SMAAART TASK TITLE: BLENDED WING BODY CONCEPT DEVELOPMENT WITH OPEN ROTOR ENGINE INTEGRATION 1.0 INTRODUCTI…

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SMAAART TASK TITLE: BLENDED WING BODY CONCEPT DEVELOPMENT WITH OPEN ROTOR ENGINE INTEGRATION 1.0 INTRODUCTION/BACKGROUND: THE BLENDED WING BODY (BWB) CONCEPT HAS BEEN STUDIED EXTENSIVELY DUE TO THE POTENTIAL IT HAS TO SIGNIFICANTLY REDUCE FUEL BURN, EMISSIONS AND NOISE LEVELS COMPARED TO CURRENT AND FUTURE CONVENTIONAL TUBE-WITH-WING SUBSONIC TRANSPORT CONFIGURATIONS. THE BWB CONCEPT HAS BEEN STUDIED WITH A VARIETY OF PROPULSION OPTIONS, INCLUDING PODDED NACELLES, EMBEDDED ENGINES, GEARED FANS AND OPEN ROTORS. OPEN ROTOR TECHNOLOGY HAS THE POTENTIAL TO PROVIDE THE GREATEST FUEL BURN REDUCTION RELATIVE TO ALL OTHER POTENTIAL PROPULSION OPTIONS FOR THE BWB. IN ADDITION, THE BWB OFFERS THE POTENTIAL FOR NOISE SHIELDING, THUS AMELIORATING ONE OF THE MAIN DRAWBACKS OF THE OPEN ROTOR. HOWEVER, OPEN ROTOR INTEGRATION WITH THE BWB HAS NOT BEEN STUDIED AS EXTENSIVELY AS PODDED AND EMBEDDED ENGINE OPTIONS. THE MAIN PURPOSE OF THIS TASK IS TO PERFORM A SYSTEMS ANALYSIS OF A BWB OPEN ROTOR CONCEPT AT THE CONCEPTUAL DESIGN LEVEL. THIS CONCEPT WILL BE UTILIZED BY NASA TO ESTIMATE OVERALL NOISE AND FUEL BURN PERFORMANCE, UTILIZING RECENT TEST DATA. 2.0 SCOPE / OBJECTIVES: THIS TASK IS FOR A CONCEPTUAL DESIGN STUDY (I.E., SYSTEMS ANALYSIS) OF AN OPEN ROTOR BWB CONCEPT OPTIMIZED TO PROVIDE A BALANCED REDUCTION OF FUEL BURN, NOISE AND EMISSIONS UTILIZING TECHNOLOGY THAT WILL SUPPORT A 2025 ENTRY INTO SERVICE (EIS) DATE. A 2025 EIS WILL REQUIRE A TECHNOLOGY READINESS LEVEL (TRL) OF 6 BY 2020. THE SCOPE OF THE TASK INCLUDES REQUIREMENTS DEVELOPMENT, PLANFORM DESIGN, INTERNAL LAYOUT AND SUBSYSTEM DEFINITION, AERODYNAMICS AND WEIGHT ESTIMATION, ENGINE DEFINITION AND INTEGRATION, STABILITY AND CONTROL (INCLUDING POWERED EFFECTS) ESTIMATION AND PERFORMANCE ESTIMATION. THE SPECIFIC OBJECTIVES FOR THIS TASK ARE AS FOLLOWS: REQUIREMENTS DEVELOPMENT IN CONJUNCTION WITH NASA. CONCEPT DEFINITION AND DESIGN FOR MINIMUM FUEL BURN, NOISE AND EMISSIONS. OPEN ROTOR PROPULSION INTEGRATION. FULL CONCEPTUAL DESIGN INCLUDING AERODYNAMICS, WEIGHTS, STABILITY AND CONTROL, SUBSYSTEMS, AND PERFORMANCE ANALYSIS. DELIVERY OF A CONCEPT DESIGN DATA PACKAGE ENABLING NASA TO PERFORM NOISE AND PERFORMANCE ANALYSIS. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 REQUIREMENTS DEVELOPMENT 3.1.1 THE CONTRACTOR SHALL WORK IN CONJUNCTION WITH NASA TO DEFINE THE REQUIREMENTS FOR THIS CONCEPT, INCLUDING RANGE/PAYLOAD, TAKEOFF AND LANDING FIELD LENGTH, CRUISE MACH NUMBER, AIRPORT COMPATIBILITY, MISSION PROFILE INCLUDING RESERVE MISSION AND SIZING CONSTRAINTS. THE CONTRACTOR SHALL DELIVER A DRAFT REQUIREMENTS DOCUMENT. MS WORD OR POWERPOINT FORMAT IS ACCEPTABLE. (DELIVERABLE ITEM 4.3) 3.1.2 THE NASA TASK MONITOR (TM) WILL PROVIDE WRITTEN COMMENTS VIA EMAIL TO THE CONTRACTOR WITHIN 10 BUSINESS DAYS. THE CONTRACTOR SHALL INCORPORATE THE NASA TMS COMMENTS AND DELIVER A FINAL REQUIREMENTS DOCUMENT. MS WORD OR POWERPOINT FORMAT IS ACCEPTABLE. (DELIVERABLE ITEM 4.4) 3.2 CONCEPT DEFINITION 3.2.1 THE CONTRACTOR SHALL DEFINE THE POINT-OF-DEPARTURE PLANFORM AND OPEN ROTOR ENGINE CONCEPT. THE OPEN ROTOR ENGINE DEFINITION SHALL BE PROVIDED BY NASA (SEE GFI 5.1). OPEN ROTOR ENGINE INSTALLATION OPTIONS SHALL BE DEVELOPED AND ASSESSED. 3.2.2 THE CONTRACTOR SHALL PERFORM INITIAL AERODYNAMICS AND WEIGHTS ESTIMATION TO DETERMINE THE POINT-OF-DEPARTURE PLANFORM SIZE AND SHAPE. 3.2.3 THE CONTRACTOR SHALL CREATE A POINT-OF-DEPARTURE INTERNAL ARRANGEMENT DESIGN, INCLUDING MAJOR STRUCTURAL ELEMENTS, SUBSYSTEMS, AND PAYLOAD. 3.3 BWB PLANFORM DESIGN 3.3.1 THE CONTRACTOR SHALL FOCUS ON THE PROPULSION/AIRFRAME INTEGRATION OF THE SELECTED OPEN ROTOR ENGINE CONCEPT, INCLUDING AERODYNAMIC, STRUCTURAL AND POWERED EFFECTS OF THE OPEN ROTOR ENGINE INSTALLATION. THE POINT-OF-DEPARTURE CONCEPT SHALL BE REFINED BASED ON RESULTS OF THIS ANALYSIS. 3.3.2 THE CONTRACTOR SHALL ANALYZE THE R