6, 2014 | ||
| IGF::OT::IGF THE NASA AUTHORIZATION ACT OF 2010 (P.L. 111-267) AUTHORIZES THE NASA OFFICE OF THE CHIEF TECHNOLOGIST (OCT) TO DEVELOP TECHNOLOGIES IN SUPPORT OF SPACE EXPLORATION. TO THIS END, OCT HAS CREATED THE GAME CHANGING DEVELOPMENT (GCD) PROGRAM WITHIN THE SPACE TECHNOLOGY PROGRAM (STP). THE GCD PROGRAM PRIMARILY FOCUSES ON MATURATION OF KEY TECHNOLOGIES ACROSS THE MID-TECHNOLOGY READINESS LEVELS (TRL), NAMELY TRL 3-5. FUTURE NASA MISSIONS REQUIRE THE DEVELOPMENT OF ADVANCED THERMAL CONTROL TECHNOLOGIES. MORE SPECIFICALLY, NASA IS INTERESTED IN THE DEVELOPMENT OF VARIABLE HEAT REJECTION (VHR) TECHNOLOGIES APPLICABLE TO THESE EXPLORATION MISSIONS. THE NASA HUMAN SPACEFLIGHT STUDIES HAVE IDENTIFIED VHR THERMAL CONTROL SYSTEMS AS A KEY CAPABILITY REQUIRED FOR EXTENDING HUMAN PRESENCE THROUGHOUT THE SOLAR SYSTEM. IN ADDITION, THE NEED FOR THESE TECHNOLOGIES WAS CAPTURED WITHIN THE RELEVANT NASA SPACE TECHNOLOGY ROADMAP (TA-14, THERMAL MANAGEMENT SYSTEMS) AND INNOVATIVE COMPONENTS AND LOOP ARCHITECTURES WERE IDENTIFIED AS THE SECOND MOST IMPORTANT TECHNICAL CHALLENGE WITHIN THAT ROADMAP. FINALLY, THE VHR INITIATIVE RESPONDS TO THE TECHNOLOGIES IN THE NATIONAL RESEARCH COUNCIL S RECOMMENDATIONS TO THE NASA TECHNOLOGY ROADMAPS. THE SUBJECT PURCHASE ORDER IS THE RESULT OF A PROPOSAL SUBMITTED BY ATK SPACE SYSTEMS SELECTED FOR AWARD UNDER THE NASA RESEARCH ANNOUNCEMENT (NRA) NNL12A3001N ENTITLED GAME CHANGING OPPORTUNITIES IN TECHNOLOGY DEVELOPMENT (GCOTD) 2012 APPENDIX C, TECHNOLOGY DEVELOPMENT FOR VARIABLE HEAT REJECTION (VHR). THE NRA SOLICITATION SOUGHT PROPOSALS FOR THE STUDY OF ADVANCED VARIABLE HEAT REJECTION TECHNOLOGIES TO ADDRESS A DIFFICULT DESIGN CHALLENGE FACING FUTURE NASA EXPLORATION MISSIONS. THE VHR DEVELOPMENT EFFORT IS ANTICIPATED TO OCCUR IN FOUR PHASES. DURING EACH PHASE, THE TECHNOLOGY READINESS LEVEL (TRL) OF THE SELECTED TECHNOLOGIES WILL BE ADVANCED AND THE CULMINATION OF PHASE IV WILL RESULT IN TRL 5/6 HARDWARE. PHASE I, IS THE FORMULATION PHASE, AND WILL INCLUDE AN ANALYTICAL STUDY TO DEMONSTRATE THE FEASIBILITY AND VIABILITY OF THE PROPOSED TECHNOLOGY. ONLY PHASE I IS PRESENTLY APPROVED BY THE GCD PROGRAM MANAGEMENT AND WAS SOLICITED UNDER APPENDIX C. AT THE END OF THE FORMULATION PHASE, THE STUDY RESULTS WILL BE REVIEWED ALONG WITH PROGRAMMATIC CONSIDERATIONS TO DETERMINE WHETHER THE PROJECT WILL ENTER IMPLEMENTATION, PHASES II THROUGH IV. | ATK SPACE SYSTEMS LLC | $50,000 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR12SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; APPLIED RESEARCH | Mar 12, 2013 | Mar 12, 2013 | Jun 12, 2013 | ||
| RESEARCH AND DEVELOPMENT EFFORTS IN SUPPORT OF THE DARPA SEEME PROJECT. | ATK SPACE SYSTEMS LLC | $742,378 | DEPT OF THE ARMY | DEPT OF THE ARMY | — | 541712 | AC23NATIONAL DEFENSE R&D SERVICES; ATOMIC ENERGY DEFENSE ACTIVITIES; EXPERIMENTAL DEVELOPMENT | Feb 14, 2013 | Jan 31, 2013 | Apr 13, 2014 | ||
| NETWORK CENTRIC WEATHER SMALLSAT STUDY | ATK SPACE SYSTEMS LLC | $5,983,352 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | B544SPECIAL STUDIES/ANALYSIS- TECHNOLOGY | Dec 14, 2012 | Dec 14, 2012 | Dec 31, 2013 | ||
