NATIONAL INSTITUTE OF AEROSPACE ASSOCIATES

NOIS3-TO-001 CONTINUING NASA'S PROBLEM SOLVING VIA THE REVOLUTIONARY AEROSPACE CONCEPTS - ACADEMIC LINKAGE (RASC-AL) CHALLENGE

GATEWAY TO BLUE SKIES COMPETITION

NOIS3-TO-001 CONTINUING NASA'S PROBLEM SOLVING VIA THE REVOLUTIONARY AEROSPACE CONCEPTS - ACADEMIC LINKAGE (RASC-AL) CHALLENGE

NOIS3-005 HUMAN LANDING SYSTEM COMPETITION (HLSC)

NOIS3-TO-001 CONTINUING NASA'S PROBLEM SOLVING VIA THE REVOLUTIONARY AEROSPACE CONCEPTS - ACADEMIC LINKAGE (RASC-AL) CHALLENGE

CAPABILITIES BROCHURE INCLUDING INTRODUCTION TO YOUR COMPANY, SERVICES PROVIDED RELATING TO NOIS3, AND CROWD SIZE. INFORMATION FOR SALESFORCE INCLUDING POINT OF CONTACT FIRST NAME, LAST NAME, AND EMAIL ADDRESS, GOOGLE-AFFILIATED EMAIL ADDRESS.

SUPPORT FOR RADIATION PROTECTION GROUND TESTS: THE PRIMARY OBJECTIVE OF THIS WORK IS THE PLANNING AND EXECUTION OF HUMAN PERFORMANCE AND USABILITY EVALUATIONS OF RADIATION PROTECTION CONCEPTS. A VARIETY OF GARMENTS, BLANKETS, AND SLEEPING BAGS HAVE

ANALYSIS OF SATELLITE AND IN SITU OBSERVATIONS OF THE ASIAN TROPOPAUSE AEROSOL LAYER (ATAL). THE ASIAN TROPOPAUSE AEROSOL LAYER IS AN ENHANCEMENT OF AEROSOLS IN THE UPPER TROPOSPHERE AND LOWER STRATOSPHERE (UTLS) ASSOCIATED WITH DEEP CONVECTION OF BOUNDARY-LAYER POLLUTION DURING THE ASIAN SUMMER MONSOON. THE PRESENCE OF ATAL HAS IMPORTANT IMPLICATIONS FOR CLOUD FORMATION, PRECIPITATION, UTLS CHEMISTRY, AND REGIONAL CLIMATE. THE PURPOSE OF THE PROPOSED RESEARCH IS TO USE OBSERVATIONAL DATA FROM SATELLITES, BALLOONS AND AIRCRAFT TO ILLUMINATE THE OPTICAL PROPERTIES, COMPOSITION, AND POTENTIAL IMPACTS OF THE ATAL ON THE UTLS REGION. FUTURE WORK MAY INCLUDE ADDITIONAL DEPLOYMENTS TO INDIA OR OTHER COUNTRIES TO MEASURE AND ANALYZE AEROSOL LEVELS IN THE UTLS, OR TO OTHER DOMESTIC OR INTERNATIONAL LOCATIONS IN RESPONSE TO VOLCANIC ERUPTIONS TO STUDY THE PHYSICAL AND CHEMICAL PROPERTIES OF VOLCANIC PLUMES.

SUPPORT THE X-57 PROJECT OFFICE ON MANAGEMENT OF STANDARDS DEVELOPMENT. THE OBJECTIVE OF THIS STATEMENT OF WORK IS TO PROVIDE THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (NASA) X-57 PROJECT OFFICE WITH SUPPORT ON PROJECT-RELATED TECHNOLOGY TRANSFER ASSOCIATED WITH CERTIFICATION AND REGULATIONS UNDER TITLE 14 OF THE CODE OF FEDERAL REGULATIONS (CFR) COVERING THE AIRWORTHINESS STANDARDS FOR NORMAL CATEGORY AIRPLANES (PART 23), AIRCRAFT ENGINES (PART 33), AND PROPELLERS (PART 35), AS WELL AS THE ASSOCIATED MEANS OF COMPLIANCE TO THOSE REGULATIONS, BEING DEVELOPED BY THE ASTM COMMITTEE F44 ON GENERAL AVIATION AIRCRAFT1 AND COMMITTEE F39 ON AIRCRAFT SYSTEMS2, WITH A SPECIAL FOCUS ON SUBCOMMITTEE F39.05 ON DESIGN, ALTERATION, AND CERTIFICATION OF ELECTRIC PROPULSION SYSTEMS. WHILE TECHNOLOGY TRANSFER IS A WELL-UNDERSTOOD PROCESS WHERE THE PROCESS OF DEMONSTRATING TECHNOLOGY IN RELEVANT ENVIRONMENTS HAS WELL-ESTABLISHED METHODS, THE ADDED COMPLEXITY OF ENSURING THAT THE TECHNOLOGY TRANSFER IS MADE MORE LITERATE IN A CERTIFICATION AND-OR REGULATORY ENVIRONMENT REQUIRES SPECIAL ATTENTION. AT ONE LEVEL, THE CERTIFICATION AND-OR REGULATORY PRACTICES CAN BE USED TO FORM THE VERY DEFINITION OF THE RELEVANT ENVIRONMENT. HOWEVER, AN UNDISCIPLINED APPLICATION OF CERTIFICATION AND-OR REGULATORY PRACTICES CAN UNNECESSARILY CONSTRAIN THE TECHNOLOGY MATURATION PROCESS, AND EFFECTIVELY STUNT THE TECHNOLOGY DEMONSTRATION. THEREFORE, A KNOWLEDGEABLE AND SCRUPULOUS REVIEW OF TECHNOLOGY TRANSFER ISSUES ASSOCIATED WITH CERTIFICATION AND REGULATION EARLY IN THE PROJECT LIFE-CYCLE PROVIDES A MEANS BY WHICH THE TECHNOLOGY CAN DEMONSTRATE ITS FUNCTION IN A RELEVANT ENVIRONMENT, AS WELL AS INFORM THE RELEVANT ENVIRONMENT TO THE POTENTIAL BENEFITS OF THE TECHNOLOGY.

AIRCRAFT LOSS OF CONTROL (LOC) RESEARCH SUPPORT: ACCIDENT ANALYSIS&TEST SCENARIOS DEVELOPMENT 2. PURPOSE, OBJECTIVE, AND BACKGROUND OF WORK TO BE PERFORMED: THE PURPOSE OF THIS TASK IS TO PROVIDE RESEARCH AND DEVELOPMENT SUPPORT, TECHNICAL AND SUBJECT MATTER EXPERTISE, AND SUBJECT MATTER ENGINEERING CONSULTATION TO NASA'S VEHICLE SYSTEMS SAFETY TECHNOLOGIES (VSST) PROJECT TO CONDUCT RESEARCH THAT SUPPORTS RESEARCH ON AIRCRAFT LOSS OF CONTROL (LOC) PREVENTION AND RECOVERY. THE CONTRACTOR SHALL PARTICIPATE IN LOC ACCIDENT ANALYSES, LOC TEST SCENARIOS DEVELOPMENT, EXPERIMENT DESIGN, PILOTED EVALUATIONS OF NASA TECHNOLOGIES, PUBLICATION AND DISSEMINATION OF RESEARCH RESULTS, AND OPERATIONS CONSULTING (INCLUDING FLIGHT CREW AND AIR TRAFFIC CONTROL OPERATIONS). 3. DESCRIPTION OF THE WORK TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASK REQUIREMENTS: 3.1. WORKING WITH THE NATIONAL TRANSPORTATION SAFETY BOARD (NTSB) AND NASA, THE CONTRACTOR SHALL UPDATE AND REFINE A DATABASE OF AIRCRAFT ACCIDENTS RELATED TO VEHICLE UPSETS AND LOSS OF CONTROL OVER A RECENT 15-YEAR TIME PERIOD. THESE ACCIDENTS SHALL COMPRISE CIVIL ACCIDENTS AND INCIDENTS FROM AVAILABLE PUBLIC RECORDS AND SHALL INCLUDE CORPORATE AS WELL AS AIRLINE OPERATIONS. 3.2. UTILIZING THE DATABASE DEVELOPED UNDER TASK 3.1, THE CONTRACTOR SHALL PERFORM A STATISTICAL ANALYSIS OF INDIVIDUAL ACCIDENT PRECURSORS TO LOC. INDIVIDUAL PRECURSORS SHALL INCLUDE (BUT ARE NOT LIMITED TO): FLIGHT CONTROL SYSTEM AND COMPONENT FAILURES AND MALFUNCTIONS, ATMOSPHERIC DISTURBANCES, CREW ERRORS, VEHICLE IMPAIRMENT AND UPSET CONDITIONS. 3.3. THE CONTRACTOR SHALL PARTICIPATE IN AND/OR PROVIDE CONSULTATION FOR FURTHER ACCIDENT ANALYSES PERFORMED BY NASA TO IDENTIFY PRECURSOR COMBINATIONS AND SEQUENCES. 3.4. THE CONTRACTOR SHALL ASSIST NASA IN THE DEVELOPMENT OF A COMPREHENSIVE SET OF LOC TEST SCENARIOS THAT CAN BE TRACED TO THE ACCIDENT SET AND ANALYSIS AND USED IN THE EVALUATION OF LOC PREVENTION AND RECOVERY

