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Award ID | Description | Recipient | Total Value | Awarding Agency | Funding Agency | Set Aside | NAICS | PSC | Award Date | Start Date | End Date | |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| NATIONAL CYBER RANGE COMPLEX INNOVATION AND TECHNOLOGY COUNCIL | THE BOEING COMPANY | $827,334 | DEPT OF THE ARMY | IMMEDIATE OFFICE OF THE SECRETARY OF DEFENSE | — | 541519Other Computer Related Services | DA01IT AND TELECOM - BUSINESS APPLICATION/APPLICATION DEVELOPMENT SUPPORT SERVICES (LABOR) | Jul 30, 2021 | Jul 27, 2021 | Apr 26, 2027 | ||
| 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. | THE BOEING COMPANY | $599,558 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR22 | Sep 1, 2017 | Sep 1, 2017 | Mar 31, 2023 | ||
| IGF::OT::IGF SUPERSONIC TAILLESS EVALUATION OF EFFECTORS (STEER) | THE BOEING COMPANY | $4,917,400 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Aug 1, 2017 | Aug 1, 2017 | Sep 24, 2019 | ||
| IGF::OT::IGF EVADE - AVIATR FOLLOW ON TASK ORDER | THE BOEING COMPANY | $2,440,821 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Jun 29, 2017 | Jun 29, 2017 | Sep 10, 2019 | ||
| IGF::OT::IGF WIND SENSING INTEGRATION STUDY | THE BOEING COMPANY | $313,851 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Mar 14, 2017 | Mar 14, 2017 | Aug 15, 2018 | ||
| IGF::OT::IGF ASSESSING THE DURABILITY AND DAMAGE TOLERANCE OF ADVANCED COMPOSITE STRUCTURAL FEATURES | THE BOEING COMPANY | $2,135,812 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Feb 6, 2017 | Feb 6, 2017 | May 7, 2019 | ||
| IGF::OT::IGF AERIAL REFUELING OPERATOR AUTOMATION | THE BOEING COMPANY | $1,173,969 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC11NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; BASIC RESEARCH | Dec 21, 2016 | Dec 21, 2016 | May 9, 2018 | ||
| IGF::OT::IGF TBCC FLIGHT DEMO CONCEPTUAL STUDY - VAATE III | THE BOEING COMPANY | $2,951,930 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Oct 7, 2016 | Oct 7, 2016 | Apr 30, 2018 | ||
| IGF::OT::IGF ADVANCED TURBINE TECHNOLOGY FOR AFFORDABLE MISSION CAPABILITY | THE BOEING COMPANY | $1,644,805 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Aug 18, 2016 | Aug 18, 2016 | May 30, 2018 | ||
| IGF::OT::IGF NRA SUBTOPIC 2.4, SASO1 "REVOLUTIONARY AND ADVANCED UNIVERSAL, RELIABLE, ALWAYS AVAILABLE, CYBER SECURE AND AFFORDABLE COMMUNICATION, NAVIGATION, SURVEILLANCE (CNS) OPTIONS FOR ALL ALTITUDES OF UAS OPERATIONS." THE SCOPE OF THE THIS WORK IS TO IDENTIFY REVOLUTIONARY AND ADVANCED INTEGRATED CNS SYSTEMS AND TECHNOLOGY OPTIONS THAT CAN SUPPORT UAS OPERATING AT ALL ALTITUDES AND IN ALL AIRSPACE. THE SYSTEM IS REQUIRED TO INCLUDE AIR-AIR AND AIR-GROUND CAPABILITIES. THESE CNS ALTERNATIVES MUST BE RELIABLE, REDUNDANT, ALWAYS AVAILABLE, CYBER-SECURE, AND AFFORDABLE FOR ALL TYPES OF VEHICLES INCLUDING SMALL UAS TO LARGE TRANSPORT CATEGORY AIRCRAFT. THE VEHICLES MUST BE TRACKED, AND IN COMMUNICATION, ALL THE WAY TO THE DOOR-STEP OR TO ANY ALTITUDE, ANYWHERE IN THE WORLD, BE ABLE TO SENSE OBSTACLES AT ALL ALTITUDES AND ACCURATELY NAVIGATE IN THE ABSENCE OF NAVIGATIONAL AIDS. | THE BOEING COMPANY | $1,008,239 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Aug 17, 2016 | Aug 17, 2016 | Mar 17, 2018 | ||
