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Real-Time Adaptive Least-Squares Drag Minimization for Performance Adaptive Aeroelastic WingThis paper contains a simulation study of a real-time adaptive least-squares drag minimization algorithm for an aeroelastic model of a flexible wing aircraft. The aircraft model is based on the NASA Generic Transport Model (GTM). The wing structures incorporate a novel aerodynamic control surface known as the Variable Camber Continuous Trailing Edge Flap (VCCTEF). The drag minimization algorithm uses the Newton-Raphson method to find the optimal VCCTEF deflections for minimum drag in the context of an altitude-hold flight control mode at cruise conditions. The aerodynamic coefficient parameters used in this optimization method are identified in real-time using Recursive Least Squares (RLS). The results demonstrate the potential of the VCCTEF to improve aerodynamic efficiency for drag minimization for transport aircraft.
Document ID
20160008104
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Ferrier, Yvonne L. (SGT, Inc. Moffett Field, CA, United States)
Nguyen, Nhan T. (NASA Ames Research Center Moffett Field, CA United States)
Ting, Eric (Stinger Ghaffarian Technologies, Inc. Moffett Field, CA, United States)
Date Acquired
June 30, 2016
Publication Date
June 13, 2016
Subject Category
Aircraft Design, Testing And Performance
Aerodynamics
Report/Patent Number
ARC-E-DAA-TN32592
Meeting Information
Meeting: AVIATION 2016
Location: Washington, D.C.
Country: United States
Start Date: June 13, 2016
End Date: June 17, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNA14AA60C
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Aeroservoelasticity
Multi-Objective Control
Drag Minimization

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