"SIMULATION DEVELOPMENT AND HANDLING QUALITIES ANALYSIS OF LOW-BOOM FLIGHT DEMONSTRATOR (LBFD) DESIGNS" THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASK REQUIREMENTS:3.1. SIMULATION DEVELOPMENT - THE CONTRACTOR SHALL WORK WITH NASA AND UTILIZE MATH MODELS PROVIDED BY THE PROJECT TEAM TO DEVELOP A HIGH FIDELITY SIX DEGREE-OF-FREEDOM SIMULATION CAPABLE OF ACCURATELY MODELING THE FLIGHT DYNAMICS OF THE LBFD DESIGNS. THIS WILL INCLUDE EXPERIMENTING WITH AND DEVELOPING NEW SIMULATION AND MODELING TECHNIQUES TO MORE ACCURATELY MODEL THE EFFECTS OF AEROELASTICITY ON THE DYNAMIC FLIGHT RESPONSE OF LONG SLENDER VEHICLE DESIGNS.3.2.STABILITY AND CONTROL ANALYSIS - THE CONTRACTOR SHALL WORK WITH NASA TO PROVIDE AN EVALUATION OF VEHICLE STABILITY AND CONTROL CHARACTERISTICS AND VEHICLE FLIGHT DYNAMICS USING THE SIMULATION TOOLS DEVELOPED. RESULTS WILL BE COMPARED AGAINST VEHICLE REQUIREMENTS AND ANY AREAS OF CONCERN SHALL BE IDENTIFIED AND POTENTIAL SOLUTIONS PROPOSED. RESULTS WILL BE PRESENTED AND DISCUSSED AT PROJECT MEETINGS AND REVIEWS AS WELL AS DOCUMENTED IN QUARTERLY REPORTS.3.3.TEST SUPPORT AND MODEL DEVELOPMENT THE CONTRACTOR MAY PROVIDE SUPPORT, AS NECESSARY, OF DEVELOPMENTAL TESTS (I.E. WIND TUNNEL, STRUCTURAL DYNAMICS, ETC.) THAT ARE RELEVANT TO THE DEVELOPMENT OF THE SIMULATION MATH MODELS USED TO SIMULATE VEHICLE DYNAMICS. THE CONTRACTOR MAY ALSO BE ASKED TO PROVIDE FEEDBACK AND GUIDANCE CONCERNING THE FORMAT AND CONTENT OF THE MATH MODELS UNDER DEVELOPMENT.3.4.FLIGHT CONTROLS DEVELOPMENT THE CONTRACTOR SHALL EXPERIMENT WITH VARIOUS CONTROL METHODOLOGIES TO PROVIDE VEHICLE STABILITY AUGMENTATION AND STRUCTURAL MODE CONTROL AS NEEDED TO MEET THE STABILITY AND CONTROL REQUIREMENTS AND IMPROVE VEHICLE HANDLING QUALITIES. THIS MAY INCLUDE DEVELOPMENT OF NOVEL APPROACHES OR CONTROL DESIGN TECHNIQUES.

TRADE STUDY, MODELING, AND ANALYSIS OF ROBOTIC DOCKING AND BERTHING AT THE LUNAR ORBITAL PLATFORM-GATEWAY. NASA SEEKS TO CONSTRUCT THE LUNAR ORBITAL PLATFORM-GATEWAY OVER A PERIOD STARTING FROM 2020 AND ENDING IN 2028. ALTHOUGH DESIGNED TO BE A MANNED SPACE STATION, IT IS EXPECTED THAT THE GATEWAY WILL BE UNOCCUPIED FOR LONG STRETCHES TOTALING OVER 90% OF ITS LIFESPAN. TASKS SUCH AS DOCKING, BERTHING, MAINTENANCE, AND OTHER MANIPULATION TASKS DURING THE UNOCCUPIED PHASES MUST BE PERFORMED BY ROBOTS. SINCE THE ROUND-TRIP COMMUNICATION TIME IS APPROXIMATELY 3 SECONDS, FULL TELEOPERATION IS NOT FEASIBLE, AND SOME DEGREE OF SUPERVISED AUTONOMY WILL BE REQUIRED. THE OBJECTIVES OF THIS WORK ARE TO: 1) PERFORM A STUDY INCLUDING THE MODELING AND ANALYSIS OF SENSING AND CONTROLS REQUIREMENTS TO ENABLE SUPERVISED AUTONOMOUS ROBOTS TO PERFORM DOCKING, BERTHING, AND MAINTENANCE OPERATIONS, AND 2) PERFORM A TRADE STUDY WHICH WILL ASSESS THE STATE OF THE ART IN PLANNED GATEWAY ROBOTS TO INFORM THE DESIGN OF NEW ROBOTIC TOOLS TO ASSIST IN DOCKING AND BERTHING.

OPERATIONS LIMITS FOR PASSENGER-CARRYING URBAN AIR MOBILITY MISSIONS.

RESEARCH AND ANALYSIS OF IN SITU AND ON-ORBIT OBSERVATIONS OF THE ASIAN TROPOPAUSE AEROSOL LAYER (BATAL - ATAL). THE ASIAN TROPOPAUSE AEROSOL LAYER (ATAL) IS AN ENHANCEMENT OF AEROSOLS IN THE UPPER TROPOSPHERE AND LOWER STRATOSPHERE (UTLS) ASSOCIATED WITH DEEP CONVECTION OF BOUNDARY-LAYER POLLUTION DURING THE ASIAN SUMMER MONSOON. THE PRESENCE OF ATAL HAS IMPORTANT IMPLICATIONS FOR CLOUD FORMATION, PRECIPITATION, UTLS CHEMISTRY, AND REGIONAL CLIMATE. A BALLOON MEASUREMENT CAMPAIGN OF THE ATAL (BATAL) IS A UNIQUE AND EFFECTIVE WAY TO VALIDATE SATELLITE OBSERVATIONS AND OBTAIN MORE INFORMATION ON THE PHYSICAL AND CHEMICAL PROPERTIES OF THE ATAL THROUGH BALLOON-BORNE INSTRUMENTS. UNDER FUNDING FROM THE NASA HEADQUARTERS EARTH SCIENCE DIVISION UPPER ATMOSPHERE RESEARCH PROGRAM (UARP) AND ATMOSPHERIC COMPOSITION MODELING AND ANALYSIS PROGRAM (ACMAP) RESEARCH&ANALYSIS PROGRAMS THIS TASK BUILDS UPON PRIOR WORK TO THE ACQUIRE, PROCESS, ANALYZE, INTERPRET AND DISSEMINATE OBSERVATIONAL DATA FROM SATELLITES, BALLOONS AND AIRCRAFT TO ILLUMINATE THE OPTICAL PROPERTIES, COMPOSITION, AND POTENTIAL IMPACTS OF THE ATAL ON THE UTLS REGION.

TD-FAST (TIME DOMAIN FAST ACOUSTIC SCATTERING TOOLKIT) APPLICATION AND ENHANCEMENT. ACCURATE AND EFFICIENT HIGH-FIDELITY NOISE PREDICTION TOOLS ARE CRITICAL TO THE DESIGN AND ASSESSMENT OF CONVENTIONAL AND UNCONVENTIONAL AIRCRAFT CONFIGURATIONS. THE PURPOSE OF THIS RESEARCH IS TO FURTHER DEVELOP, IMPLEMENT AND VALIDATE AN EFFICIENT HIGH-FIDELITY TIME DOMAIN ACOUSTIC SCATTERING PREDICTION TOOL THAT IS CAPABLE OF CONSIDERING A COMPLETE AIRCRAFT, COVERING A FULL FREQUENCY RANGE OF INTEREST WITHIN A SHORT TURN-AROUND TIME. TIME DOMAIN ACOUSTIC SCATTERING PREDICTION CAPABILITIES HAVE SOME DISTINCT ADVANTAGES OVER FREQUENCY DOMAIN APPROACHES. MOST NOTABLY, SCATTERING SOLUTIONS AT ALL FREQUENCIES ARE OBTAINED WITHIN ONE SINGLE COMPUTATION. IN ADDITION, BROADBAND NOISE SOURCES AND TIME DEPENDENT TRANSIENT SIGNALS CAN BE SIMULATED AND STUDIED. THE TIME DOMAIN APPROACH ALSO COUPLES NATURALLY WITH NONLINEAR COMPUTATIONS WHERE MANY FREQUENCIES ARE GENERATED. FINALLY, WITH RECENT ADVANCES IN MULTI-LEVEL ALGORITHMS, COMPUTATIONAL COMPLEXITY CAN BE GREATLY REDUCED, MAKING IT FEASIBLE FOR ROUTINE APPLICATION AT MID TO HIGH FREQUENCIES WITH REDUCED RESOURCE REQUIREMENTS. THIS TASK CONTINUES THE DEVELOPMENT OF THE TIME DOMAIN FAST ACOUSTIC SCATTERING TOOLKIT (TD-FAST) PREVIOUSLY DEVELOPED UNDER NIA TASK ORDER 80LARC18F0106.

HYPERSONIC, COMMERCIAL TRANSPORTATION FEASIBILITY STUDY. THIS STUDY WILL EXPLORE THE FEASIBILITY, PRACTICALITY, AND AFFORDABILITY OF COMMERCIAL HYPERSONIC TRANSPORTS AND TO USE THE RESULTS TO GUIDE FUTURE NASA HYPERSONIC RESEARCH INVESTMENTS.