| IGF::OT::IGF POWER AND THERMAL ADVANCED DEMONSTRATION DESIGN (PTADD) - NEW TASK ORDER | THE BOEING COMPANY | $15,000,054 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC13NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; EXPERIMENTAL DEVELOPMENT | Mar 31, 2016 | Mar 31, 2016 | Sep 3, 2019 | ||
| IGF::OT::IGF HADES - "HYBRID APERTURE AERO-OPTICS FOR DIRECTED ENERGY SYSTEM" TASK ORDER | THE BOEING COMPANY | $1,069,065 | DEPT OF THE AIR FORCE | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Mar 16, 2016 | Mar 16, 2016 | Apr 30, 2018 | ||
| IGF::OT::IGF LOW COST ATTRITABLE AIRCRAFT DEVELOPMENT | THE BOEING COMPANY | $1,586,736 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Dec 17, 2015 | Dec 17, 2015 | Dec 23, 2016 | ||
| IGF::OT::IGF ADVANCED TANKER TECHNOLOGY, INTEGRATION, AND CONFIGURATION STUDY (ATTICS) | THE BOEING COMPANY | $283,274 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC11NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; BASIC RESEARCH | Dec 17, 2015 | Dec 17, 2015 | Jun 14, 2017 | ||
| 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 | THE BOEING COMPANY | $2,395,243 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 16, 2015 | Sep 16, 2015 | Oct 12, 2016 | ||
| IGF::OT::IGF INDUSTRY PERSPECTIVE ON NASA HYPERSONIC RESEARCH 1.0 INTRODUCTION/BACKGROUND:NASA IS REFINING ITS HYPERSONIC PORTFOLIO WITHIN NASAS AERONAUTICS RESEARCH MISSION DIRECTORATE (ARMD) TO ENSURE THAT IT IS MOST EFFECTIVELY ALIGNED TO SUPPORT NATIONAL PRIORITIES TO UTILIZE RESEARCH, COMPUTATIONAL TOOLS, AND EXPERIMENTAL CAPABILITIES IN SUPPORT OF TECHNOLOGY AND SYSTEM DEVELOPMENT AS WELL AS FLIGHT TEST IN SUPPORT OF NATIONAL NEEDS. OUR EXPECTATION IS THAT THESE INITIAL NATIONAL NEEDS ARE PRIMARILY DEFENSE RELATED. THIS TASK ORDER STUDY WILL ALLOW INDUSTRY A UNIQUE OPPORTUNITY TO PROVIDE INPUT INTO THE NATIONAL HYPERSONIC RESEARCH NEEDS FROM PURELY AN INDUSTRY PERSPECTIVE. NASA IS INTERESTED IN THE INDUSTRY VISION FOR MID-TERM (5-10 YEARS) AND LONG-TERM (10+ YEARS) ATMOSPHERIC HYPERSONIC FLIGHT AND RESPONSIVE SPACE ACCESS APPLICATIONS. IN PARTICULAR, NASA IS INTERESTED IN INDUSTRY VISIONS FOR 1) NEW HYPERSONIC PROPULSION AND VEHICLE TECHNOLOGIES, 2) TECHNOLOGY GAPS WHICH COULD INCLUDE ENHANCEMENT/MODIFICATION OF EXISTING TECHNOLOGIES TO IMPROVE PERFORMANCE OR DURABILITY, 3) ANALYTICAL/DESIGN TOOLS TO BRING NEW CAPABILITIES AND IMPROVEMENTS TO EXISTING TOOLS, 4) CAPABILITY IMPROVEMENTS TO EXISTING FACILITIES AND (IF NECESSARY) REQUIREMENTS FOR NEW NATIONAL FACILITIES, AND 5) AFFORDABLE FLIGHT DEMONSTRATIONS. FURTHERMORE, NASA IS INTERESTED TO LEARN TOPIC AREAS IN WHICH NASA SHOULD CONDUCT INDEPENDENT RESEARCH AND CAPABILITIES ENHANCEMENT FOR INDUSTRY PURPOSES AS WELL AS TO DEFINE OPPORTUNITIES FOR COLLABORATIVE WORK.2.0 SCOPE&OBJECTIVES: 2.1. THE SCOPE OF THIS TASK ORDER IS TO CONDUCT A STUDY AND WRITTEN ASSESSMENT ON ADVANCED TECHNOLOGIES FOR HYPERSONIC AIRBREATHING PROPULSION SYSTEMS FOR AEROSPACE VEHICLES.2.2. THE OBJECTIVES OF THIS TASK ORDER ARE TO: 1.ASSESS ANALYTICAL COMPETENCIES AND TECHNICAL GAPS WITHIN INDUSTRY. 2.RESERVED.3.IDENTIFY COLLABORATION APPROACHES BETWEEN INDUSTRY PARTNERS AND NASA. 4. RESERVED. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS | THE BOEING COMPANY | $232,084 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 1, 2015 | Sep 1, 2015 | Feb 29, 2016 | ||
