Real-Time Adaptive Least-Squares Drag Minimization for Performance Adaptive Aeroelastic Wing

Ferrier, Yvonne L.; Nguyen, Nhan T.; Ting, Eric B.

doi:10.2514/6.2016-3567

Cited by 26 publications

(15 citation statements)

References 11 publications

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“…Preceding this work was extensive research on the control and drag reduction of morphing wings. Particular focus was directed at the actuation of variable trailing edge [7][8][9][10][11]. flap control system.…”

Section: Literature Reviewmentioning

confidence: 99%

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Design, Implementation And Experimental Testing Of An Inertial Sensor System To Quantify Wing Deflection

Schirmer

Steck

Chakravarthy

2019

AIAA Scitech 2019 Forum

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creative mind. However, the process of turning such a vision into reality is one that often necessitates the help and support of many others who deserve credit and recognition. I want to thank my father whose ingenuity has been a lifelong inspiration to me and who played an integral role in the early conceptual stages of this project, particularly during the initial preliminary testing. Throughout my time at Wichita State University I had the pleasure of working with many individuals who have positively influenced me in one way or another and I owe my sincere gratitude to them all. I would like to recognize the GAFL research group for the outstanding team work and particularly Alok Menon, who has been a true friend and tremendous help throughout every phase of the project. I want to give special thanks to committee chair Dr. James Steck, for his support, guidance, and encouragement during this research. I also want to express my appreciation to committee members Dr. Buerge, Dr. Chakravarthy, Dr. Jewell and Dr. Sawan for their willingness to devote their time and effort and provide me with invaluable input. I would like to give thanks to Dr. Suresh Keshavanarayana and his graduate student Dmitrii Ivanov for the help and allowing me to use the WSU Flight Structures Lab and equipment as well as NIAR, John Laffen and his staff for giving me the opportunity to test in the WSU Walter Beech Wind Tunnel. Finally, I want to thank my wife for her patience, her sacrifices and her support throughout this journey. In the end I would not have accomplished this without the help of many others.

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Section: Literature Reviewmentioning

confidence: 99%

“…7) does not change and continues to be the acceleration as sensed by the accelerometer. The system matrices are also not affected by the change in how the measurement is computed.…”

mentioning

confidence: 99%

Design, Implementation And Experimental Testing Of An Inertial Sensor System To Quantify Wing Deflection

Schirmer

Steck

Chakravarthy

2019

AIAA Scitech 2019 Forum

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“…This strategy has been examined in a recent study which proposes a real-time model identification technique based on the recursive least-squares method to construct an on-line surrogate aerodynamic model of a flexible wing aircraft. 9 The surrogate aerodynamic model is then used in a gradient optimization to compute the optimal setting of the VCCTEF that minimizes the cruise drag while maintaining the aircraft flight path.…”

Section: Introductionmentioning

confidence: 99%

Real-Time Adaptive Drag Minimization Wind Tunnel Investigation of a Flexible Wing with Variable Camber Continuous Trailing Edge Flap System

Nguyen

Cramer

Hashemi

et al. 2019

AIAA Aviation 2019 Forum

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This paper reports the results of a recently completed real-time adaptive drag minimization wind tunnel investigation of a highly flexible wing wind tunnel model equipped with the Variable Camber Continuous Trailing Flap (VCCTEF) technology at the University of Washington Aeronautical Laboratory (UWAL). The wind tunnel investigation is funded by NASA SBIR Phase II contract with Scientific Systems Company, Inc. (SSCI) and University of Washington (UW) as a subcontractor. The wind tunnel model is a sub-scale Common Research Model (CRM) wing constructed of foam core and fiberglass skin and is aeroelastically scaled to achieve a wing tip deflection of 10% of the wing semi-span which represents a typical wing tip deflection for a modern transport such as Boeing 787. The jig-shape twist of the CRM wing is optimized using a CART3D aero-structural model to achieve the minimum induced drag for the design cruise lift coefficient of 0.5. The wing is equipped with two chordwise cambered segments for each of the six spanwise flap sections for a total of 12 individual flap segments that comprise the VCCTEF system. Each of the 12 flap segments is actively controlled by an electric servo-actuator. The real-time adaptive drag optimization strategy includes an on-board aerodynamic model identification, a model excitation, and a real-time drag optimization. The on-board aerodynamic model is constructed parametrically as a function of the angle of attack and flap positions to model the lift and drag coefficients of the wing. The lift coefficient models include a linear model and a second-order model. The drag coefficient models include a quadratic model and a higher-order up to 6 th-order model to accurately model the drag coefficient at high angles of attack. The onboard aerodynamic model identification includes a recursive least-squares

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“…1, provides active wing shaping control to improve the aerodynamic efficiency throughout a flight envelope. Initial studies indicate the ability of the VCCTEF to reduce drag for significant fuel savings 7,8 and the ability to provide flutter mode suppression and maneuver load alleviation in combination with drag cognizant control. 2,9 This paper describes the formulation of an aeroservoelastic model of the GTM with the VCCTEF and the application of a multi-objective flight control framework focusing on gust load alleviation for an altitude-hold flight control mode in symmetric flight conditions.…”

Section: Introductionmentioning

confidence: 99%

“…4 2. Next to these objectives a real-time drag minimization approach can be included in the control design 8.…”

mentioning

confidence: 99%

Active Gust Load Alleviation of High-Aspect Ratio Flexible Wing Aircraft

Ferrier

Nguyen

Ting

et al. 2018

2018 AIAA Guidance, Navigation, and Control Conference

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This paper presents a novel active gust load alleviation approach within a multi-objective flight control framework developed by NASA for a flexible wing aircraft. The aircraft model is based on the NASA Generic Transport Model (GTM). The wing structures incorporate an aerodynamic control surface known as the Variable Camber Continuous Trailing Edge Flap (VCCTEF). Previous work already showed the ability of the VCCTEF to perform aeroelastic mode suppression, drag minimization and maneuver load alleviation in a multi-objective flight control framework. In this paper, the multi-objective flight control framework is extended to include active gust load alleviation. A Linear-Quadratic Gaussian (LQG) controller is augmented with Model Reference Adaptive Control (MRAC) to provide active gust load alleviation. Disturbance estimation is done using an Extended State Observer (ESO) to support the design of the active gust load alleviation controller. The results demonstrate the potential of active gust load alleviation within a multi-objective flight control framework for a high-aspect ratio flexible wing aircraft embodied with the VCCTEF.

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Real-Time Adaptive Least-Squares Drag Minimization for Performance Adaptive Aeroelastic Wing

Cited by 26 publications

References 11 publications

Design, Implementation And Experimental Testing Of An Inertial Sensor System To Quantify Wing Deflection

Design, Implementation And Experimental Testing Of An Inertial Sensor System To Quantify Wing Deflection

Real-Time Adaptive Drag Minimization Wind Tunnel Investigation of a Flexible Wing with Variable Camber Continuous Trailing Edge Flap System

Active Gust Load Alleviation of High-Aspect Ratio Flexible Wing Aircraft

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