U.S. DEMAND FOR A LOW-BOOM SUPERSONIC TRANSPORT AIRCRAFT. THIS TASK IS TO DETERMINE THE PASSENGER AND VEHICLE DEMAND FOR A LOW-BOOM SUPERSONIC TRANSPORT AIRCRAFT IN THE U.S. MARKET. A PREVIOUS TASK ORDER (NNL16AA36T) UNDER NASA/NIA CONTRACT NNL13AA08B EXAMINED THE GLOBAL MARKET FOR BOTH LOW-BOOM AND NON LOW-BOOM SUPERSONIC TRANSPORTS. THIS PREVIOUS STUDY IDENTIFIED TWO POTENTIALLY SEPARATE MARKETS FOR A SUPERSONIC TRANSPORT: A LONG RANGE (>2500 MI) MARKET FOR A NON LOW-BOOM SUPERSONIC TRANSPORT THAT HAS ROUTES PRIMARILY OVER OPEN WATER, AND AN INTERMEDIATE RANGE MARKET (BETWEEN 1,500 AND 2,500 MI) FOR A LOW-BOOM SUPERSONIC TRANSPORT THAT HAS ROUTES PRIMARILY OVER LAND. FOR THE LONG RANGE MARKETS, A LOW-BOOM SUPERSONIC TRANSPORT WOULD BE BURDENED BY THE WEIGHT AND PERFORMANCE PENALTIES ASSOCIATED WITH ITS LOW-BOOM DESIGN WITH LITTLE OR NO TRAVEL TIME BENEFIT COMPARED TO A NON LOW-BOOM AIRCRAFT, MAKING IT MUCH LESS COMPETITIVE. FOR THE INTERMEDIATE RANGE MARKETS, A LOW-BOOM SUPERSONIC TRANSPORT WOULD HAVE A CLEAR TRAVEL TIME ADVANTAGE OVER A NON LOW-BOOM TRANSPORT ON MOST ROUTES DUE TO ITS ABILITY TO CRUISE SUPERSONICALLY OVER LAND. IN ADDITION, IF THE DESIGN RANGE OF THE LOW-BOOM TRANSPORT WAS DECREASED TO REFLECT THE INTERMEDIATE RANGE MARKETS (DECREASING THE TAKEOFF GROSS WEIGHT (TOGW)), IT IS POSSIBLE THAT THE CRUISE MACH NUMBER COULD BE INCREASED WITHOUT A SIGNIFICANT IMPACT ON THE BOOM SIGNATURE, PROVIDING EVEN MORE TRAVEL TIME SAVINGS. THE NEW STUDY WILL NARROW THE FOCUS TO LOW-BOOM SUPERSONIC TRANSPORTS OPERATING IN THE U.S., WHICH WILL PROVIDE A STRONG INDICATION OF THE VIABILITY OF AN INTERMEDIATE RANGE LOW-BOOM TRANSPORT. THE PROPOSED STUDY WILL ALSO EXAMINE THE POTENTIAL IMPACT OF OPERATING A SUPERSONIC TRANSPORT AIRCRAFT AT U.S. AIRPORTS AND IN U.S. AIRSPACE. THE NEW AIRCRAFT COULD POTENTIALLY IMPACT AIRPORT/AIRSPACE CAPACITY, AIRPORT INFRASTRUCTURE, AND COMMUNITY NOISE.

IMPACT OF AUTONOMOUS GROUND VEHICLES ON URBAN AIR MOBILITY OPERATIONS. OVER THE PAST FEW YEARS THE CONCEPT OF UTILIZING ADVANCED, SMALL AIRCRAFT FOR ON-DEMAND TRANSPORTATION AROUND METROPOLITAN AREAS HAS BEEN GROWING IN POPULARITY. SUCH NOVEL TRANSPORTATION SERVICES FOR BOTH PEOPLE AND GOODS HAS BECOME KNOWN AS URBAN AIR MOBILITY (UAM). ADVANCES IN ELECTRIC PROPULSION SYSTEMS, AUTOMATION/AUTONOMY, MANUFACTURING, AND OTHER TECHNOLOGIES MAY CONVERGE TO PROVIDE NOVEL AIRCRAFT CONFIGURATIONS THAT ARE AFFORDABLE, SAFE, AND QUIET ENOUGH TO OPERATE AS A PRACTICAL MEANS OF DAILY TRANSPORTATION. IN 2016, THE RIDE HAILING COMPANY UBER RELEASED A WHITE PAPER DESCRIBING ITS PLANS TO BEGIN OFFERING AN URBAN AIR MOBILITY (UAM) SERVICE WITH THE NOVEL ELECTRIC VERTICAL TAKEOFF AND LANDING (I.E., EVTOL) AIRCRAFT, AND SEVERAL MANUFACTURERS HAVE SINCE MADE PUBLIC THEIR PLANS OF DEVELOPING EVTOL AIRCRAFT TO OPERATE WITHIN SUCH A SYSTEM. THE UAM CONCEPT SHARES SOME SIMILARITIES WITH EXISTING PUBLIC TRANSIT SYSTEMS. SPECIFICALLY, MOST UAM CONCEPTS RELY ON PASSENGERS TO CHANGE MODES TO COMPLETE A SINGLE TRIP I.E., A TRAVELER WILL TAKE A GROUND VEHICLE OR WALK TO A TAKEOFF LOCATION, EXIT THE GROUND VEHICLE (IF REQUIRED), TRANSFER INTO AN AIR VEHICLE, THEN TRANSFER AGAIN AFTER A FLIGHT TO A GROUND-BASED TRANSPORTATION MODE. SUCH MULTI-MODE TRIPS ARE COMMON TODAY WITH TRANSIT SYSTEMS WITH THE AIR PORTION OF THE TRIP BEING REPLACED BY A GROUND-BASED MODE (OR MODES) USING BUSES AND/OR TRAINS. THEREFORE, THE LESSONS LEARNED FROM THE TRANSIT WORLD MAY BE DIRECTLY APPLICABLE TO UAM OPERATIONS, AND COULD HELP INCREASE PUBLIC ADOPTION OF UAM TRANSPORTATION. FOR EXAMPLE, TRANSIT RIDERS MAY PREFER TO HAVE SERVICES, SUCH AS THE DRY CLEANERS, CO-LOCATED WITH A TRANSIT STATION SO THAT THEY DO NOT NEED TO MAKE AN EXTRA TRIP. SUCH PREVIOUSLY EVIDENCED BEHAVIOR MAY IMPLY THAT UAM OPERATIONS SHOULD CONSIDER CO-LOCATING THESE SERVICES AT THE AIR VEHICLE TAKEOFF AND LANDING LOCATIONS. AT THE SAME TIME AS THE

DEVELOPMENT OF A MULTIPLE SAMPLING EXTENSION FOR A MIXED INTEGER EFFICIENT GLOBAL OPTIMIZATION (AMIEGO) MIXED INTEGER NONLINEAR PROGRAMMING ALGORITHM. A RECENTLY PUBLISHED ALGORITHM FOR MIXED INTEGER NONLINEAR PROGRAMMING, A MIXED INTEGER EFFICIENT GLOBAL OPTIMIZATION (AMIEGO), HAS SIGNIFICANTLY ADVANCED THE STATE OF THE ART FOR SOLVING OPTIMIZATION PROBLEMS WITH BOTH INTEGER AND CONTINUOUS DESIGN VARIABLES. THIS ALGORITHM CAN BENEFIT GREATLY FROM EXPLOITING GRADIENT BASED OPTIMIZATION WITH ANALYTIC DERIVATIVES FOR ITS INNER OPTIMIZATION ROUTINE. NASA S OPENMDAO FRAMEWORK SPECIALIZES IN GRADIENT BASED OPTIMIZATION WITH ANALYTIC DERIVATIVES, WHICH MAKES IT A NATURAL PLACE TO IMPLEMENT THE NEWLY CREATED AMIEGO ALGORITHM. THERE ARE A NUMBER OF INTERESTING MIXED INTEGER NONLINEAR PROGRAMMING PROBLEMS THAT ARE OF INTEREST TO NASA AERONAUTICS RESEARCH MISSION DIRECTORATE S (ARMD) TRANSFORMATIONAL TOOLS AND TECHNOLOGIES (TTT) PROJECT, INCLUDING THE SOLUTION TO A LARGE SCALE WING TOPOLOGY OPTIMIZATION OPTIMIZATION PROBLEM. THE GOAL OF THIS WORK IS TO IMPLEMENT THE AMIEGO ALGORITHM WITHIN OPENMDAO, USING A MULTIPLE SAMPLING BASED INFILL CRITERION AND THEN TO DEMONSTRATE THE ALGORITHM ON THE SOLUTION OF THE WING OPTIMIZATION PROBLEM.

SUBJECT MATTER EXPERTISE FOR AIRPLANE STATE AWARENESS RESEARCH STUDIES. PROVIDE RESEARCH AND DEVELOPMENT SUPPORT, TECHNICAL AND SUBJECT MATTER EXPERTISE, AND SUBJECT MATTER CONSULTATION TO RESEARCHERS IN SUPPORT OF AIRPLANE STATE AWARENESS AND AVIATION SAFETY RESEARCH ACTIVITIES. THE TASKING DEFINES THE CONDUCT OF RESEARCH, DEVELOPMENT, TEST, AND EVALUATION THAT SUPPORTS, BUT IS NOT LIMITED TO, THE TECHNOLOGIES FOR AIRPLANE STATE AWARENESS SUBPROJECT WITHIN THE SYSTEM-WIDE SAFETY PROJECT OF NASA AIRSPACE OPERATIONS AND SAFETY PROGRAM.

SYSTEMS ANALYSIS AND UNCERTAINTY ANALYSIS IN SUPPORT OF NASA PROGRAMS/PROJECTS: THE STATEMENT OF WORK FOCUSES ON TWO AREAS OF RESEARCH. ONE AREA OF FOCUS IS SYSTEMS ANALYSIS OF ADVANCED CONCEPTS THAT ARE BEING CONSIDERED UNDER NASA S AERONAUTICS RESEARCH MISSION DIRECTORATE (ARMD) PROGRAMS. THE OTHER AREA OF FOCUS IS UNCERTAINTY ANALYSIS AND RISK REDUCTION THROUGH VIRTUAL AND PHYSICAL EXPERIMENTAL PLANNING. NASA IS SEEKING TO UNDERSTAND THROUGH SYSTEM ANALYSIS THE POTENTIAL BENEFITS OF PROPOSED VISION SYSTEMS HOW THEY RELATE TO ESTABLISHED PROGRAM GOALS. NASA IS ALSO SEEKING TO UNDERSTAND THE POTENTIAL GAP THAT MAY EXIST BETWEEN THE VISION SYSTEM AND THE ESTABLISHED GOALS AND WHAT TECHNOLOGIES ARE NEEDED TO POTENTIALLY CLOSE THAT GAP. FURTHERMORE, NASA IS SEEKING A FORMALIZED METHOD TO REDUCE UNCERTAINTY AND ASSOCIATED RISK THROUGH A STRUCTURED EXPERIMENT DESIGN PROCESS THAT RESULTS IN MATURATION OF THE TECHNOLOGIES NEEDED TO CLOSE GAPS TO ACHIEVE PROGRAM GOALS. THE MAJOR OBJECTIVES FOR THE PROPOSED RESEARCH ARE LISTED BELOW. THE SPECIFIC TASKS DESCRIBED HEREIN CORRESPOND TO THESE OBJECTIVES: PERFORM SYSTEM ANALYSIS TO DETERMINE FUEL BURN, NOX EMISSIONS MARGIN, AND NOISE MARGIN FOR THE FOLLOWING VISION SYSTEMS: AURORA D8 BOEING TRANSONIC TRUSS-BRACED WING (TTBW) INDUSTRY-BASED HYBRID ELECTRIC TRANSPORT (HET) DYZNE REGIONAL BLENDED WING BODY (BWB) LOCKHEED BWB BOEING BWB DETERMINE MOST PROMISING SET OF TECHNOLOGIES TO BRIDGE THE GAP OF VISION SYSTEM TO ACHIEVE PROGRAM GOALS PERFORM UNCERTAINTY ANALYSIS FOR THE PURPOSE OF RISK REDUCTION FOR IDENTIFIED EXPERIMENTATION PROGRAMS THIS TASK IS RELATED TO WORK ORIGINALLY PERFORMED UNDER NIA TASK ORDER NNL17AA71T.