| IGF::OT::IGF TASK: AIR TRAFFIC MANAGEMENT TECHNOLOGY DEMONSTRATION 1 (ATD-1)AVIONICS, PHASE 2 THIS SOW AIMS TO DEVELOP A RETROFIT FIM AVIONICS SOLUTION INTENDED TO FACILITATE INTERVAL MANAGEMENT (IM) OPERATIONS IN THE NEAR TERM NAS. THE CONTRACTOR SHALL BE RESPONSIBLE FOR DEVELOPING AND TESTING THE FIM AVIONICS SYSTEM. THE CONTRACTOR SHALL ALSO BE REQUIRED TO SUPPORT THE INTEGRATION OF THE FIM AVIONICS SYSTEM IN AN ACTUAL FLIGHT DECK. THE CONTRACTOR SHALL ALSO IDENTIFY AND SECURE TEST AIRCRAFT TO BE USED FOR A FLIGHT TEST TO DEMONSTRATE THE SYSTEM OPERATING IN THE FIELD.AS STATED IN THE INTRODUCTION, THE FUTURE PHASE-2 ATD-1 FLIGHT TRIALS ARE EXPECTED TO INCLUDE MULTIPLE HETEROGENEOUS AIRCRAFT. SINCE THE AVAILABILITY OF SPECIFIC AIRCRAFT IS UNKNOWN AT THIS TIME, THIS TASK ENDEAVORS TO CREATE A SYSTEM THAT CAN BE ADAPTED TO FUNCTION IN FLIGHT DECKS FROM MULTIPLE MANUFACTURERS. FURTHER, TO FACILITATE REQUIRED SURVEILLANCE PROCESSING FUNCTIONS, THE SYSTEM WILL INCLUDE A TCAS TRAFFIC PROCESSOR UNIT (TPU) COMMONLY FOUND ON TODAY S COMMERCIAL TRANSPORT CATEGORY AIRCRAFT. FIGURE 3.1 ILLUSTRATES THE FIM AVIONICS ARCHITECTURE EXPLORED IN THE PHASE-1 WORK THAT WILL SERVE AS THE BASIS FOR THE SYSTEM DEFINED IN THIS SOW. THE ARCHITECTURE EMPLOYS AN ARINC 735B COMPLIANT TPU TO COLLECT TRAFFIC STATE DATA VIA ADS-B MESSAGES AND OWNSHIP STATE DATA FROM ON-BOARD SENSORS. THE TPU WILL ADOPT SURVEILLANCE PROCESSING AND BASIC AIRBORNE SITUATION AWARENESS (AIRB) STANDARDS AND PERFORM SURVEILLANCE PROCESSING FUNCTIONS AS DEFINED IN DOCUMENT ORDER (DO)-317B. TRAFFIC FILES AND RAW STATE DATA ARE PASSED TO AN ELECTRONIC FLIGHT BAG (EFB), WHICH HOSTS THE FIM APPLICATION. THE EFB ALSO SERVES AS THE HUMAN MACHINE INTERFACE (HMI) FOR DATA ENTRY, OPERATION INFORMATION FEEDBACK, AND SITUATION AWARENESS REQUIRED FOR THE FIM APPLICATIONS, WHICH IS ASSUMED TO BE SATISFIED BY DO-317B AIRB STANDARDS THAT DRIVE REQUIREMENTS FOR COCKPIT DISPLAY OF TRAFFIC INFORMATION (CDTI) SCREENS. IN ADDITION TO THE FIM APPLICATION, THE HMI/CDTI CAN ALSO HOST AN ARINC 424 COMPATIBLE DATABASE (PER THE ATD-1 FIM SRD, GFI ITEM 5.13, THE REQUIREMENT IS FOR THE FIM APPLICATION TO HAVE ACCESS TO A NAVIGATION DATABASE CONSISTENT WITH ARINC 424 STANDARDS. IT IS LEFT TO THE CONTRACTOR TO DETERMINE WHERE THE DATABASE RESIDES.). THE ARINC 424 COMPATIBLE DATABASE SHALL HAVE THE SAME RELEASE DATE AS THE AIRCRAFT S FMS DATABASE, WHICH IS USED BY THE TRAJECTORY GENERATOR TO BUILD A 4-D PATH ON WHICH ASTAR BASES ITS CALCULATIONS. THERE ARE TWO HMI/CDTI S (ONE ON EACH SIDE OF THE COCKPIT) MOUNTED IN LOCATIONS ADEQUATELY ACCESSIBLE TO THE FLIGHT CREW TO CONDUCT FIM OPERATIONS. A CONFIGURABLE GRAPHICS DISPLAY (CGD) PROVIDES SPEED GUIDANCE AND PROGRESS INFORMATION. THERE ARE TWO CGDS, ONE ON EACH SIDE OF THE COCKPIT, IN THE CREW S PRIMARY FIELD OF VIEW (PFOV). A SINGLE CGD IS ACCEPTABLE IN SOME FLIGHT DECK IMPLEMENTATIONS IF THE INFORMATION IT CONTAINS IS EASILY VIEWABLE BY THE PILOT AND COPILOT. HOWEVER, THE FIM AVIONICS SYSTEM MUST BE DESIGNED TO ACCOMMODATE TWO CGDS. HOSTING THE FIM APPLICATION IN THE HMI/CDTI FACILITATES THE USE OF A COMMON SUBSET OF FIM HARDWARE (EFB AND CGD) ACROSS A NON-HOMOGENOUS FLEET OF AIRCRAFT. IF THE INTERFACE BETWEEN THE TPU AND HMI/CDTI CAN BE STANDARDIZED FOR THE NON-HOMOGENOUS FLEET OF AIRCRAFT, THE DEVELOPMENT VARIATIONS SHOULD BE LIMITED TO THE TPU TO MINIMIZE DEVELOPMENT COSTS. | THE BOEING COMPANY | $11,101,463 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Jun 5, 2015 | Jun 5, 2015 | Jun 29, 2017 | ||