| IGF::OT::IGF OTHER FUNCTIONS - STATEMENT OF WORK (SOW) SMAAART TASK TITLE: AHSTF ENHANCED MIXING RESEARCH PROJECT 1.0 INTRODUCTION/BACKGROUND: THE HYPERSONIC AIRBREATHING PROPULSION BRANCH (HAPB) AT NASA LANGLEY RESEARCH CENTER (LARC) RECENTLY INITIATED THE AHSTF ENHANCED MIXING RESEARCH PROJECT WHICH SEEKS TO MEET FUTURE HYPERSONIC RESEARCH REQUIREMENTS. THE PURPOSE OF THIS PROJECT IS TO INVESTIGATE AND DEVELOP FLIGHT SIMULATION CAPABILITY AND IMPROVE THE ABILITY TO ASSESS FLOW QUALITY FOR HYPERSONIC RESEARCH. IMPROVED DIAGNOSTICS AND MEASUREMENT SYSTEMS ARE NEEDED TO ROUTINELY QUANTIFY THE FLOW PROPERTIES DELIVERED TO THE TEST ARTICLES. THIS PROJECT ALSO INCLUDES INVESTIGATING FUEL INJECTION AND MIXING FOR SCRAMJET ENGINES TO ENHANCE OUR UNDERSTANDING OF SCRAMJET FUEL INJECTION AND MIXING DEVICES IN A CONTROLLED TEST ENVIRONMENT TO EVALUATE INNOVATIVE CONCEPTS. SINCE THE SCRAMJET MIXING AND COMBUSTION PROCESSES ARE KNOWN TO HAVE THE GREATEST POTENTIAL FOR IMPROVING SCRAMJET ENGINE PERFORMANCE AND EFFICIENCY, THIS PROJECT SEEKS TO PROVIDE A MAJOR STEP TOWARDS DEVELOPING PRACTICAL PROPULSION SYSTEMS FOR AEROSPACE VEHICLES OPERATING IN THE HYPERSONIC SPEED REGIME. THE AHSTF ENHANCED MIXING RESEARCH PROJECT, SCHEDULED TO BE IMPLEMENTED IN FISCAL YEAR (FY) 13, INVOLVES THE RESEARCH, DEVELOPMENT, AND INSTALLATION OF TWO NEW FACILITY NOZZLES (I.E., MACH 3.5 AND MACH 2.2) TO DEMONSTRATE MACH 2.5 TO 4.0 FLIGHT SIMULATED CONDITIONS. 2.0 SCOPE AND OBJECTIVE(S): THE SCOPE OF THIS TASK ORDER IS TO RESEARCH, PROCURE, AND DEVELOP THE AHSTF WITH MAJOR HARDWARE COMPONENTS NECESSARY TO SUCCESSFULLY COMPLETE THE AHSTF ENHANCED MIXING PROJECT. THE OBJECTIVES OF THIS TASK ORDER ARE TO OBTAIN: 1) PROCURE FACILITY TEST HARDWARE. 2) TEST AND EVALUATE VARIOUS FUEL INJECTION AND MIXING DEVICES IN THE AHSTF. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTACTOR SHALL DESIGN, ANALYZE, AND FABRICATE THE FOLLOWING COMPONENT(S): 1) A MACH 3.5 FACILITY NOZZLE. 2) A MACH 2.2 FACILITY NOZZLE. 3) A RAKE TRAVERSE SYSTEM. 4) THREE (3) IN-STREAM RAKES FOR THE FACILITY NOZZLE EXIT. 5) THREE (3) IN-STREAM RAKES FOR THE MIXING TEST APPARATUS. 6) A GAS COMPOSITION MEASUREMENT SYSTEM. 7) FOUR (4) FACILITY NOZZLE JET STRETCHERS. NOTE: LARC WILL BE RESPONSIBLE FOR THE INSTALLATION AND INTEGRATION OF THIS HARDWARE INTO THE AHSFT. A CAD IMAGE OF THE AHSTF, WITH ITS MIXING TEST APPARATUS INSTALLED IN THE TEST CABIN IS SHOWN IN SOW 8.1. THE RAKE TRAVERSE SYSTEM AND IN-STREAM RAKES WILL BE USED TO SURVEY THE FLOW OVER A RANGE OF AXIAL LOCATIONS ALONG THE TEST CABIN FROM THE NOZZLE EXIT TO THE END OF THE MIXING REGION. GENERAL REQUIREMENTS: A) ALL HARDWARE SHALL INTEGRATE/INSTALL WITHIN THE AHSTF. B) ALL HARDWARE SHALL INCORPORATE DESIGN FEATURES THAT REDUCE MAINTENANCE TIME. DESIGN CHOICES THAT ALLOW DAY SHIFT CONFIGURATION CHANGES ARE PREFERRED AS LONG AS THEY DO NOT COMPROMISE THE FUNCTIONALITY OR DESIGN LIFE. C) ALL FLUID, ELECTRICAL, AND INSTRUMENTATION LINES SHALL INCORPORATE MATCHING CONNECTION TO THE ADJOINING FACILITY INTERFACE. D) ALL HARDWARE SHALL COMPLY WITH LANGLEY PROCEDURAL REQUIREMENT (LPR) 1710.15 ENTITLED WIND TUNNEL MODEL SYSTEMS CRITERIA (GFI 5.1). THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 MACH 3.5 AND MACH 2.2 FACILITY NOZZLES THE GOVERNMENT HAS DEVELOPED THE REQUIREMENTS FOR THE FACILITY NOZZLES WITH THE INTENT TO MINIMIZE HARDWARE DESIGN AND FABRICATION COSTS BY LIMITING THE MAXIMUM OPERATING TEMPERATURE TO LEVELS CONSISTENT WITH UN-COOLED HARDWARE. THE DESIGN SHALL TAKE ADVANTAGE OF MATERIALS AND THERMAL MANAGEMENT THAT PROVIDES THE BEST TRADE-OFF BETWEEN COST AND DIMENSIONAL TOLERANCE. 3.1.1 THE CONTRACTOR SHALL DESIGN, ANALYZE, AND DELIVER ENGINEERING DRAWINGS FOR A MACH 3.5 FACILITY NOZZLE AND A MACH 2.2 FACILITY NOZZLE WHICH DELIVER FLOW TO THE TEST CABIN/EXPERIMENT HARDWARE. A. EACH NOZZLE SHALL MATE WITH EX | ATK SPACE SYSTEMS LLC | $2,546,027 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 28, 2012 | Sep 28, 2012 | Nov 28, 2014 | ||
