Numerically Efficient Three-Dimensional Fluid-Structure Interaction Analysis for Composite Camber Morphing Aerostructures

Abstract

This paper presents a newly developed three-dimensional Fluid-Structure Interaction (FSI) routine for the Fish Bone Active Camber (FishBAC) concept that couples a three-dimensional Lifting-Line theory analysis to a two-dimensional viscous corrected panel method (XFOIL) to create a viscous corrected three-dimensional wing aerodynamic solver. This aerodynamic model is then coupled to a previously developed multi-component Mindlin-Reissner plate model based composite analysis routine for the FishBAC morphing device. The methodology is explained, and predictions are validated against existing modeling tools. The FSI model developed in this paper shows good agreement when compared against other structural, aerodynamic and FSI tools. Additionally, results show the FishBAC's ability to improve aerodynamic performance at a wide range of operating conditions.

Recent developments in the aeroelasticity of morphing aircraft

“…In addition, the drag coefficient of the airfoil and the deformation in the flexible skin increased sharply at speeds beyond a certain value. Rivero et al [154] developed a 3D FSI routine for the FishBAC concept that coupled a 2D viscous corrected panel method (XFOIL) with a 3D Lifting-Line theory analysis to create a viscous corrected 3D wing aerodynamic solver. A previously developed multi-component Mindlin-Reissner plate model based composite analysis routine was then coupled with this aerodynamic model for the FishBAC morphing device.…”

“…Most of the studies belong to aeroelastic stability theme with a very limited number under aeroelastic control. For both themes, the majority of studies are numerical analysis using FE software for structural modeling with beam [136,138,139] and plate models [125,154] being the most popular. The DLM [126-129, 132, 140, 141, 155, 157] and panel method (2D and 3D) [130, 134-136, 139, 143-145, 147, 149, 150, 153-156], VLM [152,159,160], nonlinear lifting line theory [124], CFD [119] and thin airfoil theory [161] were used for aerodynamic modeling.…”