| 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. | THE BOEING COMPANY | $6,331,686 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | May 21, 2015 | May 21, 2015 | Oct 12, 2016 | ||
| IGF::OT::IGF INNOVATIVE AIRCRAFT PROPULSION SYSTEM DEFINITION AND INTEGRATION STUDY - SMAAART (STRUCTURES MATERIALS, AERODYNAMICS, AEROTHERMODYNAMICS, AND ACOUSTICS RESEARCH&TECHNOLOGY) TASK ORDER STATEMENT OF WORK- 1.0 INTRODUCTION/BACKGROUND: ELECTRICALLY-POWERED AIRCRAFT WILL REVOLUTIONIZE THE WAY WE TRAVEL, BRINGING DRAMATIC INCREASES IN EFFICIENCY AND RELIABILITY, REDUCED EMISSIONS, AND REDUCED NOISE AS COMPARED TO TODAY S COMBUSTION-POWERED AIRCRAFT. THIS STUDY EFFORT WILL SUPPORT THE DESIGN OF A NOVEL FLIGHT DEMONSTRATION CONCEPT THAT WILL ENABLE THE BENEFITS OF ELECTRIC PROPULSION WHILE KEEPING THE CONVENIENCE AND UTILITY OF COMMON FUELS AVAILABLE AT TODAY S AIRPORTS. THE LARGEST DRAWBACK OF ELECTRICALLY-POWERED AIRCRAFT HAS BEEN THE ONBOARD ENERGY STORAGE SYSTEM NAMELY, ITS WEIGHT, COST, AND LOGISTICAL NEEDS. A PROMISING ENERGY STORAGE MECHANISM FOR ELECTRIC AIRCRAFT IS THE FUEL CELL. WITH ONGOING DEVELOPMENT, FUEL CELLS HAVE A GREAT POTENTIAL TO REPLACE INTERNAL COMBUSTION ENGINES (ICE) AS THEY OFFER HIGHER EFFICIENCIES AND LOWER EMISSIONS. OVERALL, THE USE OF A SOLID OXIDE FUEL CELL (SOFC)-ENABLED ELECTRIC PROPULSION ARCHITECTURE HAS THE MOST PROMISE TO ENABLE TRANSITION TO ELECTRIC PROPULSION. THE SOFC ENABLED ELECTRIC PROPULSION SYSTEM CAN REFORM TRADITIONAL FUELS INTO ELECTRICITY AT HIGH EFFICIENCY, THUS ADDING NO INFRASTRUCTURE COST OR UTILITY PENALTY THE AIRCRAFT CAN USE THE EXACT SAME AIRPORTS AND FUEL DEPOTS AS BEFORE. THE HIGH EFFICIENCY OF THE SOFC VS. THE ICE RESULTS IN LESS FUEL USAGE (AND THEREFORE LOWER OPERATING COSTS), AND IS DIRECTLY CORRELATED WITH LOWER CARBON EMISSIONS. IN ADDITION, THE REDUCTION IN TEMPERATURE OF THE SOFC REFORMER VS. ICE COMBUSTION LEADS TO ELIMINATION OF NITROGEN OXIDES FROM THE EXHAUST. THIS STUDY EFFORT COMPRISES A SOFC SYSTEM DESIGN AND INSTALLATION TO ENABLE AN INNOVATIVE ELECTRIC AIRCRAFT. THIS TASK ORDER IS A RESULT OF A COMPETITIVE SELECTION OF A 2015 AERONAUTICS RESEARCH MISSION DIRECTORATE (ARMD) SEEDLING PHASE I PROPOSAL THROUGH THE NASA AERONAUTICS RESEARCH INSTITUTE (NARI). 2.0 SCOPE&OBJECTIVE(S): 2.1 THE SCOPE OF THIS TASK ORDER IS TO DETERMINE THE FEASIBILITY OF MERGING A SOFC-ENABLED ELECTRIC PROPULSION ARCHITECTURE WITH AN EXISTING LIGHT AIRCRAFT DESIGN BY DEFINING A CANDIDATE POWER ARCHITECTURE WHILE QUANTIFYING PERFORMANCE, COST, AND RISK. THIS TASK ORDER WILL GENERATE CONCEPTUAL DESIGN DATA AND TEST PLANS FOR A SELECTED SOFC ARCHITECTURE AND SUPPORT THE VETTING OF THE SYSTEM REQUIREMENTS AND DESIGN THROUGH TWO COMPLETE DESIGN CYCLE ITERATIONS. 2.2 THE OBJECTIVES OF THIS TASK ORDER ARE TO: DEFINE THE DESIGN SPACE AND DEVELOP REQUIREMENTS FOR THE SOFC SYSTEM. PERFORM TRADE STUDIES AND IDENTIFY THE PREFERRED SOFC ARCHITECTURE CONCEPT. PERFORM ENGINEERING AND ANALYSIS TO DEVELOP A TECHNICAL DEFINITION OF THE PREFERRED SOFC SYSTEM SUPPORTING CONFIGURATION AND LAYOUT OF THE OVERALL AIR VEHICLE SYSTEM. CONDUCT PERFORMANCE, RISK, AND COST ANALYSES OF THE PREFERRED SOFC ARCHITECTURE CREATE A DEVELOPMENT ROADMAP AND DEFINE THE FOLLOW-ON SOFC SYSTEM DEVELOPMENT PHASE. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 SOFC SYSTEM SCALING STUDIES AND REQUIREMENTS DEVELOPMENT 3.1.1 THE CONTRACTOR SHALL CONDUCT SOFC SCALING STUDIES AND DEVELOP TOP-LEVEL SOFC DESIGN REQUIREMENTS BASED ON AN INITIAL SET OF SCALING STUDY PARAMETERS PROVIDED BY THE GOVERNMENT (GFI ITEM 5.1). THE RESULT OF THIS WORK SHALL BE A SCALING STUDY RESULTS AND INITIAL REQUIREMENTS DOCUMENT (DELIVERABLE ITEM | THE BOEING COMPANY | $351,451 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Apr 14, 2015 | Apr 14, 2015 | Sep 13, 2016 | ||