| IGF::OT::IGF STATEMENT OF WORK (SOW) SMAAART TASK TITLE: SUPERSONIC COMBUSTION TESTS IN THE HYPULSE SHOCK TUBE FACILITY AND HIGH PRESSURE AIR UPGRADE FOR EXTENDED RUN TIME 1.0 INTRODUCTION/BACKGROUND: IN COORDINATION WITH THE NATIONAL CENTER FOR HYPERSONIC COMBINED CYCLE PROPULSION (NCHCCP), NASA INTENDS TO SUPPORT TESTING OF THE HY-V (HIGH-FIVE) SCRAMJET FLOWPATH MODEL IN THE HYPULSE SHOCK TUBE FACILITY LOCATED AT THE ATK GENERAL APPLIED SCIENCES LABORATORY (GASL) FACILITY IN RONKONKOMA, NY. HY-V WAS A PREVIOUSLY FUNDED PROGRAM BY THE DEPARTMENT OF DEFENSE (DOD) TEST RESOURCE MANAGEMENT CENTERS ADVANCED PROPULSION TEST TECHNOLOGY (SINCE RENAMED HIGH SPEED SYSTEMS TEST) FOCUS AREA. THIS TESTING WILL PRODUCE A DATABASE FOR SUPERSONIC COMBUSTION AT SIMULATED HYPERVELOCITY FLIGHT SPEEDS WHICH WILL BE UTILIZED TO HELP IMPROVE THE UNDERSTANDING OF THE COMPLEX PHYSICS WITHIN A SCRAMJET COMBUSTOR. THIS IS RELEVANT TO ON-GOING WORK FOR THE HYPERSONICS PROJECT WHERE THE GOAL IS ULTIMATELY TO BE ABLE TO DESIGN HIGHER PERFORMANCE SCRAMJET COMBUSTORS. THE SCRAMJET MIXING AND COMBUSTION PROCESSES ARE KNOWN TO HAVE THE GREATEST POTENTIAL FOR IMPROVING SCRAMJET ENGINE PERFORMANCE AND EFFICIENCY. THE TESTING WILL EXTEND THE HYPERVELOCITY SCRAMJET CAPABILITY OF BOTH THE NASA HYPERSONICS PROJECT AND THE NCHCCP, ALSO KNOWN AS THE CENTER. THIS TASK WILL LEVERAGE THE EXISTING HARDWARE AND DATA OF THE HY-V TEST PROGRAM. THE HYPULSE FACILITY WILL BE OPERATED IN REFLECTED SHOCK TUBE (RST) MODE TO SIMULATE A FLIGHT MACH NUMBER OF 7 AND 10 WITH CLEAN AIR TEST GAS. THIS FACILITY IS OPERATED BY ATK GASL. FUEL PLUME IMAGING (FPI), AND TUNABLE DIODE LASER ABSORPTION SPECTROSCOPY (TDLAS) ALONG WITH TRADITIONAL WALL PRESSURE AND HEAT FLUX MEASUREMENTS WILL BE CONDUCTED. THE IMAGING WILL BE USED PRIMARILY FOR QUALITATIVE OBSERVATION TO GIVE INSIGHT INTO FLOW PHYSICS AND IN COMPARISON AGAINST COMPUTATIONAL MODELING AS WELL AS THE TRADITIONAL WALL PRESSURE AND HEAT FLUX MEASUREMENTS FOR THE SAME PURPOSES. THESE DATA WILL BE POST-PROCESSED INTO A DATABASE TO BE COMPARED AGAINST COMPUTATIONAL FLUID DYNAMICS (CFD) MODELS. ALSO IN COORDINATION WITH THE TEST RESOURCE MANAGEMENT CENTERS (TRMCS) HIGH SPEED SYSTEM TEST (HSST) TECHNOLOGY AREA, NASA INTENDS TO SUPPORT THE LARGE-SCALE SCRAMJET ENGINE TEST TECHNOLOGY (LSETT) TESTS AT GASL AND DEVELOPMENT OF THE HYPERSONIC AIRBREATHING PROPULSION CLEAN AIR TESTBED (HAPCAT), A NEW TEST CAPABILITY BEING BUILT AT ATK GASL. THE LSETT TESTS AT GASL WILL EXPLORE THE ACCURACY OF SEMI-FREEJET AND DIRECT CONNECT TEST METHODS, CONDUCTED UNDER AIR FORCE RESEARCH LABORATORY (AFRL) CONTRACT F33615-03-D-2416 DO 021 WITH ATK. AN UPGRADE TO THE GASL HIGH PRESSURE AIR SYSTEM IS NECESSARY TO PROVIDE SUFFICIENT RUN TIME FOR THESE TESTS. ADDITIONAL HIGH PRESSURE AIR CAPACITY IS ALSO REQUIRED TO FULLY UTILIZE THE CAPABILITIES OF THE HAPCAT FACILITY, WHICH WILL BE USED TO TEST HYPERSONIC PROPULSION TECHNOLOGY UNDER VARIABLE CONDITIONS FROM MACH 5 TO 8. BOTH OF THESE EFFORTS ARE RELEVANT TO ON-GOING WORK OF THE HYPERSONICS PROJECT WHERE THE GOAL IS ULTIMATELY TO BE ABLE TO DESIGN LARGER AND HIGHER PERFORMANCE SCRAMJET COMBUSTORS. 