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THE BOEING COMPANY
HUNTINGTON BEACH, CA, 92647
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Prime contracting experience
11 records from government sources. Past participation is not evidence of current teaming interest.
| Role | Agency | Description | Vehicle | Obligated | Action date | Period |
|---|---|---|---|---|---|---|
| Prime | Department of Defense Defense Contract Management Agency | IGF::OT::IGF ASSESSING THE DURABILITY AND DAMAGE TOLERANCE OF ADVANCED COMPOSITE STRUCTURAL FEATURES | — | $2,114,724 | Aug 30, 2024 | Feb 6, 2017 – May 7, 2019 |
| Prime | National Aeronautics and Space Administration National Aeronautics and Space Administration | IGF::OT::IGF TASK TITLE: REDUCING RISK TO ACHIEVING THE NASA N2 NOISE GOAL. 1.0 INTRODUCTION/BACKGROUND:NASAS ENVIRONMENTALLY RESPONSIBLE AVIATION (ERA) PROJECT HAS FOCUSED ON DEVELOPING AND DEMONSTRATING TECHNOLOGIES FOR INTEGRATED AIRCRAFT SYSTEMS. THE FUEL BURN GOAL IS A REDUCTION BY 50 RELATIVE TO A BEST IN FLEET AIRCRAFT IN 2005, THE NOISE GOAL IS 42 DECIBELS (DB) CUMULATIVE RELATIVE TO THE FEDERAL AVIATION ADMINISTRATIONS STAGE 4 REQUIREMENT, AND THE EMISSIONS GOAL IS FOR A REDUCTION OF 75 IN NITROUS OXIDE BELOW THE COMMITTEE ON AVIATION ENVIRONMENTAL PROTECTION STANDARD NUMBER 6 (CAEP6). THE TARGET DATE IS 2020 FOR KEY TECHNOLOGIES TO BE AT A TECHNOLOGY READINESS LEVEL (TRL) OF FOUR TO SIX (I.E., SYSTEM OR SUB-SYSTEM PROTOTYPE DEMONSTRATED IN A RELEVANT ENVIRONMENT). THIS CORRESPONDS TO A PROJECTED AIRCRAFT ENTRY INTO SERVICE NO EARLIER THAN 2025. THESE GOALS AND TIMEFRAME ARE DEFINED BY NASA AS N21. THIS EFFORT BUILDS UPON PREVIOUS CONTRACT WORK BY BOEING. THE HYBRID WING BODY (HWB) AIRCRAFT WAS PREVIOUSLY IDENTIFIED AS ONE CONCEPT THAT HAS THE POTENTIAL TO MEET THE ERA PROJECTS AIRCRAFT NOISE GOAL. NASA PUBLISHED IN AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS (AIAA) PAPER NUMBERS 2010-3912 AND 2010-3913 RESULTS SHOWING A TECHNICAL PATH FOR THE HWB CONCEPT TO MEET THE 42 DB GOAL. UNDER THE ERA ADVANCED VEHICLE CONFIGURATIONS (AVC) TASK THE ADVANCED HWB AIRCRAFT CONCEPT PROPOSED BY BOEING WAS SHOWN TO MEET ALL THREE OF THE ERA N2 GOALS SIMULTANEOUSLY. NASA HAS PARTICIPATED IN A DETAILED AND UPDATED NOISE ASSESSMENT THAT WAS PUBLISHED AS AIAA PAPER 2014-0365 (GUO, BURLEY, AND THOMAS) INCLUDING COMPARISON WITH THE PREVIOUS NASA NOISE ASSESSMENT. FINALLY, UNDER SMAAART TASK ORDER NNL13AB86T, BOEING IS CURRENTLY WORKING WITH AN UPDATED DESIGN OF ITS HWB PREFERRED SYSTEM CONCEPT (PSC) AIRCRAFT WITH IMPROVED DESIGN FEATURES INCLUDING A KRUEGER FLAP LEADING EDGE, AN IMPROVED ENGINE SELECTION, AND IMPROVED ENGINE/AIRFRAME INTEGRATION.IN REVIEW OF THE ABOVE RESEARCH, NASA HAS IDENTIFIED FOUR CRITICAL AREAS NEEDED TO IMPROVE NASAS CURRENT SYSTEM NOISE ASSESSMENT METHODOLOGY. ALSO, INVESTIGATION OF NOISE REDUCTION APPROACHES IN THESE FOUR AREAS WILL RESULT IN HIGHER CONFIDENCE NOISE ASSESSMENTS RELATIVE TO MEETING THE 42 DB GOAL. IT IS OF ADDITIONAL VALUE TO NASA THAT THE RESULTS FROM THIS TASK WILL ALSO BE APPLICABLE TO ASSESSMENTS OF OTHER ADVANCED AIRCRAFT CONCEPTS. THE OVERALL PURPOSE OF THIS TASK ORDER IS TO REDUCE THE RISK TO ACHIEVING THE 42 DB GOAL BASED ON THE MOST ADVANCED ASSESSMENTS TO BE DONE BY NASA ON THE ERA VEHICLE CONCEPTS. 1.NASAS RESEARCH FOCUSES ON FUTURE AIRCRAFT DESIGN CONCEPTS AND TECHNOLOGY THAT COULD BE INTRODUCED INTO SERVICE IN 2020, 2025 AND 2030. THE FIRST NEXT GENERATION FOR 2020 IS REFERRED TO AS N1. THE SECOND GENERATION IS N2. THE THIRD AND FARTHEST OUT GENERATION IS N3. EACH DESIGN GENERATION OFFERS TECHNOLOGY FEATURES MORE SOPHISTICATED THAN THOSE OF THE GENERATION BEFORE. 2.0 SCOPE&OBJECTIVE(S):2.1THE SCOPE OF THIS TASK ORDER IS LIMITED TO USING BOEINGS HWB PSC IN THE FOLLOWING FOUR TECHNICAL AREAS THAT HAVE BEEN IDENTIFIED AS CRITICAL TO IMPROVING THE CURRENT STATE OF THE ART OF NASAS AIRCRAFT SYSTEM NOISE ASSESSMENTS, TO ACHIEVE THE 42 DB NOISE GOAL. 1.HIGH FIDELITY ULTRA-HIGH BYPASS (UHB) FAN NOISE SHIELDING EFFECTIVENESS. 2.AIRFRAME SYSTEM DATABASE WITH COMPONENT NOISE RANKING. 3.KRUEGER FLAP NOISE. 4.FLIGHT PATH AND SYSTEM NOISE OPTIMIZATION. THE CONTRACTOR SHALL UTILIZE COMPUTATIONAL AND ANALYTICAL MODELING METHODS AND ANALYSIS OF EXISTING EXPERIMENTAL AND SIMULATION DATA IN CONDUCTING THE WORK UNDER THIS SOW. 2.2THE OBJECTIVES OF THIS TASK ORDER ARE TO: 1. DEVELOP SHIELDING SUPPRESSION MAPS FROM HIGH FIDELITY SIMULATIONS OF UHB AFT RADIATED FAN NOISE THAT ARE TO BE USED IN SYSTEM NOISE ASSESSMENTS.2. DEVELOP AND PREDICT THE PERFORMANCE OF A CONC | NNL10AA05BUSAspending | $2,382,032 | Sep 22, 2023 | Sep 16, 2015 – Oct 12, 2016 |
| Prime | Department of Defense Defense Contract Management Agency | IGF::OT::IGF WIND SENSING INTEGRATION STUDY | FA865008D3857USAspending | $310,659 | Sep 18, 2023 | Mar 14, 2017 – Aug 15, 2018 |