| IGF::OT::IGF BAA-RQKP-2013-0006 VERSATILE AFFORDABLE ADVANCED TURBINE ENGINE III&BEYOND TECHNOLOGY CONCEPTS | THE BOEING COMPANY | $317,556 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC11NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; BASIC RESEARCH | Mar 13, 2015 | Mar 13, 2015 | Feb 27, 2017 | ||
| IGF::OT::IGF WB-57F RE-ENGINE ASSESSMENT OPTIONS | THE BOEING COMPANY | $245,480 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Feb 25, 2015 | Feb 25, 2015 | Jan 25, 2016 | ||
| IGF::OT::IGF FUTURE AIR DOMINANCE ARCHITECTURE ASSESSMENT STUDY | THE BOEING COMPANY | $662,321 | DEFENSE CONTRACT MANAGEMENT AGENCY (DCMA) | DEPT OF THE AIR FORCE | — | 541712 | AC12NATIONAL DEFENSE R&D SERVICES; DEPARTMENT OF DEFENSE - MILITARY; APPLIED RESEARCH | Jan 13, 2015 | Jan 13, 2015 | Jul 13, 2016 | ||
| IGF::OT::IGF TASK TITLE: ASSESSMENT OF THE STATE OF THE ART OF PROGRESSIVE DAMAGE ANALYSIS 1.0 INTRODUCTION/BACKGROUND: THE NASA ADVANCED COMPOSITES PROJECT (ACP) SEEKS TO DEVELOP AND TRANSITION TECHNOLOGY THAT WILL ENABLE REDUCTION IN THE TIMELINE REQUIRED FOR DEVELOPMENT AND CERTIFICATION OF NEW AIRCRAFT STRUCTURES THAT UTILIZE ADVANCED COMPOSITE MATERIALS. HIGH FIDELITY ANALYSIS METHODS THAT CAN RELIABLY PREDICT THE ONSET OF DAMAGE AND DAMAGE PROGRESSION IN COMPOSITE MATERIALS CAN CONTRIBUTE TO THIS GOAL BY REPLACING SOME OF THE TESTING REQUIREMENTS IN THE BUILDING BLOCK APPROACH USED FOR THE DESIGN AND CERTIFICATION OF PRIMARY AIRCRAFT STRUCTURE. ADDITIONALLY, THESE ANALYSIS METHODS OFFER THE POTENTIAL FOR THE DEVELOPMENT OF MORE EFFICIENT STRUCTURAL CONCEPTS BY ENABLING THE EXPLORATION OF THE LARGE DESIGN SPACE OF LAMINATED COMPOSITES, WHICH IS NOT POSSIBLE WITH THE CURRENT LARGELY EMPIRICAL APPROACH FOR STRUCTURAL DESIGN AND SUBSTANTIATION. WITH THIS GOAL IN MIND, NASA IS SEEKING TO DEVELOP, OR MATURE, NEW OR IMPROVED, PHYSICALLY ACCURATE, VERIFIED AND VALIDATED, HIGH FIDELITY PROGRESSIVE DAMAGE ANALYSIS (PDA) TOOLS FOR QUASI-STATIC, DYNAMIC AND FATIGUE LOADING CONDITIONS. THESE HIGH FIDELITY TOOLS NEED TO BE COMPUTATIONALLY RIGOROUS, APPLICABLE TO STRUCTURAL LEVEL SIMULATIONS, AND CAPTURE NOT ONLY THE GLOBAL RESPONSE OF THE COMPONENT MODELED, BUT ALSO CAPTURE THE CORRECT FAILURE MODES AND INTERACTIONS, LOCATION, AND PROGRESSION OF DAMAGE AND THE ULTIMATE EFFECT OF DAMAGE PROGRESSION ON THE COMPONENT STRENGTH AND LIFE. THE NASA ACP IS FOCUSING ON THREE CASE STUDIES FOR DEVELOPMENT AND VALIDATION OF ANALYSIS TOOLS: (1) STATIC CASE STUDY: PREDICTIVE CAPABILITY FOR RESIDUAL DAMAGE TOLERANCE OF LOW-VELOCITY-IMPACT DAMAGED STRINGER-REINFORCED, POST-BUCKLED, THIN-SKIN COMPOSITE STRUCTURE; (2) FATIGUE CASE STUDY: PREDICTIVE CAPABILITY FOR FATIGUE LIFE OF DYNAMIC ROTOR COMPONENTS AND HIGHLY LOADED BOLTED JOINTS; AND (3) DYNAMIC CASE STUDY: PREDICTIVE CAPABILITY FOR CONTAINMENT OF ENGINE FAN BLADES SUBJECTED TO HIGH ENERGY IMPACTS. CASE STUDIES (1) AND (2) WILL USE A GRAPHITE EPOXY PRE-IMPREGNATED TAPE MATERIAL ARCHITECTURE AND CASE STUDY (3) WILL USE A DRY WOVEN RESIN-INFUSED MATERIAL ARCHITECTURE OR AND A GRAPHITE EPOXY PRE-IMPREGNATED TAPE MATERIAL. 