Morphing consists of introducing smooth deformations to a structure outer mold line (OML), improving a desired performance metric. Because of the intrinsic and coupled nature of morphing actuators, metrics commonly utilized for typical aircraft selection are inadequate (e.g., the lift-to-drag ratio is not constant for range calculations). Therefore, there is a need to 1) identify the pitfalls of current performance metrics, 2) identify possible metrics that are more accurate for morphing aircraft, and 3) compare different non-morphing and morphing airfoils utilizing current and new metrics.  The performance parameters consist of standard or modified versions of the lift-to-drag ratio and range for either constant velocity or angle of attack. The authors explore the use of the expected value based on the angle of attack and velocity measurements from ADS-B surveillance technology for Cessna 172 Skyhawk. Multiple fixed airfoils are evaluated (NACA0012, NACA4415, NACA641212, and others) as well as the optimal morphed shapes for each. Class/Shape Transformation (CST) equations define each shape, and the design domain is constrained by a database of 1600 already existing airfoils. A reduced-order kinematics-based morphing airfoil represents the archetype of interest, while the parametric algorithm P3GA determines the non-dominated solutions for all flight conditions. The authors' goal is not to demonstrate that morphing is feasible but to motivate the utilization of adaptive technologies and demonstrate how engineers will incorporate this actuation method in concept selection.


Selection Criteria and Parametric Optimization of Camber Morphing Aircraft

Division / Sponsors: 
Aerospace Division

Paper Proceedings: https://asmedigitalcollection.asme.org/SMASIS/SMASIS2020/volume/84027

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