2.0 SCOPE AND OBJECTIVES: THE SCOPE OF THIS TASK ORDER ENTAILS TWO EFFORTS. FIRST IS TO APPLY OPTICAL IMAGING IN CONJUNCTION WITH CONVENTIONAL MEASUREMENTS TO EXAMINE SUPERSONIC MIXING AND COMBUSTION IN THE HY-V FLOWPATH MODEL. SECOND IS TO INCREASE THE HIGH PRESSURE AIR STORAGE CAPACITY AT GASL IN ORDER TO BE ABLE TO ACHIEVE REQUIRED TEST DURATIONS FOR THE LSETT AND HAPCAT PROJECTS. EXTENDED RUN TIME SUPPORTS NASAS NEED TO CHARACTERIZE THE PERFORMANCE OF FUEL COOLED SCRAMJET ENGINES. THE OBJECTIVES OF THIS TASK ORDER ARE TO: 1) CONDUCT FPI, SCHLIEREN IMAGING, TDLAS WATER CONCENTRATION AND TEMPERATURE MEASUREMENTS, AND PRESSURE AND HEAT FLUX MEASUREMENTS ON THE HY-V FLOWPATH A AT MACH 7 SIMULATED FLIGHT SPEED. 2) CONDUCT FPI, SCHLIEREN IMAGING, TDLAS WATER CONCENTRATION AND TEMPERATU | ATK SPACE SYSTEMS LLC | $315,652 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 13, 2012 | Sep 13, 2012 | Apr 30, 2014 | ||
| IGF::OT::IGF DARPA-BAA-12-02 "PHOENIX" ATK SPACE SYSTEMS, INC., 3. OTHER FUNCTIONS | ATK SPACE SYSTEMS LLC | $6,386,613 | DEPARTMENTAL OFFICES | DEFENSE ADVANCED RESEARCH PROJECTS AGENCY (DARPA) | — | 541330Engineering Services | AZ14 | Jul 6, 2012 | May 31, 2012 | May 31, 2017 | ||
| STATEMENT OF WORK (SOW) - TASK TITLE: HYPERVELOCITY MIXING PROJECT 1.0 INTRODUCTION/BACKGROUND: THE PROPULSION DISCIPLINE OF THE NASA HYPERSONICS PROJECT HAS INITIATED A NEW RESEARCH PROJECT TO INVESTIGATE THE INJECTION AND MIXING OF FUEL AND AIR FOR SCRAMJET ENGINES AT HYPERVELOCITY FLIGHT SPEEDS (GENERALLY CONSIDERED MACH 10 AND GREATER). THIS RESEARCH PROJECT WILL ENHANCE OUR UNDERSTANDING OF SCRAMJET INJECTION AND MIXING DEVICES AND WILL PROVIDE A CONTROLLED TEST ENVIRONMENT TO EVALUATE INNOVATIVE IDEAS. ONE OF THE MILESTONES FOR THE HYPERSONICS PROJECT IS TO DEVELOP AN AIR-BREATHING COMBINED CYCLE SPACE LAUNCH VEHICLE. TO ACHIEVE THIS MILESTONE, A SCRAMJET ENGINE WHICH CAN OPERATE AT HYPERVELOCITY FLIGHT SPEEDS IS CRITICAL. SINCE THE SCRAMJET MIXING AND COMBUSTION PROCESSES ARE KNOWN TO HAVE THE GREATEST POTENTIAL FOR IMPROVING SCRAMJET ENGINE PERFORMANCE AND EFFICIENCY, THIS RESEARCH PROJECT IS INTENDED TO PROVIDE A MAJOR STEP TOWARDS REACHING THE HYPERSONICS PROJECT MILESTONE. THE HYPERVELOCITY MIXING PROJECT, WHICH IS SCHEDULED TO BEGIN IN FY12, WILL INVOLVE GROUND-BASED EXPERIMENTS IN THE NASA LANGLEY RESEARCH CENTER (LARC) ARC-HEATED SCRAMJET TEST FACILITY (AHSTF). CANDIDATE INJECTOR CONCEPTS WILL BE FABRICATED AT LANGLEY USING THE SELECTIVE LASER MELTING PROCESS AND WILL BE MOUNTED TO A COMMON PLATE IN THE TEST FACILITY. FLOWFIELD MEASUREMENTS WILL BE MADE USING LASER-BASED OPTICAL DIAGNOSTICS AND WITH IN-STREAM PRESSURE AND GAS SAMPLING RAKES POSITIONED DOWNSTREAM OF THE INJECTOR HARDWARE. THE EXPECTED OUTCOME OF THE HYPERVELOCITY MIXING PROJECT IS HIGH-SPEED INJECTORS THAT SIGNIFICANTLY IMPROVE SCRAMJET PERFORMANCE (I.E., FASTER MIXING WITH DECREASED DRAG) IN THE HYPERVELOCITY SPEED RANGE. THIS TASK ORDER IS INTENDED TO PROVIDE DESIGN AND FABRICATION SUPPORT OF THE MAJOR HARDWARE COMPONENTS NECESSARY TO SUCCESSFULLY COMPLETE THE GOALS OF THIS PROJECT. 2.0 SCOPE / OBJECTIVE(S): THE SCOPE OF THIS TASK ORDER IS TO OBTAIN THE DESIGN, ANALYSIS, FABRICATION, AND MANUFACTURING SCHEDULES OF THE HARDWARE NECESSARY TO TEST AND EVALUATE VARIOUS FUEL INJECTION DEVICES THAT WILL BE TESTED IN THE LANGLEY AHSTF. THE OBJECTIVES OF THIS TASK ORDER ARE TO: 1) OBTAIN DETAILED ENGINEERING DESIGNS, ANALYSIS, AND ENGINEERING DRAWINGS OF THE TEST HARDWARE. 2) DELIVERY OF TEST HARDWARE. | ATK SPACE SYSTEMS LLC | $296,888 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Dec 28, 2011 | Jan 3, 2012 | Oct 31, 2012 | ||
