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Flight Test of an Adaptive Configuration Optimization System for Transport AircraftA NASA Dryden Flight Research Center program explores the practical application of real-time adaptive configuration optimization for enhanced transport performance on an L-1011 aircraft. This approach is based on calculation of incremental drag from forced-response, symmetric, outboard aileron maneuvers. In real-time operation, the symmetric outboard aileron deflection is directly optimized, and the horizontal stabilator and angle of attack are indirectly optimized. A flight experiment has been conducted from an onboard research engineering test station, and flight research results are presented herein. The optimization system has demonstrated the capability of determining the minimum drag configuration of the aircraft in real time. The drag-minimization algorithm is capable of identifying drag to approximately a one-drag-count level. Optimizing the symmetric outboard aileron position realizes a drag reduction of 2-3 drag counts (approximately 1 percent). Algorithm analysis of maneuvers indicate that two-sided raised-cosine maneuvers improve definition of the symmetric outboard aileron drag effect, thereby improving analysis results and consistency. Ramp maneuvers provide a more even distribution of data collection as a function of excitation deflection than raised-cosine maneuvers provide. A commercial operational system would require airdata calculations and normal output of current inertial navigation systems; engine pressure ratio measurements would be optional.
Document ID
19990019435
Acquisition Source
Armstrong Flight Research Center
Document Type
Reprint (Version printed in journal)
Authors
Gilyard, Glenn B. (NASA Dryden Flight Research Center Edwards, CA United States)
Georgie, Jennifer (NASA Dryden Flight Research Center Edwards, CA United States)
Barnicki, Joseph S. (NASA Dryden Flight Research Center Edwards, CA United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1999
Subject Category
Aircraft Stability And Control
Report/Patent Number
H-2284
NAS 1.15:206569
AIAA Paper 99-0831
NASA/TM-1999-206569
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 11, 1999
End Date: January 14, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 522-16-14-00-39
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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