| Prime | National Aeronautics and Space Administration National Aeronautics and Space Administration | IGF::OT::IGF TRUSS BRACED WING DESIGN AND TEST 1.0 INTRODUCTION/BACKGROUND:AS PART OF THE NASA FUNDAMENTAL AERONAUTICS PROGRAM, THE FIXED WING (FW) PROJECT IS PERFORMING RESEARCH INTO CONCEPTS, TECHNOLOGIES, AND TOOLS THAT WILL ENABLE DRAMATIC REDUCTIONS IN NOISE AND EMISSIONS, AND INCREASE THE PERFORMANCE (FUEL BURN AND REDUCED FIELD LENGTH) CHARACTERISTICS OF SUBSONIC/TRANSONIC FIXED WING AIRCRAFT. THE FW PROJECT PURSUES A MULTI-GENERATIONAL APPROACH ADDRESSING THE NEEDS OF TODAY BUT WITH AN EMPHASIS ON ESTABLISHING THE TECHNOLOGICAL FOUNDATIONS NECESSARY TO ENABLE THE CAPABILITIES NEEDED IN THE DECADES AHEAD. NASA SUBSONIC TRANSPORT SYSTEM LEVEL METRICS/GOALS ARE SHOWN BELOW IN TABLE 1. TABLE 1: NASA'S TECHNOLOGY GOALS FOR FUTURE SUBSONIC VEHICLES THIS EFFORT IS INTENDED TO IDENTIFY HIGH PAY-OFF RESEARCH THAT BUILDS ON THE EXISTING KNOWLEDGE AND RESULTS OF THE TRUSS-BRACED WING (TBW) RESEARCH TO FURTHER REFINE AND ADVANCE THE TBW DESIGN CONFIGURATION AND VALIDATE THE LIFT/DRAG (L/D) AERODYNAMIC PERFORMANCE FOR ON AND OFF DESIGN CONDITIONS. THE TBW IS A TECHNOLOGY CONCEPT THAT HAS THE POTENTIAL TO CHANGE THE DESIGN SPACE BY AFFECTING THE TRADES BETWEEN WING SWEEP, THICKNESS, SPEED, LIFT, AND WEIGHT. THESE TRADES CAN ENABLE VERY HIGH ASPECT RATIO, HIGH SPAN WINGS THAT MAY CONTRIBUTE SIGNIFICANTLY TO AN OVERALL FUEL BURN REDUCTION GOAL OF -60% FOR TRANSPORT AIRCRAFT ENTERING INTO SERVICE IN THE 2030-35 TIMEFRAME, MARKET PERMITTING, RELATIVE TO 2005 BEST-IN-CLASS AIRCRAFT. CURRENT AERODYNAMIC PREDICTIONS FOR HIGH-SPEED AND LOW-SPEED AERODYNAMIC PERFORMANCE FOR HIGH SPAN TBWS ARE LIMITED BY A SHORTAGE OF RELEVANT EMPIRICAL DATA. THIS UNCERTAINTY, WHEN CYCLED THROUGH PERFORMANCE AND SIZING, RESULTS IN SIGNIFICANT VARIATIONS IN AIRCRAFT WING AREA AND OTHER PARAMETERS IMPORTANT TO THE WING DESIGN AND OPTIMIZATION. CRUISE DRAG UNCERTAINTY IS PRIMARILY CAUSED BY UNKNOWN STRUT-WING INTERFERENCE. EMPIRICAL DATA FOR A TRANSONIC STRUT-WING FAIRING IS NOT KNOWN TO EXIST. ADDITIONALLY, NACELLES ARE QUITE DIFFERENT THAN STRUTS AND THE ATTAINABLE LEVEL OF INTERFERENCE IS CURRENTLY UNKNOWN. LOW-SPEED ANALYSES AND OPTIMIZATION OF SPANWISE FLAP DEFLECTION IS NECESSARY FOR AN ACCURATE PREDICTION OF TAKEOFF PERFORMANCE. THIS RESULTS IN UNCERTAINTY IN THE LOW-SPEED PERFORMANCE OF THE AIRCRAFT AS LIFT TO DRAG RATIO IS EQUALLY IMPORTANT AS MAXIMUM LIFT COEFFICIENT. EXISTING METHODS FOR DETERMINING THE DYNAMIC EFFECTS OF LARGE ROLL AND PITCH RATES ARE INSUFFICIENT FOR HIGH ASPECT RATIO WINGS. ROLL DAMPING ESTIMATES BASED ON CONVENTIONAL WING ASPECT RATIOS MAY BE INSUFFICIENT TO ESTIMATE ROLL CONTROL POWER REQUIRED. EFFECTS OF AILERON AND/OR SPOILER