| SMAAART TASK ORDER: SOW TASK TITLE: WELD REPAIR THERMAL AND STRUCTURAL ANALYSIS FOR THE MACH 5 HIGH DYNAMIC PRESSURE NOZZLE AT NASA LANGLEYS 8 HIGH TEMPERATURE TUNNEL 1.0 INTRODUCTION/BACKGROUND: THE 8 HIGH TEMPERATURE TUNNEL (HTT) AT NASA LANGLEY RESEARCH CENTER (LARC) IS A TRUE ENTHALPY, TRUE PRESSURE, BLOW-DOWN, HYPERSONIC TEST FACILITY THAT IS UTILIZED BY RESEARCH ENGINEERS TO PERFORM HYPERSONIC AEROTHERMODYNAMIC AND PROPULSION SYSTEM TESTING. THE FACILITY PROVIDES TEST CONDITIONS AT MACH 7, MACH 5, MACH 4, AND MACH 3. FOR TESTING AT EACH MACH NUMBER, SEPARATE CONVERGING-DIVERGING NOZZLES ARE REQUIRED TO BE INSTALLED. EACH FACILITY CUSTOMER SELECTS THEIR DESIRED TEST CONDITION AT THE NOMINAL MACH NUMBER AND THE FACILITY STAFF DETERMINES WHAT CONTROLLED CONDITIONS ARE REQUIRED TO MEET THE CUSTOMER S OBJECTIVES. ONE OF THE CONVERGING-DIVERGING NOZZLES AVAILABLE FOR USE BY THE FACILITY CUSTOMERS IS DESIGNATED THE MACH 5 HIGH DYNAMIC PRESSURE NOZZLE (M5HIQ). THIS NOZZLE WAS DESIGNED AND BUILT BY ATK UNDER NASA CONTRACT/TASK ORDER NNL05AA06B, NNL06AA60T. THIS NOZZLE IS REQUIRED TO CONDUCT MISSILE RADOME TESTING BY THE NAVAL AIR WARFARE CENTER AND IS ALSO REQUIRED FOR FUTURE TESTING OF HYPERSONIC ENGINES. RECENTLY, DAMAGE IN THE FORM OF A LARGE SURFACE CRACK WAS FOUND ON THE M5HIQ NOZZLE. THIS LARGE CRACKED HAS CAUSED THE FACILITY TO HALT TESTING OPERATIONS FOR THE NAVAL AIR WARFARE CENTER. BECAUSE THE NOZZLE IS SUBJECTED TO EXTREME TEMPERATURES DURING OPERATION, THE CRACK MUST BE REPAIRED PRIOR TO RESUMING TESTING OPERATION REQUIRING THAT PARTICULAR NOZZLE. NASA WILL CONTRACT THROUGH ITS FABRICATION DIVISION FOR THE WELD REPAIR OF THE NOZZLE CRACK ONCE THE THERMAL / STRUCTURAL ANALYSIS REQUIRED UNDER THIS SOW IS COMPLETED. THIS SOW ANALYSIS WILL REQUIRE RESEARCHING THE INCONEL 800H BASE METAL AND THE WELD FILLER METAL MATERIAL PROPERTIES AT ELEVATED TEMPERATURES AND PERFORMING THERMAL AND STRUCTURAL ANALYSIS OF THIS WELD JOINT TO ESTIMATE THE LOW CYCLE FATIQUE LIFE OF THE REPAIRED NOZZLE. THE WELD JOINT EXPERIENCES TRANSIENT MECHANICAL PRESSURE LOADING COUPLED WITH EXTREME THERMAL TRANSIENTS WHICH COMBINE TO MAKE THIS ANALYSIS COMPLEX. IN ADDITION, THE DATABASE FOR THESE MATERIALS ARE EXPECTED TO BE INCOMPLETE, SO TECHNICAL REASONING BASED ON THE BEST AVAILABLE DATA WILL BE REQUIRED TO COMPLETE THE EFFORT. THE ANALYSIS OF THE WELD JOINT IS REQUIRED TO MEET NASA SAFETY STANDARD LPR 1710.15. THE M5HIQ NOZZLE WAS ORIGINALLY DESIGNED BY ATK-GASL AND THEY POSSESS FEM GRIDS, TUNNEL OPERATING CONDITIONS, AND OTHER THERMAL AND STRUCTURAL ANALYSIS TOOLS THAT CAN BE UTILIZED TO EVALUATE THE WELD REPAIR LOW CYCLE FATIQUE LIFE. THIS ANALYSIS IS CRUCIAL TO THE SAFE RETURN TO TESTING OPERATIONS FOR THE NAVAL AIR WARFARE CENTER. 2.0 SCOPE/OBJECTIVES: THE SCOPE OF THIS TASK ORDER IS TO CONDUCT A THERMAL AND STRUCTURAL ANALYSIS OF THE REPAIR WELD JOINT LOCATED IN THE NASA LARC 8 HTT. THE OBJECTIVE(S) OF THIS TASK ORDER ARE TO: DELIVER A REPORT SHOWING THE LOW CYCLE FATIQUE LIFE FOR THE WELD REPAIR DEPICTED IN THE GOVERNMENT-FURNISHED DRAWING (GFI 5.1). 