ADJUSTABLE GEOMETRY BLOWN SURFACE PROTOTYPE AND AIRCRAFT CONCEPTUAL DESIGN. DISTRIBUTED ELECTRIC PROPULSION (DEP) ENABLES A HIGH DEGREE OF COUPLING BETWEEN THE AERODYNAMICS AND PROPULSION CHARACTERISTICS OF AIRCRAFT WING SYSTEMS. TIGHT COUPLING OF THESE TWO DISCIPLINES OFFER OPPORTUNITIES TO IMPROVE THE PERFORMANCE AND ACHIEVE CAPABILITIES THAT CANNOT BE ACHIEVED WITH ISOLATED WING AND PROPULSION SOLUTIONS. HIGHER-ORDER ANALYSIS USING COMPUTATIONAL FLUID DYNAMICS (CFD) TOOLS WAS ACCOMPLISHED IN PREVIOUS WORK TO CAPTURE THESE HIGHLY COUPLED EFFECTS WITH ANALYSIS TOOLS THAT HAVE BEEN CALIBRATED TO VALIDATION DATASETS FROM PRIOR AERO-PROPULSIVE WIND TUNNEL TESTS. TESTING OF SPECIFIC DEP SYSTEMS IS DESIRED TO IMPROVE THE STATE OF THE ART TO ACHIEVE VERY HIGH LIFT AT LOW SPEEDS, AND AT STATIC CONDITIONS WHILE ENTRAINING FLOW TO MAXIMIZE THE SYSTEMS LIFTING CHARACTERISTICS. AT THE SAME TIME HIGH CRUISE EFFICIENCY IS DESIRED, ALONG WITH EXCELLENT CONTROL CHARACTERISTICS THROUGHOUT THE FLIGHT ENVELOPE. THIS RESEARCH WILL DEVELOP A BENCH TEST PROTOTYPE TO CHARACTERIZE A SPECIFIC DEP CONFIGURATION TO BETTER UNDERSTAND THE AERO-PROPULSIVE CHARACTERISTICS. PREVIOUSLY, A CENTRIFUGAL FAN SYSTEM WAS DESIGNED TO ENABLE A DISTRIBUTED BLOWING SYSTEM OVER SURFACES OF A VERTICAL TAKE-OFF AND LANDING (VTOL) CONCEPTUAL AIRCRAFT WITH AN ULTRA-LOW NOISE SIGNATURE. A LIFT SYSTEM WAS DESIGNED AND FOUND TO PERFORM WELL ACCORDING TO COMPUTATIONAL ANALYSIS. A FULL-SCALE SHORT SPAN PROTOTYPE SECTION OF THE LIFTING DEVICE IS DESIRED. THE PROTOTYPE SHALL HAVE AN ADJUSTABLE GEOMETRY SO THAT GEOMETRIC ITERATIONS CAN BE TESTED QUICKLY. A PLENUM WILL BE DESIGNED TO BE FABRICATED BY NASA LARC. A PORTABLE, HIGH MASS-FLOW AIR SOURCE WILL BE FABRICATED WITH PARTS MACHINED BY NASA LARC. A METHOD FOR MEASURING THE FORCES AND MOMENTS ACTING UPON THE PROTOTYPE SHALL BE DEVISED. AN AIRCRAFT CONCEPTUAL DESIGN SHALL BE CREATED USING THE COMPONENT PERFORMANCE AS CHARACTERIZED BY PREVIOUS COMPUTATIONAL ANALYSIS. C

INVESTIGATION OF SHORT TAKE-OFF AND LANDING (STOL) APPLICABILITY TO URBAN, SUBURBAN, AND RURAL AIR MOBILITY. RISING POPULATIONS IN AND AROUND CITIES WORLDWIDE ARE CAUSING SUBSTANTIAL MOBILITY ISSUES. THERE IS INCREASING GEOGRAPHICAL SPRAWL OF URBAN AREAS AND COMMUTE TIMES ARE EVER-RISING, BOTH DUE TO INCREASING COMMUTING DISTANCES AND INCREASING CONGESTION ON ROADS AND PUBLIC TRANSIT. MEANWHILE, A CONVERGENCE OF EVOLVING TECHNOLOGIES, SUCH AS ELECTRIC PROPULSION AND AUTONOMOUS SYSTEMS, IS ENABLING TRANSFORMATIONAL CHANGES IN AIRCRAFT DESIGN AND OPERATION. THERE IS INTEREST, THEREFORE, IN EXPANDING THE METROPOLITAN TRANSPORT NETWORK INTO THE AIR. AT PRESENT, THERE IS SUBSTANTIAL INTEREST IN THE USE OF ELECTRIC VERTICAL TAKE-OFF AND LANDING (EVTOL) AIRCRAFT FOR URBAN AIR MOBILITY (UAM) HOWEVER, THIS CONCEPT HAS MANY TECHNOLOGICAL AND OPERATIONAL CHALLENGES. OPERATION IN A COMPLETELY URBAN ENVIRONMENT IS A STEP CHANGE FROM TODAYS AIRCRAFT OPERATIONS IN WHICH WE ATTEMPT TO SEPARATE AIR TRAVEL FROM POPULOUS AREAS. THE USE OF EVTOL AIRCRAFT THEMSELVES ALSO INTRODUCES A NUMBER OF INHERENT CONSTRAINTS TO VEHICLE AND MISSION DESIGN, SUCH AS HIGH ENERGY AND POWER REQUIREMENTS DUE TO VERTICAL FLIGHT, AND LIMITED FORECASTED BATTERY TECHNOLOGIES. AN ALTERNATIVE POSSIBILITY WOULD BE TO USE SHORT TAKE-OFF AND LANDING (STOL) AIRCRAFT. STOL OPERATIONS, WITH NO HOVER REQUIREMENT, INHERENTLY HAVE REDUCED ENERGY AND POWER REQUIREMENTS RELATIVE TO VERTICAL OPERATIONS. IF A VIABLE CONCEPT OF OPERATIONS EXISTS FOR STOL, INCLUDING ELECTRIC STOL (ESTOL) AIRCRAFT, THERE MAY BE IMPROVEMENTS RELATIVE TO EVTOL OPERATIONS, IN ASPECTS SUCH AS ENERGY EFFICIENCY, RANGE, PAYLOAD CAPACITY, OVERALL VEHICLE PERFORMANCE, NOISE, AND INFRASTRUCTURE REQUIREMENTS. FOR EXAMPLE, WITH A GREATER RANGE THAN EVTOL OPERATIONS, STOL OPERATIONS MAY IMPROVE THE ACCESS OF SUBURBAN AND RURAL COMMUNITIES TO URBAN CENTERS, PROVIDE ACCESS TO IMPROVED WORK AND STUDY OPPORTUNITIES, AND ULTIMATELY IMPROVE THE ECONOMY IN RU

AUGMENTOR-EJECTOR REFERENCE COMPILATION. A LARGE NUMBER OF VERTICAL TAKEOFF AND LANDING (VTOL) AIRCRAFT WERE DEVELOPED ACROSS THE WORLD, AND PARTICULARLY IN THE U.S. DURING THE 1950S THROUGH 1980S THAT EXPLORED DIVERSE CONFIGURATION APPROACHES TOWARDS ACHIEVING FEASIBLE OPERATIONS. HOWEVER, ACROSS THESE HUNDREDS OF DESIGN STUDIES AND FLIGHT DEMONSTRATORS ONLY THE V-22 OSPREY AND AV-8B HARRIER HAVE ACHIEVED OPERATIONAL STATUS AS FEASIBLE CONCEPT APPROACHES. THE DEVELOPMENT OF DISTRIBUTED ELECTRIC PROPULSION REPRESENTS A FUNDAMENTALLY NEW PROPULSION TECHNOLOGY THAT WILL LIKELY CHANGE THE FEASIBILITY OF PREVIOUSLY ATTEMPTED CONCEPT APPROACHES, DUE TO THE SCALE-FREE NATURE OF THE ELECTRIC PROPULSION TO BE APPLIED ANYWHERE ACROSS THE AIRCRAFT SYSTEM. IT IS HIGHLY DESIRABLE TO RE-EVALUATE PRIOR VTOL CONFIGURATION ATTEMPTS TO UNDERSTAND THE POTENTIAL OF THIS TECHNOLOGY TO ALTER THE FEASIBILITY. MUCH OF THE RESEARCH RELATING TO VTOL AIRCRAFT HAS BEEN DISAPPEARING AS THE RESEARCHERS WHO PERFORMED THIS RESEARCH ARE RETIRING AND COMPANIES FAIL TO RETAIN THE DETAILED RESEARCH RESULTS. THIS RESEARCH WILL DEVELOP A COMPREHENSIVE SET OF REFERENCES RELATING TO PRIOR FIXED WING VTOL CONFIGURATIONS EMPLOYING HIGH MASS FLOW AUGMENTORS AND AUGMENTOR-EJECTORS AND DOCUMENT THE LESSONS LEARNED RELATING TO THE APPLICATION OF DISTRIBUTED ELECTRIC PROPULSION AS A NEW TECHNOLOGY ENABLER THAT PROMOTES FEASIBILITY OF SPECIFIC CONCEPT APPROACHES. THIS RESEARCH WILL ALSO GATHER A NUMBER OF ORNITHOPTER REFERENCES THAT COULD APPLY TO THE APPLICATION OF DISTRIBUTED ELECTRIC PROPULSION (DEP).