DEFLECTION MUST BE CONSIDERED IN THE PERFORMANCE AND IN AEROELASTIC COUPLING TO THE SPANLOAD AND THUS TO THE ROLL DAMPING. DUE TO THE HIGH WING SPAN, ALLOWABLE ROLL ANGLE FOR TAKEOFF AND LANDING WILL BE LOWER THAN A CONVENTIONAL AIRCRAFT, POSSIBLY AFFECTING CROSSWIND CONTROL. ANOTHER POTENTIAL CONCERN IS THE ROLL-YAW COUPLING. THE HIGH SPAN WING, ESPECIALLY AT HIGH ROLL RATES THAT CAN RESULT IN SEPARATED FLOW NEAR THE WING TIPS, CAN LEAD TO UNUSUALLY LARGE YAWING MOMENT COEFFICIENT DUE TO ROLL RATE DERIVATIVE (I.E., CNP VALUES) VALUES WHICH MAY AFFECT VERTICAL TAIL SIZING BEYOND THE NORMAL TRIM, ENGINE-OUT, AND DIRECTIONAL STABILITY CRITERIA. FOR THE PITCH AXIS, UNDERSTANDING CHANGES IN BASIC WING+BODY STABILITY LEVELS IN BOTH THE CRUISE AND IN THE HIGH-LIFT CONFIGURATIONS IS ALSO ESSENTIAL. IN ORDER TO MITIGATE THESE UNCERTAINTIES, HIGHER FIDELITY AERODYNAMIC DATA AT OFF-DESIGN CONDITIONS ARE NEEDED TO AUGMENT AND IMPROVE THE STRUCTURES, LOADS, AND STABILITY AND CONTROL ANALYSES IN ADDITION TO THE PRIMARY ON-DESIGN CRUISE DRAG (L/D) FOR THE TBW CONFIGURATION. 2.0 SCOPE, OBJECTIVE(S), APPLICABLE DOCUMENTS, AND ACRONYMS: 2.1 SCOPE: THE SCOPE OF THIS TASK ORDER IS TO REFINE THE DESIGN OF A TRANSONIC TBW AIRCRAFT WITH HIGH-FIDELITY TOOLS, AND ANY R | NNL10AA05BUSAspending | $4,996,630 | Aug 23, 2023 | Jul 22, 2014 – Oct 12, 2016 |
| Prime | National Aeronautics and Space Administration National Aeronautics and Space Administration | IGF::OT::IGF SMAAART (SMART MODEL FOR ATMOSPHERIC AND ASTRONOMICAL RADIANCE AND TRANSMITTANCE) TASK ORDER TITLED ADVANCED COMPSITES PROJECT (ACP)FOR CERTIFICATION TIMELINE REDUCTION . 1.0 INTRODUCTION/BACKGROUND: THE NASA ADVANCED COMPOSITES PROJECT (ACP) IS FOCUSED ON REDUCING THE TIMELINE FOR DEVELOPING AND CERTIFYING STATE-OF-THE-ART COMPOSITE STRUCTURES BY 30 PERCENT IN AN EFFORT TO RETAIN AMERICAS COMPETITIVE ADVANTAGE IN THE GLOBAL AEROSPACE INDUSTRY. IN ORDER TO ACHIEVE THIS AGGRESSIVE AND FAR REACHING GOAL, NASA HAS WORKED TO SET UP A PUBLIC-PRIVATE PARTNERSHIP KNOWN AS THE ADVANCED COMPOSITES CONSORTIUM (ACC). THE CONSORTIUM CONSISTS OF NASA, THE FEDERAL AVIATION ADMINISTRATION (FAA), BOEING, GENERAL ELECTRIC, LOCKHEED MARTIN, NORTHROP GRUMMAN, AND UNITED TECHNOLOGIES CORPORATION. THE ADVANCED COMPOSITES PROJECT IS DIVIDED INTO TWO PHASES. PHASE I IS INVESTIGATING A WIDE RANGE OF HIGH PAYOFF TOOLS AND METHODOLOGIES IDENTIFIED BY THE ACC MEMBERS. PHASE II WILL MATURE AND VALIDATE THE TECHNOLOGIES SHOWN TO HAVE THE MOST IMPACT DURING THE PHASE I INVESTIGATION. THE WORK DEFINED