2.0 SCOPE&OBJECTIVES: 2.1 THE SCOPE OF THIS TASK ORDER IS TO ASSESS THE STATE OF THE ART (SOA) IN PROGRESSIVE DAMAGE ANALYSIS METHODOLOGIES AND TOOLS FOR THE CASE STUDIES STATED ABOVE. OF PARTICULAR INTEREST TO NASA ARE THE DEVELOPMENTS REQUIRED TO ADVANCE THE DOWN-SELECTED METHODOLOGIES AND TOOLS TO A MATURITY LEVEL SUITABLE FOR INTEGRATION INTO AN AIRCRAFT CERTIFICATION PROCESS. 2.2 THE OBJECTIVES OF THIS TASK ORDER ARE TO: IDENTIFY THE MOST PROMISING PDA METHODOLOGIES AND TOOLS FOR PREDICTING DAMAGE FORMATION, GROWTH, ACCUMULATION AND THE EFFECT ON STRENGTH AND LIFE FOR PRACTICAL APPLICATION. IDENTIFY THE MATURITY OF THESE METHODOLOGIES AND TOOLS RELATIVE TO THEIR POTENTIAL TO BE CONSIDERED FOR USE IN A NEW PRODUCT CERTIFICATION EFFORT BY 2019 AND TO HAVE ACHIEVED A MATURITY LEVEL REQUIRED FOR AIRCRAFT CERTIFICATION BY 2024. RECOMMEND THE SUBSET OF METHODOLOGIES AND TOOLS MOST PROMISING FOR FURTHER INVESTMENT BY THE NASA ACP. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: 3.1 PDA METHODOLOGY AND TOOL ASSESSMENT THE CONTRACTOR SHALL PERFORM AN ASSESSMENT THAT SHALL: - INCLUDE A SUMMARY OF CANDIDATE PREDICTION METHODOLOGIES RELEVANT TO EACH CASE STUDY, AND RECOMMENDATIONS ON THE MOST PROMISING METHODOLOGIES TO BE POTENTIALLY CARRIED FORWARD BY THE ACP FOR THOROUGH QUANTITATIVE EVALUATION AND FOR FUTURE DEVELOPMENT. - ADDRESS THE THEORETICAL FOUNDATIONS OF THE METHODOLOGY, AS WELL AS THE POTENTIAL FOR PRACTICAL APPLICATION AT THE STRUCTURAL LEVEL, AND SHALL INCLUDE SUFFICIENT DATA ON CANDIDATE CODES TO ENABLE SELECTION OF ANALYSIS CODES FOR FUTURE EVALUAT | THE BOEING COMPANY | $529,343 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 29, 2014 | Sep 29, 2014 | Apr 28, 2015 | ||
| IGF::OT::IGF SMAAART TASK ORDER SOW - SLIT-TAPE BUCKLING AFP PROCESS CHARACTERIZATION. 1.0 INTRODUCTION AND BACKGROUND: AS PART OF THE ADVANCED COMPOSITES PROJECT (ACP), NASA IS PARTNERING WITH THE AEROSPACE INDUSTRY TO SIGNIFICANTLY REDUCE THE TIMELINE TO CERTIFY COMPOSITE STRUCTURE FOR COMMERCIAL AND MILITARY AERONAUTIC VEHICLES. THREE MAIN FOCUS AREAS, OR TECHNICAL CHALLENGES, HAVE BEEN IDENTIFIED BY NASA AND INDUSTRY AS HAVING MAJOR IMPACT ON THE CURRENT CERTIFICATION TIMELINE. THE ACP THIRD TECHNICAL CHALLENGE (TC3), MANUFACTURING PROCESS AND SIMULATION, IS CONCERNED WITH REDUCING THE OCCURRENCE OF DEFECTS WHICH COMMONLY OCCUR IN AEROSPACE COMPOSITE STRUCTURES AS A RESULT OF THE PROCESSING METHODS UTILIZED TO FABRICATE THESE LARGE, HIGHLY COMPLEX VEHICLES. ONE OF THE OBJECTIVES IN TC3 IS TO DEVELOP PHYSICS-BASED PROCESS MODELS WHICH ARE CAPABLE OF ACCURATELY PREDICTING THE FORMATION OF DEFECTS DURING ROBOTIC, AUTOMATED FIBER PLACEMENT (AFP) OF COMPOSITE STRUCTURE. WHILE THE EFFICIENCY DEMONSTRATED IN AFP HAS LED TO ITS ADOPTION BY THE AEROSPACE INDUSTRY FOR FABRICATION OF AIRCRAFT FUSELAGE, WING, AND ENGINE NACELLE PRIMARY COMPOSITE STRUCTURES, THE POTENTIAL ADVANTAGES HAVE NOT BEEN FULLY REALIZED DUE TO THE OCCURRENCE OF PERFORMANCE REDUCING DEFECTS WHICH RESULT IN COSTLY AND TIME-CONSUMING REWORK. THE DEVELOPMENT OF ACCURATE AFP PROCESS MODELS WILL GIVE AIRCRAFT MANUFACTURERS THE ABILITY TO PREDICT DEFECTS