BLOWN AIRFOIL CFD. THIS TASK WILL PERFORM COMPUTATIONAL FLUIDIC DYNAMIC (CFD) ANALYSIS ON A BLOWN WING CONFIGURATION TO DETERMINE AERO-PROPULSIVE PERFORMANCE. DISTRIBUTED ELECTRIC PROPULSION (DEP) ENABLES A HIGH DEGREE OF COUPLING BETWEEN THE AERODYNAMICS AND PROPULSION CHARACTERISTICS OF AIRCRAFT WING SYSTEMS. TIGHT COUPLING OF THESE TWO DISCIPLINES OFFER OPPORTUNITIES TO IMPROVE THE PERFORMANCE AND ACHIEVE CAPABILITIES THAT CAN T BE ACHIEVED WITH ISOLATED WING AND PROPULSION SOLUTIONS. HIGHER-ORDER ANALYSIS USING CFD TOOLS IS REQUIRED TO CAPTURE THESE HIGHLY COUPLED EFFECTS WITH ANALYSIS TOOLS THAT HAVE BEEN CALIBRATED TO VALIDATION DATASETS FROM PRIOR AERO-PROPULSIVE WIND TUNNEL TESTS. ANALYSIS OF SPECIFIC DEP WING SYSTEMS IS DESIRED TO IMPROVE THE STATE OF THE ART TO ACHIEVE VERY HIGH LIFT AT LOW SPEEDS, AT EVEN STATIC CONDITIONS WHILE ENTRAINING FLOW TO MAXIMIZE THE WING LIFTING CHARACTERISTICS. AT THE SAME TIME HIGH CRUISE EFFICIENCY IS DESIRED, ALONG WITH EXCELLENT CONTROL CHARACTERISTICS THROUGHOUT THE FLIGHT ENVELOPE. THIS RESEARCH WILL INVESTIGATE SPECIFIC DEP CONFIGURATION TO BETTER UNDERSTAND THE AERO-PROPULSIVE CHARACTERISTICS. EXISTING ANALYSIS WAS PERFORMED ON A GEOMETRY. THIS CURRENT STATEMENT OF WORK EXTENDS PREVIOUS WORK WITH MODIFICATIONS TO THE LOCATIONS AND SHAPE OF THE PROPULSORS, SLOT LOCATIONS, AND WING.

JUNCTURE FLOW VALIDATION EXPERIMENT SUPPORT

DEMAND FORECAST MODEL DEVELOPMENT AND SCENARIOS GENERATION FOR URBAN AIR MOBILITY CONCEPTS. THIS TASK IS TO ESTIMATE DEMAND FOR VARIOUS URBAN AIR MOBILITY CONCEPTS (UAM) OF OPERATIONS, AND TO GENERATE SCENARIOS FOR USE IN ANALYSIS AND SIMULATIONS. THE DEMAND FORECAST MODEL, PREVIOUSLY DEVELOPED UNDER NASA/NIA CONTRACT NO: NNL13AA08B TASK ORDER NO: NNL16AA36T, FOR AN URBAN ON DEMAND AIR TAXI COMMUTER CONCEPT WILL BE THE BASIS FOR THIS WORK. ADDITIONAL CONCEPTS MAY INCLUDE AN AIR-METRO CONCEPT WHERE SOMEWHAT LARGER AIRCRAFT (6 TO 10 PASSENGERS) OPERATE A SCHEDULED OR SEMI-SCHEDULED SERVICE FROM A LIMITED NUMBER OF VERTIPORTS. (SCHEDULED AT PEAK TIMES, OTHER FLIGHTS OCCUR IF DEMAND WARRANTS). THE MODEL WILL REQUIRE UPDATES TO INCORPORATE THE UAM CONCEPTS BEING INVESTIGATED AND THE CONCEPTS ARE EXPECTED TO EVOLVE AS KNOWLEDGE IS GAINED. THE DEMAND FORECASTING MODEL MUST THEREFORE BE FLEXIBLE AND EASY TO MODIFY. THE REGION OF INTERESTS WILL INCLUDE NORTHERN CA AND SUBURBS AND OTHER REGIONS AS DETERMINED BY NASA IN CONSULTATION WITH THE CONTRACTOR.

EXPLORATION OF POTENTIAL MINIMUM VIABLE PRODUCT MISSIONS FOR PASSENGER-CARRYING URBAN AIR MOBILITY MISSIONS. THE CONVERGENCE OF NEW TECHNOLOGIES, SUCH AS ELECTRIC PROPULSION, AUTONOMY, AND NEW BUSINESS MODELS, SUCH AS APP-BASED RIDE SHARING, ARE GENERATING THE POTENTIAL FOR A NEW AVIATION MARKET KNOWN AS URBAN AIR MOBILITY (UAM) TO EMERGE. IT IS ENVISIONED THAT UAM MAY REVOLUTIONIZE MOBILITY WITHIN METROPOLITAN AREAS BY ENABLING A SAFE, EFFICIENT, CONVENIENT, AFFORDABLE, AND ACCESSIBLE AIR TRANSPORTATION SYSTEM FOR PASSENGERS AND CARGO. SUCH AN AIR TRANSPORTATION SYSTEM COULD BRING AVIATION INTO PEOPLE S DAILY LIVES AND PROVIDE AN AUGMENTATION AND/OR ALTERNATIVE TO OTHER GROUND-BASED TRANSIT MODES, SUCH AS CARS. THE UAM MARKET IS NOT LIKELY TO APPEAR OVERNIGHT. RATHER, SOME FORM OF EVOLUTIONARY APPROACH BASED ON THE PACE OF TECHNOLOGY DEVELOPMENT, SOCIETAL ACCEPTANCE, AND MANY OTHER FACTORS MAY BRING US FROM THE CURRENT STATE OF THE ART TO THE ENVISIONED FUTURE STATE WHERE AVIATION IS A NORMAL PART OF PEOPLE S DAILY LIVES. TO HELP NASA ARMD CONSIDER POTENTIAL EVOLUTIONARY PATHS TO PASSENGER-CARRYING UAM OPERATIONS, THE DEVELOPMENT OF A MINIMUM VIABLE PRODUCT IS THE FOCUS OF THIS TASK. MINIMUM VIABLE PRODUCT (MVP) IS A TERM THAT EVOLVED FROM PRODUCT DEVELOPERS IN SILICON VALLEY WHO WERE SEEKING WAYS TO GET PRODUCTS INTO THE HANDS OF CONSUMERS AS EARLY AS POSSIBLE. BY DEFINING THE SMALLEST SET OF FEATURES THAT SATISFIES EARLY ADOPTERS, THE MVP APPROACH OFFERS THE ADVANTAGE OF PURSUING AN AMBITIOUS VISION WHILE LEARNING FROM REAL-WORLD USERS, GENERATING REVENUE EARLIER IN THE PRODUCT DEVELOPMENT PROCESS (POSSIBLY), AND FEEDING THE BUILD-MEASURE-LEARN CYCLE WITH DATA. MVP IS AN ITERATIVE PROCESS THAT REDUCES THE RISK OF DEVELOPING A PRODUCT BASED ON RISKY ASSUMPTIONS. THERE ARE MANY POTENTIAL MISSIONS THAT COULD EMERGE AS A MVP. ONE POTENTIAL MISSION, WHICH HAS RECEIVED SOME ATTENTION IN THE LITERATURE, IS THE MEDEVAC OR AERIAL MEDICAL TRANSPORT MARKET. ANOTHER POTENTIA

MODULAR HIGH-ORDER UNSTRUCTURED DISCONTINUOUS GALERKIN. THE PURPOSE OF THE TASK IS TO DESIGN AND DEVELOP A FULLY MODULAR, EXTENDABLE, AND FLEXIBLE HIGH-ORDER UNSTRUCTURED DISCONTINUOUS GALERKIN (DG) CODE FOR GENERAL RESEARCH PURPOSES. THE OBJECTIVE IS TO DEVELOP A PARALLEL, WELL DOCUMENTED, FULLY TESTED, DIMENSION INDEPENDENT, HIGH-ORDER DG CODE THAT MAY BE USED FOR STUDYING A WIDE RANGE OF PARTIAL DIFFERENTIAL EQUATIONS, INCLUDING SCALAR NONLINEAR ADVECTION-DIFFUSION EQUATIONS, AND COMPRESSIBLE EULER, AND NAVIER-STOKES EQUATIONS (LAMINAR AND/OR TURBULENT) WITH OR WITHOUT SOURCE TERMS, USING LINEAR AND NONLINEAR SIMPLEX (PREFERABLY ARBITRARY) ELEMENTS, FOR A WIDE RANGE OF CONTINUOUS (SMOOTH) AND/OR DISCONTINUOUS SOLUTIONS.

TOW-STEERED PANELS FOR TAILORED WINGS. THE PASSIVE AEROELASTIC TAILORED (PAT) WING TASK UNDER THE ADVANCED AIR TRANSPORTATION TECHNOLOGIES (AATT) PROJECT IS DEVELOPING DESIGNS TO SUPPORTED LIGHTWEIGHT HIGH-ASPECT RATIO COMPOSITE WINGS FOR FUTURE COMMERCIAL TRANSPORT AIRCRAFT. ONE APPROACH IS TO USE AUTOMATED FIBER PLACEMENT (AFP) MANUFACTURING TECHNOLOGY WITH FIBER ORIENTATIONS TAILORED IN DIRECTIONS WITHIN THE PLANE TO SUPPORT OPTIMUM SHAPES RELATIVE TO STATIC AND AERODYNAMIC LOADS. THE GOAL OF THIS RESEARCH PROJECT IS TO DEVELOP MINIMUM-WEIGHT STRUCTURAL DESIGNS OF TOW-STEERED FLAT COMPOSITE PANELS REPRESENTATIVE OF WING STRUCTURE WHICH CAN BE FABRICATED ON THE INTEGRATED STRUCTURAL ASSEMBLY OF ADVANCED COMPOSITES (ISAAC) ROBOT AT NASA LANGLEY RESEARCH CENTER (LARC) AND TESTED IN THE LARC FACILITIES. THE CURRENT NEED IS TO DEVELOP DESIGNS AND CONDUCT DETAILED ANALYSES OF TWO OR MORE FLAT TOW-STEERED CARBON-FIBER PANELS BASED ON A COMPUTER MODEL OF THE RELEVANT WING WHICH WILL BE PROVIDED BY NASA. THE CONTRACTOR SHALL USE SUITABLE ANALYSIS TO DEMONSTRATE THE VALUE OF TOW STEERING IN REDUCING WEIGHT COMPARED TO STRAIGHT-FIBER PANELS.