IN THIS STATEMENT OF WORK (SOW) REPRESENTS A PORTION OF THE ACP PHASE I ACTIVITIES THAT IS NOT INTENDED INCLUDE LIMITED RIGHTS DATA OR RESTRICTED RIGHTS SOFTWARE AS DEFINED UNDER FAR 52.227-14 (RIGHTS IN DATA GENERAL), AS MODIFIED BY NFS 1852.227-14. THESE ACTIVITIES ARE LIMITED TO: ASSESSING THE CURRENT STATE OF PRACTICE, IDENTIFYING TECHNOLOGY GAPS, FABRICATING COUPONS AND NON-DESTRUCTIVE EVALUATION (NDE) STANDARDS, AND EVALUATING MANUFACTURING PROCESSES AND SIMULATIONS. THE CONTRACTOR SHALL ALSO DEVELOP A REPRESENTATIVE DEVELOPMENT TO CERTIFICATION TIMELINE MODEL TO QUANTIFY THE TIMELINE REDUCTION ASSOCIATED WITH EACH OF THE TOOLS AND METHODS DEVELOPED OR MATURED UNDER THE ACP. NASA WILL USE THE DEVELOPMENT TO CERTIFICATION TIMELINE MODEL TO: 1) MEASURE PROGRESS TOWARD THE OVERALL ACP GOAL OF REDUCING THE TIMELINE BY 30%, 2) SELECT THE MOST PROMISING TOOLS AND METHODOLOGIES TO FURTHER ADVANCE IN PHASE II OF THE ACP, AND 3) DETERMINE THE FINAL TIMELINE REDUCTION ACHIEVED AT THE END OF THE 5-YEAR PROJECT. SUCCESSFUL IMPLEMENTATION OF THE ACP GOAL WILL SERVE TO BRING PRODUCTS TO THE AEROSPACE MARKET SOONER AND PROVIDE IMPROVED CHARACTERIZATION OF MAJOR COMPOSITE COMPONENTS TO ENHANCE SAFETY AND PERFORMANCE. 2.0 SCOPE, OBJECTIVES, AND DEFINITIONS FOR TERMS AND ACRONYMS:2.1SCOPE:THE SCOPE OF THIS TASK ORDER IS TO PERFORM STATE OF THE ART ASSESSMENTS, PLAN DEVELOPMENTS, FABRICATE COUPON AND PANEL TEST SPECIMENS, AND PERFORM THE INITIAL TESTING AND DATA COLLECTION NECESSARY TO SUPPORT FUTURE ADVANCED COMPOSITE PROJECT ACTIVITIES CURRENTLY PLANNED FOR THE ADVANCED COMPOSITES CONSORTIUM. 2.2 OBJECTIVES:THE OBJECTIVES OF THIS TASK ORDER ARE:A)DEVELOPING A DEVELOPMENT TO CERTIFICATION TIMELINE MODEL FOR ASSESSING THE TIMELINE REDUCTION POTENTIAL OF VARIOUS TECHNOLOGIES DEVELOPED UNDER THE ACP.B)OBTAINING MATERIAL PROPERTY INPUT DATA AND DEVELOPING VALIDATION PLANS FOR THE MOST PROMISING PROGRESSIVE FAILURE ANALYSIS TOOLS APPROPRIATE FOR SIZING AIRCRAFT STRUCTURES. C)OBTAINING MATERIAL PROPERTY INPUT DATA AND DEVELOPING VALIDATION PLANS FOR THE MOST PROMISING PROGRESSIVE FAILURE ANALYSIS TOOLS APPROPRIATE FOR SIZING JET ENGINE FAN CONTAINMENT AND FUSELAGE SHIELDING STRUCTURES. D)EVALUATING THE MOST PROMISING RAPID DESIGN TOOLS, DEVELOPING VALIDATION PLANS, AND ESTABLISHING REQUIREMENTS FOR ADVANCING RAPID DESIGN TOOLS. E)EVALUATING THE NON-DESTRUCTIVE EVALUATION (NDE) INDUSTRY STATE OF PRACTICE AND DEVELOPING NDE STANDARDS COUPONS FOR EVALUATING ADVANCED NDE TECHNIQUES. F)EVALUATING THE ACCURACY AND CAPABILITY OF CURRENTLY AVAILABLE AUTOMATED FIBER PLACEMENT (AFP) SIMULATION SOFTWARE TO ASSESS HOW IT CAN BE INCORPORATED INTO A FULL DESIGN FOR MANUFACTURING SOFTWARE SUITE. G) CHARACTERIZING THE EFFECTS OF AFP DEFECTS TO BETTER UNDERSTAND THE ASSOCIATED MATERIAL PROPERTY REDUCTION. | NNL10AA05BUSAspending | $6,291,684 | Aug 15, 2023 | May 21, 2015 – Oct 12, 2016 |
