A constructal aeroelastic design approach for cross-section configuration of "flying wing aircraft"
A uniform stress distribution can improve the aeroelastic flight envelope of flying wing aircraft through the structure. We investigate the effect of spar and rib design on a flying wing aircraft’s stress distribution and aeroelastic behavior. We apply the principles of Constructal law, ensuring that by avoiding the obstruction of stress pathways, we achieve the most efficient and stable design for wings. To investigate the stress distribution and stability of the flying wing aircraft, we employ the software Gmsh and VABS (Variational Asymptotic Beam Sectional Analysis), and code NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft). The findings suggest that specific wing cross-section designs promote even stress distribution, thereby enhancing aeroelastic stability. Configurations exhibiting higher flutter speeds demonstrate a more seamless and smoother stress flow within the wing’s structure.