"TRAINING SCENARIO DEVELOPMENT FOR ATTENTION-RELATED HUMAN PERFORMANCE LIMITATIONS" THE PURPOSE OF THIS TASK IS TO PROVIDE RESEARCH AND DEVELOPMENT SUPPORT, TECHNICAL AND SUBJECT MATTER EXPERTISE, AND SUBJECT MATTER CONSULTATION TO LANGLEYS CREW SYSTEM AND AVIATION OPERATIONS BRANCH (CSAOB/D-318).

TITLE- "REVOLUTIONARY AVIATION TECHNOLOGIES MEASUREMENTS AND MATERIALS DEVELOPMENT" THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASK REQUIREMENTS:3.1 THE CONTRACTOR SHALL DEVELOP ELECTROMAGNETIC CHARACTERIZATION TECHNIQUES THAT WILL SUPPORT RATB MATERIALS DEVELOPMENT EFFORTS. THE DETAILS ARE COVERED IN A SEPARATE DOCUMENT. 3.2 THE CONTRACTOR SHALL DESIGN, DEVELOP, SYNTHESIZE, CHARACTERIZE AND INTEGRATE NEW MATERIALS TO ENHANCE PERFORMANCE OF AIRCRAFT AND AIRCRAFT SYSTEMS. THE DETAILS ARE COVERED IN A SEPARATE DOCUMENT. 3.3 THE CONTRACTOR SHALL DESIGN, DEVELOP AND BUILD TEST FIXTURES THAT WILL SUPPORT RATB MATERIALS DEVELOPMENT EFFORTS. THE DETAILS ARE COVERED IN A SEPARATE DOCUMENT.

THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASK REQUIREMENTS:3.1 PERFORM THERMAL, MECHANICAL AND ELECTRICAL CHARACTERIZATION OF MATERIALS DEVELOPED BY RATB. 3.2 [DE-SCOPED IN ITS ENTIRETY] SYNTHESIZE NEW MATERIALS AS DIRECTED BY THE TASK MONITOR (TM) TO ENHANCE THE PERFORMANCE OF AIRCRAFT AND AIRCRAFT SYSTEMS. 3.3 PARTICIPATE IN TECHNOLOGY REVIEWS AS REQUIRED BY THE TASK TM. THIS MAY INCLUDE TECHNICAL GROUP MEETINGS AND TELECONS. CONTRACTORS SHALL PROVIDE INFORMATION AND DATA TO THE TM OR SUBMIT POWERPOINT PRESENTATIONS AS REQUIRED FOR INTERNAL OR AGENCY REVIEWS. 3.4 PREPARE A FINAL TECHNICAL REPORT TO DESCRIBE THE MATERIALS CHARACTERIZATION PERFORMED, MATERIALS FABRICATED, DESCRIPTION OF HOW THE MATERIALS MEET THE TECHNICAL PROGRAMMATIC OBJECTIVES, AND DATA ANALYSIS. 3.5 [DE-SCOPED IN ITS ENTIRETY] AS REQUESTED BY TM, PREPARE AND CHARACTERIZE KNOWN CHEMICAL COMPOUNDS TO SUPPORT THE OBJECTIVES OF THE TASK. PREPARATION DETAILS, CHARACTERIZATION REQUIREMENTS, QUANTITY REQUIREMENTS AND DELIVERY DATE REQUIREMENTS WILL BE PROVIDED BY THE TM TO THE CONTRACTOR FOR EACH INDIVIDUAL REQUEST. CONTRACTOR SHALL PROVIDE ADDITIONAL PERSONNEL AND FACILITIES TO PERFORM THIS INTERMITTENT WORK, AS WELL AS ANY ADDITIONAL FUNDING REQUESTS REQUIRED TO COMPLETE WORK.

TD-FAST (TIME DOMAIN FAST ACOUSTIC SCATTERING TOOLKIT). ACCURATE AND EFFICIENT HIGH-FIDELITY NOISE PREDICTION TOOLS ARE CRITICAL TO THE DESIGN AND ASSESSMENT OF NEXT GENERATION AIRCRAFT. THE PURPOSE OF THIS RESEARCH IS TO FURTHER DEVELOP, IMPLEMENT AND VALIDATE AN EFFICIENT HIGH-FIDELITY TIME DOMAIN ACOUSTIC SCATTERING PREDICTION TOOL THAT IS CAPABLE OF TREATING A COMPLETE AIRCRAFT, COVERING A FULL FREQUENCY RANGE OF INTEREST WITHIN A SHORT TURN-AROUND TIME. TIME DOMAIN ACOUSTIC SCATTERING PREDICTION CAPABILITIES HAVE SOME DISTINCT ADVANTAGES OVER FREQUENCY DOMAIN APPROACHES. MOST NOTABLY, SCATTERING SOLUTIONS AT ALL FREQUENCIES ARE OBTAINED WITHIN ONE SINGLE COMPUTATION. IN ADDITION, BROADBAND NOISE SOURCES AND TIME DEPENDENT TRANSIENT SIGNALS CAN BE SIMULATED AND STUDIED. THE TIME DOMAIN APPROACH ALSO COUPLES NATURALLY WITH NONLINEAR COMPUTATIONS WHERE MANY FREQUENCIES ARE GENERATED. FINALLY, WITH RECENT ADVANCES IN MULTI-LEVEL ALGORITHMS, COMPUTATIONAL COMPLEXITY CAN BE GREATLY REDUCED, MAKING IT FEASIBLE FOR ROUTINE APPLICATION AT MID TO HIGH FREQUENCIES WITH REDUCED RESOURCE REQUIREMENTS.

COMMERCIAL CREW VEHICLE ENTRY, DECENT, AND LANDING (EDL) INDEPENDENT SIMULATION AND ANALYSIS - EDL INDEPENDENT SIMULATION AND ANALYSIS. NASA HAS A SUCCESSFUL HISTORY DEVELOPING COMPLEX SPACEFLIGHT ATMOSPHERIC REENTRY SYSTEMS FOR BOTH CREWED AND ROBOTIC SYSTEMS. ALL OF THESE HUMAN AND ROBOTIC FLIGHT PROGRAMS HAVE BENEFITED FROM USING INDEPENDENT SYSTEM MODELS AND INTEGRATED SIMULATIONS TO IDENTIFY AND RESOLVE HIGHLY COUPLED SYSTEM FAILURE MODES AND TECHNICAL RISKS, PARTICULARLY THOSE THAT OCCUR AT OR NEAR COMPLEX HARDWARE, SOFTWARE, OR DISCIPLINE INTERFACES. COMPLEX FLIGHT SYSTEMS OFTEN HAVE FAILURE MODES AT ELEMENT AND SUBSYSTEM INTERFACES. THESE FAILURE MODES MAY ONLY MANIFEST THEMSELVES WHEN COMPONENTS ARE OPERATED AS AN INTEGRATED SYSTEM THEY DO NOT NECESSARILY OCCUR WHEN EVALUATING, TESTING, OR OPERATING SINGLE COMPONENTS OR ELEMENTS. NUMEROUS EXAMPLES EXIST IN WHICH FLIGHT PROJECTS AND PROGRAMS HAVE BENEFITED FROM INDEPENDENT PHYSICS-BASED END-TO-END MODELING AND SIMULATION (M&S). COROLLARY EXAMPLES EXIST WHERE FAILURES COULD HAVE BEEN IDENTIFIED AND RESOLVED BY INDEPENDENT M&S. HISTORICALLY, THE ENTRY, DESCENT, AND LANDING (EDL) PHASES OF FLIGHT PRESENT SOME OF THE HIGHEST RISK ELEMENTS OF FLIGHT SYSTEM ARCHITECTURES. FOR COMPLEX FLIGHT SYSTEMS, NASA AND DEPARTMENT OF DEFENSE DEVELOPMENT ACTIVITIES HAVE BENEFITED FROM INDEPENDENT M&S EFFORTS. LOW-, MODERATE-, AND HIGH-FIDELITY MULTIPLE-DOF FLIGHT SIMULATIONS ARE OFTEN UTILIZED TO INTEGRATE AND ANALYTICALLY STRESS CRITICAL ELEMENT AND SUBSYSTEM MODELS AND TO DEFINE AND UNDERSTAND THE BOUNDARIES OF OPERATIONAL ENVIRONMENTS WITHIN WHICH SYSTEMS MUST PERFORM. THE NASA ENGINEERING AND SAFETY CENTER (NESC) ASSEMBLED A MULTI-CENTER TEAM TO DEVELOP INDEPENDENT 3- AND 6-DEGREE-OF-FREEDOM (DOF) SIMULATION CAPABILITY OF EDL FLIGHT PHASES FOR THE COMMERCIAL CREW VEHICLES, AND TO CONDUCT INDEPENDENT EDL ANALYSIS USING THESE SIMULATIONS. THIS PLAN OUTLINES DEVELOPMENT OF HIGHER-FIDELITY EDL CAPABILITY FOR TWO COMMERCIAL C

CANCELING FUNDS MOD

STATISTICAL ENGINEERING FOR AIRSPACE TECHNOLOGY DEMONSTRATION. STATISTICAL METHODS ARE BEING UTILIZED IN NASA S AIRSPACE TECHNOLOGY DEMONSTRATION (ATD) PROJECT WITHIN THE AIRSPACE OPERATIONS AND SAFETY PROGRAM TO ASSESS THE PERFORMANCE AND EFFICIENCY OF CONCEPTS, TOOLS, PROCEDURES, AND ALGORITHMS, AND SUPPORT OPERATIONAL ANALYSES. MORE SPECIFICALLY, STATISTICAL EXPERIMENT DESIGN AND ANALYSIS IS REQUIRED TO SUPPORT EXPERIMENTS INVESTIGATING THE INTEGRATION OF CONCEPTS AND TECHNOLOGIES, LEADING TO A DEMONSTRATION OF THE TECHNOLOGIES IN A RELEVANT ENVIRONMENT. TO SUPPORT ATD, STATISTICAL EXPERTISE IS REQUIRED THAT FOCUSES ON HYPOTHESIS DEFINITION, EXPERIMENT DESIGN, PLANNING AND OBSERVATION, SAMPLE SIZE DETERMINATION, ANALYSIS OF VARIANCE, REGRESSION MODELING, NONPARAMETRIC ANALYSES, HYPOTHESIS TESTING, INFERENCE, AND INTERPRETATION OF THE EXPERIMENTAL RESULTS, WHICH INCLUDE PILOT FOCUS GROUP, FLIGHT TEST, AND OPERATIONAL EVALUATION. THIS TASK ORDER REQUIRES STATISTICAL MODELING, ANALYSIS, INTERPRETATION, COMMUNICATION, AND WRITTEN REPORTS.