| Prime | Department of Defense Defense Contract Management Agency | IGF::OT::IGF ADVANCED TURBINE TECHNOLOGY FOR AFFORDABLE MISSION CAPABILITY | FA865015D2507USAspending | $1,612,860 | Aug 13, 2022 | Aug 18, 2016 – May 30, 2018 |
| Prime | National Aeronautics and Space Administration National Aeronautics and Space Administration | IGF::OT::IGF TASK ORDER - STATEMENT OF WORK (SOW) TASK TITLE: BOEING LCAT ARC JET TEST IN SUPPORT OF FLEXIBLE TPS EVALUATION AND DEVELOPMENT 1.0 INTRODUCTION / BACKGROUND: THE HYPERSONIC INFLATABLE AERODYNAMIC DECELERATOR (HIAD) PROJECT IS A TECHNOLOGY DEVELOPMENT EFFORT INVESTIGATING THE VIABILITY AND SURVIVABILITY OF INFLATABLE AERODYNAMIC DECELERATORS AT FLIGHT RELEVANT ENVIRONMENTS FOR APPLICATION TO FUTURE PLANETARY ENTRY SPACECRAFT. IN ORDER TO EVALUATE A FLEXIBLE THERMAL PROTECTION SYSTEMS (FTPS), WHICH IS THE HEAT SHIELD FOR THE HIAD, THE FTPS MUST BE SUBJECTED TO FLIGHT-RELEVANT HEATING, PRESSURES, AND SHEARING ENVIRONMENTS EXPERIENCED DURING REENTRY, AND SHOW MARGINED PERFORMANCE AND SURVIVAL. IN SUPPORT OF THE HIAD PROJECTS FLEXIBLE SYSTEMS TECHNICAL DEVELOPMENT AREA, THE NASA LANGLEY RESEARCH CENTER (LARC) ENGINEERING GROUP IS MODELING, TESTING, AND VERIFYING MODELING OF FTPS LAYUPS IN FLIGHT RELEVANT REACTIVE FLOW ENVIRONMENTS IN ORDER TO ESTABLISH A MODELING PARADIGM AND A MORE EFFECTIVE MARGIN POLICY FOR INFLATABLE AND RIGID REENTRY SYSTEMS. SPECIFIC NASA PROVIDED SPECIMENS, (MADE UP OF VARIOUS LAYUP COMBINATIONS OF ADVANCED FLEXIBLE MATERIALS) ARE MODELED AND TESTED IN FLIGHT RELEVANT CONDITIONS FOR MODEL VERIFICATION AND MARGIN MATURATION. THIS EFFORT BUILDS UPON TESTING ALREADY CONDUCTED AT THE LCAT UNDER BOEINGS SMAAART CONTRACT NNL10AA05B, TASK ORDER NNL11AD16T, ENTITLED BOEING LCAT ARC-JET TEST IN SUPPORT OF FLEXIBLE TPS EVALUATION AND DEVELOPMENT. UNDER NNL11AD16T, HUNDREDS OF FTPS SAMPLES HAVE BEEN EVALUATED AT SEVERAL CONDITIONS OF DEVELOPMENT INTEREST, ESTABLISHING A BASIS FOR THE CRITICAL ADVANCEMENT OF THE SUCCESSFUL FLIGHT OF THE INFLATABLE REENTRY VEHICLE EXPERIMENT (IRVE)-3 IN JULY 2012 AND ADVANCING THE DEVELOPMENT OF THE NEXT GENERATION OF FTPS. THE TESTING DESCRIBED BY THIS SOW WILL CONTINUE THIS CRUCIAL ADVANCEMENT BY BUILDING UPON THE DATABASE OF RESULTS ALREADY OBTAINED. FURTHER TESTING IS NEEDED TO COMPARE MORE ADVANCED MATERIALS AND LAYUPS WITH PREVIOUSLY TESTED COUPONS AND TO EXTEND THE HEAT FLUX AND PRESSURE TEST RANGE, SIMULATING HARSHER ATMOSPHERIC REENTRY FLIGHT ENVIRONMENTS. 