The Active Aeroelastic Wing (AAW) Flight Research Program's (Pendleton, E., Griffin, K., Kehoe, M., and Perry, B., A Flight Research Program for Active Aeroelastic Wing Technology, AIAA Paper 96-1574, April 1996 and Pendleton, E., Bessette, D., Field, P., Miller, G., and Griffin, K., The Active Aeroelastic Wing Flight Research Program, AIAA Paper 98-1972, April 1998) technical content is presented and analytical model development is summarized. Goals of the AAW flight research program are to demonstrate, in full scale, key AAW parameters and to measure the aerodynamic, structural, and flight control characteristics associated with AAW. Design guidance, derived from the results of this benchmark flight program, will be provided for implementation on future aircraft designs.

Active Aeroelastic Wing Flight Research Program: Technical Program and Model Analytical Development

Active flutter suppression, which is a part of the group of flight vehicle technologies known as active controls, is an important contributor to the effective solution of aeroelastic instability pr...

https://arc.aiaa.org/doi/pdf/10.2514/1.C034442

Aircraft Active Flutter Suppression: State of the Art and Technology Maturation Needs

This paper describes the use of full-span deforming control surfaces (including controlled chordwise cambering of the wing) to provide effective subsonic induced drag control with precise control of the spanwise lift distribution. Examples of these proposed controllers are smart, adaptive actuators for advanced unmanned air vehicle concepts. Reshaping the wing spanwise lift distribution with aeroelastic tailoring concepts is shown to reduce induced drag at high airspeeds. Active controllers such as conventional ailerons or leading-edge devices also reduce induced drag if they have a tailored spanwise deflection pattern; the required deflections of these surfaces depend on wing deformation and can be so large that they are not practical. Combining wing aeroelastic stiffness tailoring with active control surface design to create a control-friendly structure reduces induced drag and requires only small controller inputs. An exact solution for the actuator deflections to generate an elliptical lift distribution for the aeroelastic wing, for minimum induced drag, is discussed. A formal optimization problem is posed for cases in which multiple surfaces are used to control drag. This controller optimization solution is complicated because aeroelastic phenomena, such as control reversal, limit the effectiveness of some actuators at high speed.

Induced Drag Reduction Using Aeroelastic Tailoring with Adaptive Control Surfaces

[] This paper summarizes the development and flight results of the X-53, better known as the Active Aeroelastic Wing (AAW) F/A-18 Flight Research Program.. Goals of the AAW Flight Research Program were to demonstrate, in full scale, key AAW parameters and to measure the aerodynamic, structural, and flight control characteristics associated with AAW. The AAW program’s technical content is discussed and some lessons learned and conclusions are described.

The x-53 a summary of the active aeroelastic wing flight research program

A flight research program for active aeroelastic wing technology

The Active Flexible Wing is an integrated technology wing concept of special interest to systems requiring high maneuverability at high speed. The following article examines the results from an application of the Active Flexible Wing (AFW) concept to an F-16 Agile Falcon, low-speed aeroelastic model. The article also summarizes, for archival purposes, design and fabrication procedures typical for construction of low-speed aeroelastic models. The Active Flexible Wing concept is applied to a 4 scale model design based upon full scale preliminary wing design studies conducted for the U.S. Air Force F-16 Agile Falcon fighter program. The model is equipped with multiple leading- and trailing-edge control surfaces. Wind tunnel test results are presented showing wing control power increases generated through the use of the leading- and trailing-edge control surfaces in conjunction with increased wing flexibility. The results show that the Active Flexible Wing concept is a viable concept for the Agile Falcon planform and that a leading-edge outboard control surface can be a particularly powerful control power effector.

Application of Active Flexible Wing Technology to the

The Active Flexible Wing is an integrated technology wing concept of special interest to systems requiring high maneuverability at high speed. The following article examines the results from an application of the Active Flexible Wing (AFW) concept to an F-16 Agile Falcon, low-speed aeroelastic model. The article also summarizes, for archival purposes, design and fabrication procedures typical for construction of low-speed aeroelastic models. The Active Flexible Wing concept is applied to a 4 scale model design based upon full scale preliminary wing design studies conducted for the U.S. Air Force F-16 Agile Falcon fighter program. The model is equipped with multiple leadingand trailing-edge control surfaces. Wind tunnel test results are presented showing wing control power increases generated through the use of the leadingand trailing-edge control surfaces in conjunction with increased wing flexibility. The results show that the Active Flexible Wing concept is a viable concept for the Agile Falcon planform and that a leading-edge outboard control surface can be a particularly powerful control power effector.

Application of Active Flexible Wing technology to the Agile Falcon

An application of the active flexible wing concept to an F-16 derivative wing model

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Application of Active Flexible Wing Technology to the

Application of Active Flexible Wing technology to the Agile Falcon

An application of the active flexible wing concept to an F-16 derivative wing model