PTR-MS (PROTON TRANSFER-MASS SPECTROSCOPY) MEASUREMENTS OF NON-METHANE HYDROCARBONS INSTRUMENT IS CAPABLE OF PROVIDING MEASUREMENTS OF A WIDE ARRAY OF NON-METHANE HYDROCARBON SPECIES WITH HIGH TIME RESOLUTION (E.G., 1 SECOND OR LESS). EXPERTISE TO MAKE SUCH MEASUREMENTS FROM AN AIRBORNE PLATFORM IS RARE, BUT SUCH MEASUREMENTS ARE NEEDED BY NASA S NORTH ATLANTIC AEROSOLS AND MARINE ECOSYSTEM STUDY (NAAMES) FIELD CAMPAIGN TO HELP UNDERSTAND THE ATMOSPHERIC DISTRIBUTIONS OF THESE IMPORTANT COMPOUNDS AND THEIR ROLE IN ATMOSPHERIC CHEMISTRY. RECENT CHANGES IN PTR-MS TEAM PERSONNEL NECESSITATE CONTRACTING OUT THE WORK DESCRIBED BELOW. THE PTR-MS SYSTEM IS INCLUDED IN THE AIRBORNE PAYLOAD FOR THE NAAMES FIELD CAMPAIGN. THIS TASK SUPPORTS THE FOLLOWING SUBTASKS OF THIS FIELD CAMPAIGN: OPERATION OF THE PTR-MS SYSTEM ONBOARD THE NASA C-130 DURING THE NAAMES MARCH/APRIL 2018 FIELD CAMPAIGN DE-INTEGRATION OF THE PTR-MS SYSTEM FROM THE NASA C-130 AT THE CONCLUSION OF THE FIELD CAMPAIGN PROCESS, QUALITY CONTROL, AND ARCHIVE PRELIMINARY DATA AFTER THE FIELD CAMPAIGN CONCLUDES

ELECTRICAL INFRASTRUCTURE STUDY FOR URBAN AIR MOBILITY (UAM) AIRCRAFT. THE CONVERGENCE OF NEW TECHNOLOGIES, SUCH AS ELECTRIC PROPULSION, AUTONOMY, AND NEW BUSINESS MODELS, SUCH AS APP-BASED RIDE SHARING, ARE GENERATING THE POTENTIAL FOR A NEW AVIATION MARKET KNOWN AS URBAN AIR MOBILITY (UAM) TO EMERGE. IT IS ENVISIONED THAT UAM MAY REVOLUTIONIZE MOBILITY WITHIN METROPOLITAN AREAS BY ENABLING A SAFE, EFFICIENT, CONVENIENT, AFFORDABLE, AND ACCESSIBLE AIR TRANSPORTATION SYSTEM FOR PASSENGERS AND CARGO. SUCH AN AIR TRANSPORTATION SYSTEM COULD BRING AVIATION INTO PEOPLE S DAILY LIVES AND PROVIDE AN AUGMENTATION AND/OR ALTERNATIVE TO OTHER GROUND-BASED TRANSIT MODES, SUCH AS CARS. BECAUSE UAM IS ENVISIONED TO AID IN MOBILITY AROUND DENSE URBAN AREAS WHERE LAND AVAILABILITY IS SCARCE, MOST VEHICLES BEING PROPOSED IN THIS SPACE ARE CAPABLE OF VERTICAL TAKEOFF AND LANDING (VTOL) LIKE CONVENTIONAL HELICOPTERS. ADDITIONALLY, THE IMPLEMENTATION OF ELECTRIC PROPULSION ONTO SMALL VTOL AIRCRAFT MAY ENABLE MORE EFFICIENT, QUIETER, AND FASTER VEHICLES THAN ARE ACHIEVABLE WITH CONVENTIONAL PROPULSION SYSTEMS AND CONFIGURATIONS. THEREFORE, THE VEHICLES THAT ARE LIKELY TO PERFORM UAM MISSIONS HAVE BECOME KNOWN AS ELECTRIC VERTICAL TAKEOFF AND LANDING, OR EVTOL, VEHICLES. THE LOCATIONS FROM WHICH THESE UAM AIRCRAFT WILL OPERATE HAVE BEEN TERMED VERTIPORTS. EACH VERTIPORT MAY HAVE A SINGLE VERTIPAD OR MULTIPLE VERTIPADS FROM WHICH AIRCRAFT MAY TAKEOFF, LAND, PARK, AND/OR RECHARGE. THE EXACT DISTRIBUTION, NUMBER, AND SIZE OF VERTIPORTS ACROSS A METROPOLITAN AREA IS AS YET UNDEFINED, THOUGH SOME ESTIMATES HAVE BEEN PRESENTED BY NASA-FUNDED RESEARCH1 AND UBER.2 FOR THIS INFRASTRUCTURE TO SUPPORT PURELY ELECTRIC VTOL AIRCRAFT, THERE WILL NEED TO BE RECHARGING CAPABILITIES AT MANY, IF NOT ALL, OF THE VERTIPORTS. SUCH INFRASTRUCTURE DOES NOT EXIST TODAY AND MUST BE INSTALLED PRIOR TO AN ALL-ELECTRIC UAM NETWORK BEING IMPLEMENTED. THE PURPOSE OF THIS TASK IS TO HELP PROVIDE A HIGH-LEVEL U

INITIAL ASSESSMENT OF AIRCRAFT CERTIFICATION PROCEDURES FOR EMERGING TECHNOLOGIES. THIS TASK ORDER WILL IDENTIFY GAPS THAT MAY EXIST DUE TO EMERGING TECHNOLOGIES IN BOTH NEW CERTIFICATION RULES AND EXISTING STANDARDS USED AS MEANS OF COMPLIANCE TO THESE RULES FOR NORMAL CATEGORY AIRCRAFT. A PROCESS WILL BE CREATED TO HELP IDENTIFY GAPS, AS WELL AS MAP KNOWN TECHNOLOGY DEVELOPMENT PROGRAMS THAT MAY BE SUITABLE FOR A MEANS OF COMPLIANCE. THIS INFORMATION WILL BE DEVELOPED WITH INPUT FROM, AND DIALOGUE WITH, THE REGULATORY COMMUNITY AND RELEVANT STANDARDS ORGANIZATIONS. NASA S X-57 MAXWELL DISTRIBUTED ELECTRIC PROPULSION FLIGHT DEMONSTRATOR WILL BE USED AS AN EXAMPLE TO TEST THE CURRENT STATE OF REGULATIONS AND MEANS OF COMPLIANCE, SINCE DETAILED INFORMATION IS AVAILABLE ON ITS DESIGN AND PERFORMANCE CHARACTERISTICS. THOUGH THE INITIAL FOCUS OF THIS EFFORT WILL BE UNDER 14 CFR PART 23, OTHER PARTS IN SCOPE INCLUDE PART 33 (AIRCRAFT ENGINES) AND PART 35 (PROPELLERS) AS APPROPRIATE. WHERE GAPS ARE FOUND, DATA AND PROCEDURES FROM CURRENT AND PREVIOUS NASA ACTIVITIES WILL BE SHARED AS RELEVANT TO THE KNOWN GAPS. THIS WORK INCLUDES SEVERAL OPPORTUNITIES TO INTERFACE WITH REGULATORS AND CONSENSUS STANDARDS MEMBERS, AND WILL USE THIS ANCHOR STUDY TO HELP ESTABLISH THE FRAMEWORK FOR FUTURE COLLABORATIVE EFFORT TO IMPROVE THE STATE OF CERTIFICATION PROCEDURES FOR NEW AIRCRAFT TECHNOLOGY.

MODELING AND ANALYSIS OF SPACE ROBOTIC SYSTEMS. THE SUCCESSFUL EXECUTION OF THE LARC (LANGLEY RESEARCH CENTER) ROLE ON CIRAS (COMMERCIAL INFRASTRUCTURE FOR ROBOTIC ASSEMBLY AND SERVICES) WILL REQUIRE DEVELOPMENT AND REFINEMENT OF TALISMAN (TENDON-ACTUATED LIGHTWEIGHT IN-SPACE MANIPULATOR) AND NINJAR (NASA INTELLIGENT JIGGING AND ASSEMBLY ROBOTS) CONTROL ALGORITHMS. NASA/LARC SEEKS SUPPORT IN THE DEVELOPMENT AND EXECUTION OF THESE ALGORITHMS AND THE IMPLEMENTATION OF THE ALGORITHMS IN MATLAB, GAZEBO, ROS, AND SPEEDGOAT ENVIRONMENTS. THIS EFFORT WILL REQUIRE THE CONVERSION AND MODIFICATION OF EXISTING CONTROL ALGORITHMS PREVIOUSLY DEVELOPED BY NASA AND RE-CONFIGURING THEM FOR USE IN NEW COMPUTING ENVIRONMENTS. THE TASK WILL ALSO REQUIRE THE DEVELOPMENT OF NEW CONTROL ALGORITHMS AND STRATEGIES FOR THE NEW TALISMAN AND NINJAR 2.0 AND 3.0 SYSTEMS PRESENTLY UNDER DEVELOPMENT UNDER THE CIRAS CONTRACT. THE RESULT OF ALL OF THIS WORK WILL BE THE DEVELOPMENT OF A CONTROL SYSTEM SPECIFICALLY DESIGNED FOR THE TALISMAN 2.0/3.0 ARCHITECTURES TO BE DEMONSTRATED AT LARC IN FY18.