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 THERMAL / STRUCTURAL ANALYSIS REPORT: 3.1.1 THE CONTRACTOR SHALL CALCULATE THE LOW CYCLE FATIGUE (LCF) LIFE OF THE NOZZLE USING THE GOVERNMENT FURNISHED DRAWING NASA LD-1268149 M5HIQ WELD REPAIR DRAWING (GFI 5.1) DEPICTING THE WELD REPAIR JOINT GEOMETRY. THE CONTRACTOR SHALL USE THE THERMAL AND STRUCTURAL LOADS FROM THE ORIGINAL NASA CONTRACT/TASK ORDER NNL05AA06B, NNL06AA60T. CONCURRENTLY, NASA WILL BE EXECUTING THE WELD REPAIR. THE CONTRACTOR SHALL CALCULATE THE LCF OF THE WELD REPAIR UNDER THE FOLLOWING TWO CONDITIONS: 3.1.1.1 NO NON-DESTRUCTIVE INSPECTION OF THE WELD JOINT IS CONDUCTED DURING THE WELDING. 3.1.1.2 100% X-RAY INSPECTION OF THE WELD JOINT IS CONDUCTED AFTER COMPLETION OF THE WELDING. | ATK SPACE SYSTEMS LLC | $34,075 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Oct 20, 2011 | Oct 20, 2011 | Dec 31, 2011 | ||
| GAME CHANGING DEVELOPMENT PROGRAM (GCDP) OFFICE SUPPORT | ATK SPACE SYSTEMS LLC | $257,422 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Sep 23, 2011 | Sep 23, 2011 | Apr 30, 2012 | ||
| SMAAART TASK ORDER - TITLE: SUPERSONIC COMBUSTION TESTS IN THE HYPULSE SHOCK TUBE FACILITY 1.0 INTRODUCTION/BACKGROUND: IN COORDINATION WITH THE NATIONAL CENTER FOR HYPERSONIC COMBINED CYCLE PROPULSION (NCHCCP), NASA INTENDS TO SUPPORT TESTING OF THE HY-V (HIGH-FIVE) SCRAMJET FLOWPATH MODEL IN THE HYPULSE SHOCK TUBE FACILITY LOCATED AT THE ATK GASL FACILITY IN RONKONKOMA, NY. HY-V WAS A FUNDED PROGRAM BY THE DEPARTMENT OF DEFENSE (DOD) TEST RESOURCE MANAGEMENT CENTERS ADVANCED PROPULSION TEST TECHNOLOGY FOCUS AREA. THIS TESTING WILL PRODUCE A DATABASE FOR SUPERSONIC COMBUSTION AT SIMULATED HYPERVELOCITY FLIGHT SPEEDS WHICH WILL BE UTILIZED TO HELP IMPROVE THE UNDERSTANDING OF THE COMPLEX PHYSICS WITHIN A SCRAMJET COMBUSTOR. THIS IS RELEVANT TO ON-GOING WORK FOR THE HYPERSONICS PROJECT WHERE THE GOAL IS ULTIMATELY TO BE ABLE TO DESIGN HIGHER PERFORMANCE SCRAMJET COMBUSTORS. THE SCRAMJET MIXING AND COMBUSTION PROCESSES ARE KNOWN TO HAVE THE GREATEST POTENTIAL FOR IMPROVING SCRAMJET ENGINE PERFORMANCE AND EFFICIENCY. THE TESTING WILL EXTEND THE HYPERVELOCITY SCRAMJET CAPABILITY OF BOTH THE NASA HYPERSONICS PROJECT AND THE NCHCCP, ALSO KNOWN AS THE CENTER. THIS TASK WILL LEVERAGE THE EXISTING HARDWARE AND DATA OF THE HY-V TEST PROGRAM. THE HYPULSE FACILITY WILL BE OPERATED IN REFLECTED SHOCK TUBE (RST) MODE TO SIMULATE A FLIGHT MACH NUMBER OF 7 WITH CLEAN AIR TEST GAS. THE FACILITY IS OPERATED BY ATK GASL (GENERAL APPLIED SCIENCES LABORATORY). THE CONTRACTOR FOR THIS PROJECT SHALL BE RESPONSIBLE FOR SETTING UP AND RUNNING THE PROPOSED TESTS. FUEL PLUME IMAGING (FPI) AND TUNABLE DIODE LASER ABSORPTION SPECTROSCOPY (TDLAS) ALONG WITH TRADITIONAL WALL PRESSURE AND HEAT FLUX MEASUREMENTS WILL BE CONDUCTED. THE IMAGING WILL BE USED PRIMARILY FOR QUALITATIVE OBSERVATION TO GIVE INSIGHT INTO FLOW PHYSICS AND IN COMPARISON AGAINST COMPUTATIONAL MODELING AS WELL AS THE TRADITIONAL WALL PRESSURE AND HEAT FLUX MEASUREMENTS FOR THE SAME PURPOSES. THESE DATA WILL BE POST-PROCESSED INTO A DATABASE TO BE COMPARED AGAINST COMPUTATIONAL FLUID DYNAMICS (CFD) MODELS. 