IGF::OT::IGF NRA INTEGRATED ADAPTIVE WING TECHNOLOGY MATURATION. THE PURPOSE OF THIS COOPERATIVE AGREEMENT IS TO CONDUCT A SHARED RESEARCH PROJECT THAT WILL LEAD TO REAL-TIME DRAG MINIMIZATION IN-FLIGHT BY SIMULTANEOUSLY CONTROLLING SPANWISE/CHORDWISE WING SHAPE WHILE PROVIDING STRUCTURAL MODAL SUPPRESSION AND ACTIVE ALLEVIATION OF GUST AND MANEUVER LOADS. THIS COOPERATIVE AGREEMENT WILL ADVANCE THE TECHNOLOGY DEVELOPMENTS AND RESEARCH WHICH HAVE BEEN PERFORMED ON A VARIETY OF BOEING/GOVERNMENT RESEARCH ACTIVITIES INCLUDING: (1) ROBUST AND ADAPTIVE FLIGHT CONTROL TECHNOLOGY FOR VERY FLEXIBLE AERIAL VEHICLES SUCH AS VULTURE PHANTOM EYE AND HIGH-SPEED CIVIL TRANSPORT AND CONTROL LAW (CLAW) FOR DRAG REDUCTION AND WING/BODY LOAD ALLEVIATION AS IMPLEMENTED ON THE BOEING 787 AND FOR STRUCTURAL MODE SUPPRESSION AND LOAD ALLEVIATION AS IMPLEMENTED ON OTHER BOEING TRANSPORTS (2) NOVEL CONTROL EFFECTORS AND ADVANCED ACTUATORS TECHNOLOGY AS DEMONSTRATED IN A SUCCESSFUL FLIGHT TEST USING AN ADAPTIVE TRAILING EDGE AND SHAPE MEMORY ADVANCED SENSOR TECHNOLOGY INCLUDING AEROELASTICITY MEASUREMENT THAT WAS DEMONSTRATED IN A CONFIGURABLE SYSTEM CAPABLE OF VERY ACCURATE REAL-TIME MEASUREMENT OF AIRCRAFT WING AND BODY. THE SPECIFIC OBJECTIVE IS TO DEVELOP AN ADAPTIVE WING STRUCTURAL DESIGN ALONG WITH ASSOCIATED SENSORS CONTROL EFFECTORS AND CONTROL SYSTEMS THAT REDUCES DRAG AND MAINTAINS AEROELASTIC STABILITY. AN AEROELASTICALLY SCALED WIND-TUNNEL MODEL WILL BE DESIGNED FABRICATED AND TESTED IN A NASA LANGLEY WIND TUNNEL FACILITY TO VALIDATE THE DESIGN.

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