WHICH OCCUR DUE TO THE PHYSICAL RELATIONSHIP BETWEEN THE MATERIAL, THE PART TOOLING, AND THE AFP PROCESSING PARAMETERS. THIS SCIENCE-BASED APPROACH TO MAXIMIZING PART QUALITY HAS PROVEN SUCCESSFUL IN OTHER COMPOSITE PROCESSING METHODOLOGIES SUCH AS INFUSION FLOW PREDICTION AND CURE PROCESS DEFECTS SUCH AS RESIDUAL STRESS. HOWEVER, CURRENTLY NO VALIDATED PHYSICS-BASED PROCESS MODEL EXISTS TO PREDICT DEFECTS SUCH AS FIBER / TAPE BUCKLING, ALSO REFERRED TO AS FIBER WAVINESS, WRINKLING, PUCKERING, OR WINDOW-SHADING. AN AFP PROCESS MODEL WHICH ACCURATELY PREDICTS PROCESS DEFECTS WILL SIGNIFICANTLY REDUCE THE TRIAL AND ERROR FABRICATION EFFORT REQUIRED TO MEET PRODUCTION CERTIFICATION OF AEROSPACE COMPOSITE STRUCTURE. THE WORK DESCRIBED IN THIS SOW IS INTENDED TO ADDRESS FABRICATION ISSUES THAT HAVE A NEGATIVE IMPACT ON THE TIMELINE REQUIRED TO CERTIFY COMPOSITE STRUCTURES. THE INTENTION OF THIS TASK ORDER IS TO CHARACTERIZE THE AFP PROCESS PARAMETERS DURING THE FABRICATION OF PARTS WHICH IN THE PAST HAVE BEEN DEMONSTRATED TO CONTAIN DEFECTS SUCH AS WRINKLING OR PUCKERING. THE GOVERNMENT WILL UTILIZE A WELL CHARACTERIZED AEROSPACE TOUGHENED EPOXY MATERIAL, HEXCEL IM7 / 8552-1 PREPREG, SO THAT THE CHARACTERIZATION STUDY IS FOCUSED ON THE AFP PLACEMENT PARAMETERS WHICH AFFECT THE FORMATION OF THE WRINKLING / PUCKERING DEFECTS. THESE PROCESSING PARAMETERS, FOR EXAMPLE, INCLUDE BUT ARE NOT LIMITED TO: PLACEMENT SPEED, COMPACTION LOAD, MATERIAL TEMPERATURE, AND/OR HEAD TURNING RADIUS. THE GEOMETRY USED TO EVALUATE THE VARIOUS AFP PROCESSING PARAMETERS WILL BE LIMITED TO THE TYPE AND FORM WHICH HAS BEEN DEMONSTRATED IN PREVIOUS BUILDS BY THE FABRICATOR TO RESULT IN FORMATION OF THE WRINKLING / PUCKERING DEFECTS. THE RESULTS OF THIS AFP PROCESSING CHARACTERIZATION EFFORT WILL BE UTILIZED IN THE FUTURE DEVELOPMENT OF AN AFP PHYSICS-BASED PROCESS MODEL TO PREDICT THESE TYPES OF DEFECTS. 2.0 SCOPE&OBJECTIVE(S): 2.1 THE SCOPE OF THIS TASK ORDER IS TO FABRICATE COMPOSITE PANELS USING THE AFP PROCESS AND CHARACTERIZE THE AFP PROCESS BY MEASURING THE PROCESSING PARAMETERS WHICH RESULT IN FIBER / TAPE BUCKLING DEFECTS (WRINKLING / PUCKERING). 2.2 THE OBJECTIVES OF THIS TASK ORDER ARE TO: A. DETERMINE AFP PLACEMENT PARAMETERS AND PLACEMENT PARAMETER INTERACTIONS WHICH INFLUENCE THE FORMATION AND MAGNITUDE OF WRINKLING / PUCKERING DEFECTS FOR THE FIXED PART GEOMETRY FABRICATED USING 0.25 WIDE HEXCEL IM7 / 8552-1 SLIT-TAPE PREPREG. B. EMPIRICALLY CHARACTERIZE THE AFP PROCESSING PARAMETERS AND QUANTIFY | THE BOEING COMPANY | $499,299 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 22, 2014 | Sep 22, 2014 | Mar 31, 2016 | ||
| IGF::OT::IGF SMAAART TASK ORDER SOW - REFINED AFC-ENABLED HIGH-LIFT SYSTEM INTEGRATION STUDY 1.0 INTRODUCTION/BACKGROUND: THE NASA FIXED WING (FW) PROJECT IS SEEKING TO DEMONSTRATE THE POTENTIAL BENEFITS OF REDUCING COMPLEXITIES ASSOCIATED WITH A MODERN HIGH-LIFT SYSTEM FOR LOW-SPEED FLIGHT CONDITIONS REPRESENTATIVE OF TAKEOFF AND LANDING WITHOUT SACRIFICING AERODYNAMIC OR ACOUSTIC PERFORMANCE. ONE PROMISING APPROACH IS TO USE ACTIVE FLOW CONTROL (AFC) TO PROVIDE THE REQUIRED HIGH-LIFT PERFORMANCE WHILE REDUCING THE SYSTEM PART COUNT AND ASSOCIATED EXTERNAL DRAG. NASA IS SEEKING TO EXPLORE AND EVALUATE AFC-ENABLED HIGH-LIFT SYSTEMS WITHIN THE FRAMEWORK OF THE FW PROJECT GOALS REGARDING NOISE AND FUEL BURN REDUCTIONS OF A