2.0 SCOPE&OBJECTIVE(S): THE SCOPE OF THIS TASK ORDER IS TO EVALUATE FTPS LAYUPS AND MATERIALS AT COMPARABLE OR HARSHER SIMULATED ATMOSPHERIC REENTRY FLIGHT CONDITIONS AND RIGID DEPLOYABLE TPS LAYUPS AND MATERIALS AT MUCH HARSHER SIMULATED ATMOSPHERIC REENTRY FLIGHT CONDITIONS. FTPS MATERIALS AND SYSTEMS WILL BE TESTED UTILIZING THE LCAT FACILITY FOR 12 WEEKS OF TOTAL TEST TIME AT FOUR SPECIFIC TEST CONDITIONS WHICH SIMULATE RELEVANT TEST ENVIRONMENTS. THE FIRST TWO TEST CONDITIONS, GIVEN IN OBJECTIVES 1 AND 2 BELOW, WERE DEVELOPED UNDER TASK ORDER NNL11AD16T. NEW MATERIALS AND SYSTEMS WILL BE COMPARED AT THESE CONDITIONS. THE REMAINING TWO TEST CONDITIONS ARE NEW TEST REQUIREMENTS OUTLINED IN OBJECTIVES 3 AND 4 BELOW TO EXTEND THE RANGE OF THE CURRENT MATERIALS AND SYSTEMS DATA BASE. THE OBJECTIVES FOR THIS TASK ORDER ARE AS FOLLOWS: OBJECTIVE ONE: EVALUATION OF FTPS LAYUPS AND MATERIALS AT FLIGHT-LIKE CONDITIONS SIMULATING A HEAT FLUX ENTRY CONDITION (SQUARE PULSE OR MISSION PROFILE IN STAGNATION OR SHEAR) OF<50 W/CM2 (HEAT FLUX BETWEEN ~17 AND<50 W/CM2, PRESSURE BETWEEN ~1.7 AND ~10KPA). OBJECTIVE TWO: EVALUATION OF FTPS LAYUPS AND MATERIALS AT FLIGHT-LIKE CONDITIONS SIMULATING A HEAT FLUX ENTRY CONDITION (SQUARE PULSE OR MISSION PROFILE IN STAGNATION OR SHEAR) OF ~50 W/CM2 (HEAT FLUX ~50 W/CM2, PRESSURE ~6KPA). OBJECTIVE THREE: EVALUATION OF FTPS LAYUPS AND MATERIALS AT FLIGHT-LIKE CONDITIONS SIMULATING A HEAT FLUX ENTRY CONDITION (SQUARE PULSE OR MISSION PROFILE IN STAGNATION OR SHEAR) OF ~75 W/CM2 (HEAT FLUX ~75W/CM2, PRESSURE ~10KPA). OBJECTIVE FOUR: EVALUATION OF FTPS LAYUPS AND MATERIALS AT FLIGHT-LIKE CONDITIONS SIMULATING A HEAT FLUX ENTRY CONDITION (SQUARE PULSE IN STAGNATION) OF ~130 W/CM2 (HEAT FLUX ~130 W/CM2, PRESSURE BETWEEN ~6 AND ~12K | NNL10AA05BUSAspending | $1,020,511 | Aug 12, 2022 | Aug 8, 2013 – Oct 12, 2016 |
| Prime | National Aeronautics and Space Administration National Aeronautics and Space Administration | COMPOSITE CRYOGENIC TECHNOLOGIES AND DEMONSTRATION (CCTD) TASK ORDER | NNL10AA05BUSAspending | $26,291,530 | Aug 4, 2022 | Sep 16, 2011 – Oct 12, 2016 |
| Prime | National Aeronautics and Space Administration National Aeronautics and Space Administration | 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. | — | $599,558 | Jun 29, 2022 | Sep 1, 2017 – Mar 31, 2023 |