CONVERGENT AERONAUTICS SOLUTIONS PROJECT ROUND 2 SYSTEMS ANALYSES SUPPORT. THE TRANSFORMATIVE AERONAUTICS CONCEPTS PROGRAM (TACP) SOLICITS AND ENCOURAGES REVOLUTIONARY CONCEPTS, CREATES THE ENVIRONMENT FOR RESEARCHERS TO EXPERIMENT WITH NEW IDEAS, PERFORMS GROUND AND SMALL-SCALE FLIGHT TESTS, ALLOWS FAILURES AND LEARNS FROM THEM, AND DRIVES RAPID TURNOVER INTO POTENTIAL FUTURE CONCEPTS TO ENABLE AVIATION TRANSFORMATION. RESEARCH IS ORGANIZED TO AGGRESSIVELY ENGAGE BOTH THE TRADITIONAL AERONAUTICS COMMUNITY AND NON-TRADITIONAL PARTNERS. ALTHOUGH TACP FOCUSES ON SHARPLY FOCUSED STUDIES, THE PROGRAM PROVIDES FLEXIBILITY FOR INNOVATORS TO ASSESS NEW-TECHNOLOGY FEASIBILITY AND PROVIDE THE KNOWLEDGE BASE FOR RADICAL AERONAUTICS ADVANCE. THE CONVERGENT AERONAUTICS SOLUTIONS (CAS) PROJECT IS ONE OF TWO PROJECTS UNDER TACP. CAS CONDUCTS SHORT-DURATION, TYPICALLY 18-30 MONTHS, ACTIVITIES TO ESTABLISH EARLY-STAGE CONCEPTS AND TECHNOLOGY FEASIBILITY FOR HIGH-POTENTIAL SOLUTIONS. THE CAS PROJECT CONDUCTS A YEARLY SELECTION PROCESS TO IDENTIFY THE MOST INNOVATIVE IDEAS. NASA INTERNAL TEAMS PROPOSE IDEAS FOR OVERCOMING KEY BARRIERS ASSOCIATED WITH LARGE-SCALE AERONAUTICS PROBLEMS. THE FOCUS IS ON MERGING TRADITIONAL AERONAUTICS DISCIPLINES WITH ADVANCEMENTS DRIVEN BY THE NON-AERONAUTICS WORLD TO MAKE POSSIBLE NEW CAPABILITIES IN COMMERCIAL AVIATION. CAS TEAMS, PRIMARILY CONSISTING OF RESEARCHERS FROM MULTIPLE NASA CENTERS PLUS INDUSTRY/UNIVERSITY PARTNERS, THEN CONDUCT INITIAL FEASIBILITY STUDIES, PERFORM EXPERIMENTS, TRY OUT NEW IDEAS, IDENTIFY FAILURES AND TRY AGAIN. AT THE END OF THAT CYCLE, NASA CONDUCTS A REVIEW TO DETERMINE WHETHER THE DEVELOPED SOLUTIONS HAVE MET THEIR GOALS, ESTABLISHED INITIAL FEASIBILITY, AND IDENTIFIED REAL-WORLD POTENTIAL. IN AN ATTEMPT TO MAXIMIZE POTENTIAL TRANSITION OPPORTUNITIES, THE CAS PROJECT IS CONDUCTING INTEGRATED, MULTI-DISCIPLINARY SYSTEMS ANALYSES OF THEIR PORTFOLIO S ROUND 2 AWARDS. THE RESULTS FROM THIS ANALYSIS, ALONG WITH ANY BENEFIT

AIRPLANE AUTOMATION AND INFORMATION MANAGEMENT EXPERIMENTS. INVOLVES HIGH-FIDELITY FLIGHT SIMULATION EXPERIMENTS DESIGNED TO ADDRESS FOUR OBJECTIVES: (1) RAISE THE TECHNOLOGY READINESS LEVEL FOR SELECTED NEW TECHNOLOGIES VIA TESTING ACROSS A SPAN OF CONDITIONS AND PLATFORMS (2) DISCOVER PREVIOUSLY UNKNOWN CONTRIBUTING FACTORS TO LOSS OF AIRPLANE STATE AWARENESS (3) ASSESS THE USABILITY AND ACCEPTABILITY OF THE NEW TECHNOLOGIES AND (4) ADVANCE TEST INFRASTRUCTURE CAPABILITY FOR SUBSEQUENT TESTS INCLUDING VALIDATING TEST PLATFORM PERFORMANCE. TWO PRIOR AUTOMATION AND INFORMATION MANAGEMENT EXPERIMENTS (AIME-1 AND AIME-2) WERE CONDUCTED TO ADDRESS MANY OF THESE RESEARCH GOALS. FOLLOW-ON EXPERIMENTS ARE BEING PLANNED NOW. IN THESE TESTS, COMMERCIAL AIRLINE PILOTS WILL FLY SPECIFIC SCENARIOS AND PROVIDE FEEDBACK ON THE FLIGHT DECK TECHNOLOGIES EMPLOYED IN THE SCENARIO. AS PART OF EXPERIMENT PREPARATION, REALISTIC SCENARIOS NEED TO BE DESIGNED THAT WILL EXERCISE TEST CONDITIONS THAT ACHIEVE EXPERIMENT OBJECTIVES. IN ADDITION, FLIGHT DECK DISPLAY TECHNOLOGIES (DEVELOPED BY NASA AND ITS PARTNERS) WILL BE EVALUATED FOR THEIR PERFORMANCE AND USABILITY BY PILOTS.

LOADS AND DYNAMICS TECHNICAL DISCIPLINE TEAM (TDT) PARTICIPATION.

WIND-TUNNEL BALANCE DESIGN TRADE STUDY. WIND-TUNNEL BALANCES ARE THE PRIMARY SOURCE FOR AERODYNAMIC FORCE AND MOMENT DATA IN GROUND-BASED AERONAUTICS RESEARCH. BUT, BALANCES ARE TIME CONSUMING AND COSTLY TO MANUFACTURE. THE TIME AND COSTS ASSOCIATED WITH BALANCE FABRICATION ARE PRIMARILY DRIVEN BY THE BLIND CUTS THAT ARE OFTEN SPECIFIED DURING THE DESIGN PROCESS. THESE CUTS ALMOST ALWAYS REQUIRE BALANCE MANUFACTURERS TO RESORT TO USING ELECTRICAL DISCHARGE MACHINING (EDM) WITH COMPLEX FLAG SHAPED ELECTRODES TO ACHIEVE THE BLIND CUTS. THE OBJECTIVE OF THIS WORK IS TO RESEARCH WIND-TUNNEL BALANCE DESIGNS THAT DO NOT REQUIRE BLIND CUTS TO ACHIEVE THE MEASUREMENT GOALS AND ULTIMATELY PERMIT BALANCE FABRICATION TO BE COMPLETED USING HIGHER SPEED MILLING, DRILLING, AND GRINDING OPERATIONS. ELIMINATING BLIND CUTS FROM THE DESIGN MAY NECESSITATE REDUCING THE MOMENT OF INERTIA OF THE BALANCE AT SECTIONS ALONG THE BALANCE LENGTH. THE REDUCED MOMENT OF INERTIA WILL LIKELY RESULT IN INCREASED BALANCE DEFLECTION AND STRESSES ALONG WITH A DECREASED RESONANT FREQUENCY. THUS, ANOTHER OBJECTIVE OF THIS WORK WILL BE TO QUANTITATIVELY ESTIMATE THE EFFECT OF THE NEW DESIGNS ON THE DEFLECTION, STRESS, AND RESONANT FREQUENCY.

ASSESSMENT AND IMPROVEMENTS FOR AEROTHERMAL PREDICTIONS USING FUN3D ASSESS. ADDRESS SHORTCOMINGS USING APPROACHES INVISCID FLUX DISCRETIZATIONS, SHOCK CAPTURING SCHEMES, RECONSTRUCTION LIMITERS, EIGENVALUE LIMITING, AND MESH ADAPTATION STRATEGIES

HYBRID ELECTRIC TECHNOLOGY COLLECTOR DEVELOPMENT AND N+3 TECHNOLOGY ASSESSMENTS FOR AATT (ADVANCED AIR TRANSPORT TECHNOLOGY) PROJECT THE CONTRACTOR SHALL PERFORM THREE MAJOR TASKS IN SUPPORT OF THE PROJECT: IDENTIFY AND MODEL TECHNOLOGY COLLECTORS FOR SIX VEHICLE CLASSES EXPLORING DIFFERENT GAS ELECTRIC PROPULSION ARCHITECTURES, N+3 TECHNOLOGY ASSESSMENTS ACROSS VEHICLE CLASSES, AND PERFORM REVIEWS, STATUS UPDATES AND REPORTS.

IMPLEMENTATION OF ELASTIC-PLASTIC CRACK INSTABILITY ANALYSIS CAPABILITY INTO THE FADD CODE (JR-A METHODOLOGY)

AUGMENTED REALITY/VIRTUAL REALITY. THE PURPOSE OF THIS WORK IS TO SUPPORT NASA IN DEVELOPING AUGMENTED REALITY / VIRTUAL REALITY APPLICATIONS, AND COMPUTER MODELING / SIMULATION OF LIVE OPERATING EQUIPMENT AT LARC COMPRESSOR STATION. POP 5/8/2017 - 08/14/2017

TD-FAST (TIME DOMAIN FAST ACOUSTIC SCATTERING TOOLKIT) THE PURPOSE OF THIS RESEARCH IS TO FURTHER DEVELOP, IMPLEMENT AND VALIDATE A FAST AND EFFICIENT HIGH-FIDELITY TIME DOMAIN SCATTERING COMPUTATION OF ACOUSTIC WAVES THAT IS CAPABLE OF TREATING THE FULL BODY OF A WHOLE AIRCRAFT, COVERING A FULL FREQUENCY RANGE OF INTEREST WITHIN A SHORT TURN-AROUND TIME.