MODERN CIVIL TRANSPORT AIRCRAFT. MODERN HIGH-LIFT SYSTEMS ARE DESIGNED TO ALLOW A TRANSPORT AIRCRAFT WITH TYPICAL TRANSONIC CRUISE SPEEDS TO SAFELY OPERATE AT SLOW SPEEDS FOR LANDING AND TAKEOFF OPERATIONS. THE HIGH-LIFT SYSTEM IS USUALLY SLOTTED BOTH ON THE LEADING EDGE AND THE TRAILING EDGE OF THE WING TO TAKE ADVANTAGE OF THE AERODYNAMIC PROPERTIES OF SLOTTED FLOWS AND ACHIEVE THE NECESSARY HIGH LIFT PERFORMANCE. THE SLOTTED LEADING AND TRAILING EDGE DEVICES, AND THE ASSOCIATED SUB-SYSTEMS NECESSARY TO CHANGE THE WING CONFIGURATION FROM CRUISE TO LOW-SPEED, ARE COMPLEX AND EMPLOY A SIGNIFICANT NUMBER OF PARTS TO ENABLE SAFE OPERATION. IN ADDITION, THESE COMPLEX MECHANICAL HIGH-LIFT SYSTEMS OFTEN PROTRUDE EXTERNALLY UNDER THE WINGS AND REQUIRE EXTERNAL FAIRINGS THAT RESULT IN INCREASED CRUISE DRAG. THIS TASK ORDER BUILDS UPON WORK COMPLETED UNDER CONTRACT/TASK ORDER NNL10AA05B/ NNL13AB65T) ENTITLED AFC-ENABLED HIGH-LIFT SYSTEM INTEGRATION STUDY, WHERE A SYSTEMS BENEFIT STUDY WAS PERFORMED ON THREE CANDIDATE AFC-ENABLED SIMPLIFIED HIGH-LIFT SYSTEMS FOR MODERN CIVIL TRANSPORTS. FOR THIS TASK ORDER, A REFINED CONVENTIONAL HIGH-LIFT SYSTEM BASED ON THE NASA COMMON RESEARCH MODEL (CRM) WILL BE USED AS THE BASELINE FOR COMPARISON PURPOSE. THIS UPDATED BASELINE WILL HAVE IMPROVED STALL CHARACTERISTICS FOR LANDING, ACCEPTABLE LIFT/DRAG (L/D) PERFORMANCE FOR TAKEOFF, AND INTEGRATED NACELLE/PYLON IN ADDITION TO THE WING-ONLY OPTION DEVELOPED UNDER SMAAART TASK ORDER # NNL13AB65T. 2.0 SCOPE&OBJECTIVE(S): 2.1 THE SCOPE OF THIS TASK ORDER IS TO EXPLORE NEW DESIGN SPACE IN ORDER TO CLOSE THE TECHNOLOGY GAP IDENTIFIED FOR THE MASS FLOW REQUIREMENT AS APPLIED TO A REFINED AFC-ENABLED HIGH-LIFT SYSTEM. 2.2 THE OBJECTIVE(S) OF THIS TASK ORDER ARE TO: USE REFINED COMPUTATIONAL FLUID DYNAMICS (CFD)-BASED ANALYSIS TO CLOSE THE CRITICAL TECHNOLOGY GAP IDENTIFIED FOR THE MASS FLOW AND PRESSURE REQUIREMENTS. PERFORM SYSTEM-LEVEL TRADE STUDY TO DETERMINE WHETHER AFC YIELDS A CLOSED DESIGN. IDENTIFY TECHNICAL CHALLENGES ASSOCIATED WITH THE INTEGRATION OF AN AFC SYSTEM. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 REFINE CONVENTIONAL BASELINE HIGH-LIFT CONFIGURATION 3.1.1 USING THE NASA CRM GEOMETRY AS A STARTING POINT, THE CONTRACTOR SHALL DELIVER A DRAFT REFINED BASELINE CONVENTIONAL HIGH-LIFT DESIGN FOR TECHNICAL POINT OF CONTACT (TECH POC) FOR APPROVAL. (DELIVERABLE ITEM 4.3). THE TECH POC WILL PROVIDE WRITTEN APPROVAL VIA EMAIL TO THE CONTRACTOR WITH A COPY TO THE CONTRACTING OFFICER WITHIN 7 CALENDAR DAYS OF RECEIPT. THIS REFINED BASELINE CONVENTIONAL HIGH-LIFT CONFIGURATION SHALL BE REPRESENTATIVE OF A MODERN IN-SERVICE COMMERCIAL TRANSPORT AIRCRAFT. THIS INCLUDES HIGH LIFT STALL CHARACTERISTICS REPRESENTATIVE OF CURRENT PRODUCTION TRANSONIC TRANSPORT AIRCRAFT, AND A NACELLE/PYLON/WING INTEGRATION THAT AVOIDS HAVING SEPARATED FLOW OVER THE NACELLE ADVERSELY IMPACTING THE CRM HIGH-LIFT PERFORMANCE. 3.1.2 THE CONTRACTOR SHALL DELIVER THE FINAL REFINED BASELINE GEOMETRY FOR THE CONVENTIONAL HIGH LIFT SYSTEM AS INITIAL GRAPHICS EXCHANGE SPECIFICATION (IGES) FIL | THE BOEING COMPANY | $439,921 | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | NATIONAL AERONAUTICS AND SPACE ADMINISTRATION | — | 541712 | AR11SPACE R&D SERVICES; SPACE FLIGHT, RESEARCH AND SUPPORTING ACTIVITIES; BASIC RESEARCH | Sep 19, 2014 | Sep 19, 2014 | Jan 29, 2016 |