| Prime | Department of Defense Defense Contract Management Agency | IGF::OT::IGF POWER AND THERMAL ADVANCED DEMONSTRATION DESIGN (PTADD) - NEW TASK ORDER | FA865008D3857USAspending | $12,807,965 | Jun 21, 2022 | Mar 31, 2016 – Sep 3, 2019 |
| Prime | Department of Defense Defense Contract Management Agency | IGF::OT::IGF LOW COST ATTRITABLE AIRCRAFT DEVELOPMENT | FA865008D3857USAspending | $1,524,436 | Apr 4, 2022 | Dec 17, 2015 – Dec 23, 2016 |
Contract vehicles are shown only when present in the source record. Linked award numbers and vehicles open the authoritative record on USAspending.gov.
Subcontracting experience
2 records from government sources. Past participation is not evidence of current teaming interest.
| Role | Agency | Description | Vehicle | Obligated | Action date | Period |
|---|---|---|---|---|---|---|
| Subcontractor | Department of Defense | OPTION PHASE II - EVALUATION OF BENCHMARKS ON APPLICATION INSTANCES 21025-221774-QS CN 3 Parent award context Parent award agency: Department of Defense · Defense Advanced Research Projects Agency Parent award NAICS: 541715 Parent award performance state: CA Parent award description: QUANTUM BENCHMARKING PROGRAM View parent award on USAspending | — | $194,137 | Oct 13, 2023 | — – — |
| Subcontractor | Department of Defense | GATHER CANDIDATE PROBLEMS TO IDENTIFY APPLICATION INSTANCES TO BE SOLVED WITH A QUANTUM COMPUTER. APPLICATION EXPERTS TO IDENTIFY AND CHARACTERIZE HIGH IMPACT PROBLEMS AND COMMUNICATE RELEVANT DETAILS OF THESE PROBLEMS, INCLUDING QUANTIFICATION AND ESTIMATION OF UTILITY. 21025-221774-QS Parent award context Parent award agency: Department of Defense · Defense Advanced Research Projects Agency Parent award NAICS: 541715 Parent award performance state: CA Parent award description: QUANTUM BENCHMARKING PROGRAM View parent award on USAspending | — | $235,978 | Jun 14, 2022 | — – — |
Contract vehicles are shown only when present in the source record. Linked award numbers and vehicles open the authoritative record on USAspending.gov.
Agencies supported
- Department of DefenseGov-sourced
- National Aeronautics and Space AdministrationGov-sourced
Government-sourced data comes from SAM.gov, SBA and USAspending.gov and is attributed to its source. Items marked company-reported were provided by the company and are verified by FedSub only where labeled. FedSub is a private company and is not affiliated with SBA, GSA/SAM.gov, or any government agency.