2.0 SCOPE/OBJECTIVES: THE SCOPE OF THIS TASK ORDER IS TO APPLY OPTICAL IMAGING IN CONJUNCTION WITH CONVENTIONAL MEASUREMENTS TO EXAMINE SUPERSONIC MIXING AND COMBUSTION IN THE HY-V FLOWPATH MODEL. THE TESTS SHALL BE IMPLEMENTED IN THE HYPULSE FACILITY AT ATK GASL, AND WILL BE UTILIZED TO SUPPORT BOTH NASA AND THE CENTERS MUTUAL NEED FOR EXPERIMENTAL HYPERVELOCITY MIXING DATA. THE OBJECTIVES OF THIS TASK ORDER ARE TO: 1) PERFORM FACILITY AND DIAGNOSTIC SHAKEDOWN TESTS. 2) PERFORM TESTING AT MACH 7 SIMULATED FLIGHT SPEED AND RECORD HIGH FIDELITY FPI IMAGING, TDLAS WATER CONCENTRATION AND TEMPERATURE MEASUREMENTS, AND PRESSURE AND HEAT FLUX MEASUREMENTS IN FULFILLMENT OF THE MACH 7 TEST MATRIX REQUIREMENTS. 3) PERFORM REDUCTION AND ANALYSIS OF THE EXPERIMENTAL DATA FOR COMPARISON TO CFD PREDICTION. | ATK SPACE SYSTEMS LLC | $129,769 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Aug 19, 2011 | Aug 19, 2011 | Sep 1, 2017 | ||
| SPACECRAFT PERFORMANCE ANALYSIS&SIMULATION OF INTEGRATED MISSIONS (SPASIM) UPDATES | ATK SPACE SYSTEMS LLC | $34,820 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Jul 25, 2011 | Jul 25, 2011 | Sep 30, 2011 | ||
| KNOWLEDGE CAPTURE FROM NASA TECHNICAL EXPERTS | ATK SPACE SYSTEMS LLC | $57,996 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Jul 12, 2011 | Jul 12, 2011 | Sep 30, 2011 | ||
| CONFIGURATION AND DATA MANAGEMENT AND PROJECT COORDINATION FOR ARD | ATK SPACE SYSTEMS LLC | $304,978 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Jun 30, 2011 | Jul 1, 2011 | Apr 30, 2012 | ||
| EVALUATION OF CONCEPTS FOR REDUCING FLAP SIDE-EDGE NOISE VIA COMPUTATIONAL SIMULATIONS | ATK SPACE SYSTEMS LLC | $307,444 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Jun 9, 2011 | Jun 9, 2011 | Apr 30, 2012 | ||
| AIRSTAR FLIGHT OPERATIONS AND SUPPORT | ATK SPACE SYSTEMS LLC | $169,124 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Mar 31, 2011 | Jul 1, 2011 | Apr 30, 2012 | ||
| SMAAART TASK ORDER: STATEMENT OF WORK (SOW) TASK TITLE: 8-FOOT HIGH TEMPERATURE TUNNEL (8 HTT) LARGE-SCALE SCRAMJET ENGINE TEST TECHNIQUES (LSETT) TEST ENGINEERING SUPPORT 1.0 INTRODUCTION/BACKGROUND: NASAS HYPERSONIC PROJECT, THE AIR FORCE RESEARCH LABORATORY (AFRL), AND THE DEPARTMENT OF DEFENSES (DODS) TEST RESOURCE MANAGEMENT CENTERS ADVANCED PROPULSION TEST TECHNOLOGY FOCUS AREA HAVE ENTERED INTO A COLLABORATIVE TEST EFFORT TO QUANTIFY LARGE SCALE SCRAMJET TO FACILITY INTERACTIONS THAT AFFECT THE TEST ARTICLE PERFORMANCE. FUTURE PROGRAMS FROM ALL THREE AGENCIES FOCUS ON THE DEVELOPMENT OF INCREASINGLY LARGE SCRAMJET ENGINES. THERE ARE TWO EXISTING NATIONAL HYPERSONIC TEST FACILITIES USED TO PERFORM FREEJET TESTING OF SCRAMJET ENGINES. THE FIRST IS THE ARNOLD ENGINEERING DEVELOPMENT CENTERS AERODYNAMIC AND PROPULSION TEST UNIT (APTU) WHICH HAS A 42 DIAMETER HYPERSONIC TEST STREAM. THE SECOND IS THE NASA LANGLEY RESEARCH CENTER 8-FOOT HIGH TEMPERATURE TUNNEL WHICH HAS A 96 DIAMETER TEST STREAM. THE DEVELOPMENT OF LARGER SCRAMJET ENGINES PLACES NEW DEMANDS ON THESE TWO TEST FACILITIES AND RESULTS IN SIGNIFICANT INTERACTION BETWEEN THE TEST ENGINE AND THE TEST FACILITY. IT IS CRITICAL THAT THESE INTERACTIONS AND THE IMPACT THEY HAVE ON THE MEASURED ENGINE PERFORMANCE ARE PREDICTABLE AND WELL UNDERSTOOD. THE INCREASING SIZE OF FUTURE SCRAMJET ENGINES WILL RESULT IN BLOCKING A LARGE PORTION OF THE TEST FACILITY HYPERSONIC FLOW AND WILL ALSO REQUIRE TRUNCATION OF THE ENGINE INLET AND EXIT NOZZLE TO PHYSICALLY FIT INTO THE EXISTING TEST FACILITIES. THE TRUNCATION OF THE INLET AND NOZZLE, AS