Aircraft wings are a compromise that allows the aircraft to fly at a range of flight conditions, but the performance at each condition is sub-optimal. The ability of a wing surface to change its geometry during flight has interested researchers and designers over the years as this reduces the design compromises required. Morphing is the short form for metamorphose; however, there is neither an exact definition nor an agreement between the researchers about the type or the extent of the geometrical changes necessary to qualify an aircraft for the title ‘shape morphing.’ Geometrical parameters that can be affected by morphing solutions can be categorized into: planform alteration (span, sweep, and chord), out-of-plane transformation (twist, dihedral/gull, and span-wise bending), and airfoil adjustment (camber and thickness). Changing the wing shape or geometry is not new. Historically, morphing solutions always led to penalties in terms of cost, complexity, or weight, although in certain circumstances, thes...

A Review of Morphing Aircraft

Review of state of the art in smart rotor control research for wind turbines

A review of modelling and analysis of morphing wings

Static and dynamic aeroelasticity considerations are a particularly important component of airframe design because they often control safety and performance. Consequently, the impact of uncertainty on aeroelastic response prediction has begun to receive substantial attention in the research literature. In this paper, general sources of uncertainty that complicate airframe design and testing are briefly described. Recent applications of uncertainty quantification to various aeroelastic problems, for example, flutter flight testing, prediction of limit-cycle oscillations, and design optimization with aeroelastic constraints, are reviewed with an emphasis on new physical insights and promising paths toward improved design methods that have resulted from these studies. Several challenges and needs are explored to suggest future steps that will enable practical application of uncertainty quantification in aeroelasticity design and certification.

Uncertainty Quantification in Aeroelasticity: Recent Results and Research Challenges

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

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

Transonic aeroelastic wind-tunnel models simulating geometric and dynamic properties of lightweight, highly swept hypersonic lifting surfaces have been designed, fabricated, and tested. The aeroelastic model designs were consistent with preliminary designs of lifting surfaces for single-stage-to-orbit vehicles. The models were tested in the NASA Langley Research Center's Transonic Dynamics Tunnel. This article summarizes the design and tests conducted for each of the two models. Wind-tunnel test results are presented showing aeroelastic instability boundaries. Aeroelastic analyses, conducted for correlation with wind-tunnel results, are also presented.

Transonic aeroelastic models of highly swept hypersonic lifting surfaces

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

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