WELL AS THE LARGE FRACTION OF FLOW BLOCKAGE FOR THESE FUTURE LARGE ENGINES, WILL RESULT IN FACILITY INDUCED IMPACTS ON THE MEASURED ENGINE PERFORMANCE. THE FUTURE DEVELOPMENT AND PRODUCTION OF LARGE SCALE SCRAMJETS DEPEND HEAVILY ON THE ABILITY TO ACCURATELY PREDICT THE IMPACT OF THE TEST FACILITY ON THE MEASURED DATA. THE COLLABORATIVE TESTING EFFORT BETWEEN THE THREE ORGANIZATIONS WILL PRODUCE EXPERIMENTAL DATA ASSESSING THESE IMPACTS AND PROVIDING A BENCHMARK DATA SET RELATIVE TO TEST FACILITY / SCRAMJET INTERACTIONS. 2.0 SCOPE / OBJECTIVE(S): THE SCOPE OF THIS TASK IS TO PROVIDE TEST ENGINEERING SUPPORT FOR THE LSETT TEST IN THE NASA LANGLEY 8 HTT. THE TESTING IS SCHEDULED TO OCCUR DURING THE SECOND HALF OF FY 2011, BUT TEST PREPARATION IS REQUIRED TO BEGIN IN JANUARY 2011 IN ORDER TO MEET THE TEST SCHEDULE. THE OBJECTIVE OF LSETT TESTING IN THE 8 HTT IS TO TEST A CONTRACTOR DESIGNED SCRAMJET ENGINE WITH A FULL INLET AND NOZZLE IN THE 8 HTT AT MACH 5 FLIGHT CONDITIONS. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 TEST PLANNING AND DOCUMENTATION. 3.1.1 THE CONTRACTOR SHALL PARTICIPATE IN WEEKLY TELECONS TO DEFINE THE INTEGRATED RUN SEQUENCE REQUIRED FOR SAFE EXECUTION OF THE LSETT TEST IN THE 8 HTT. THE DEFINITION OF THE INTEGRATED RUN SEQUENCE SHALL BE A COLLABORATIVE EFFORT AND WILL BE MUTUALLY AGREED UPON BY THE CONTRACTOR AND NASA. THE COMPLETED INTEGRATED RUN SEQUENCE SHALL SATISFY ALL NASA LANGLEY TEST SAFETY REQUIREMENTS AND THE CONTRACTOR ENGINE OPERATING LIMITS. FINAL APPROVAL WILL BE GIVEN BY THE NASA TASK MONITOR (TM) VIA EMAIL TO THE CONTRACTORS PROJECT MANAGER (PM). THE CONTRACTOR SHALL UPDATE AND MAINTAIN THE DETAILED INTEGRATED RUN SEQUENCE DOCUMENT (IRSD) FOR WEEKLY REVIEW DURING THE TELECONS. (DELIVERABLE ITEM 4.3). THE INITIAL IRSD DRAFT WILL BE PROVIDED TO THE CONTRACTOR AS SPECIFIED UNDER GOVERNMENT FURNISHED INFORMATION (GFI) SOW 5.1. 3.1.2 THE CONTRACTOR SHALL DEVELOP, AT A MINIMUM, THE FOLLOWING FACILITY SYSTEMS VERIFICATION CHECK LISTS (DELIVERABLE ITEM 4.4): - ENGINE FUEL DELIVERY SYSTEM. - WATER COOLING SYSTEM PERFORMANCE. - SILANE IGNITOR GAS SYSTEM PERFORMANCE. - ANGLE OF ATTACH/MODEL ELEVATOR COORDINATION. - NORMAL STOP SEQUENCE OF EVENTS. - ABNORMAL STOP SEQUENCE | ATK SPACE SYSTEMS LLC | $197,974 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Mar 7, 2011 | Mar 7, 2011 | Jun 29, 2012 | ||
| DESIGN AND DEVELOPMENT OF TEST HARDWARE FOR DEPLOYABLE SPACE STRUCTURES | ATK SPACE SYSTEMS LLC | $25,000 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Feb 8, 2011 | Feb 8, 2011 | Jul 15, 2011 | ||
| HIGH TEMPERATURE LEADING EDGE TEST ARTICLES FOR DARPA ARCLIGHT VEHICLE | ATK SPACE SYSTEMS LLC | $215,688 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Jan 31, 2011 | Jan 31, 2011 | Apr 30, 2012 | ||
| EARTH SYSTEMS SCIENCE PATHFINDER (ESSP) SCHEDULES MANAGEMENT AND REPORTING | ATK SPACE SYSTEMS LLC | $4,118 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Nov 15, 2010 | Nov 15, 2010 | Mar 15, 2011 | ||
| SENSOR INVESTIGATIONS FOR AVIATION HAZARDS | ATK SPACE SYSTEMS LLC | $272,065 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Nov 10, 2010 | Nov 10, 2010 | Apr 30, 2012 | ||
| ENGINEERING DESIGN AND DEVELOPMENT SUPPORT FOR PERIODIC STRUCTURE CONCEPTS | ATK SPACE SYSTEMS LLC | $88,240 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541710 | AD24 | Nov 10, 2010 | Nov 10, 2010 | May 15, 2011 |