Modal Design Optimization for Panel Flutter and Buckling ifasd2024 Tracking Number 2Presentation: Session: Flutter 2 Room: Room 1.6 Session start: 09:40 Wed 19 Jun 2024 Kevin McHugh kevin.mchugh.3@us.af.mil Affifliation: US Air Force Research Lab Cate Leszcz Cate.leszcz@colorado.edu Affifliation: University of Colorado, Boulder Joshua Deaton joshua.deaton@us.af.mil Affifliation: US Air Force Research Lab Topics: - Computational Aeroelasticity (High and low fidelity (un)coupled analysis methods:), - Reduced Order Modeling (High and low fidelity (un)coupled analysis methods:), - High Speed Structural Dynamics Phenomena (High and low fidelity (un)coupled analysis methods:) Abstract: This work investigates a new method to design aircraft skin panels to minimize weight while providing sufficient strength to withstand both buckling due to aerodynamic heating and flutter due to dynamic pressure over the panel. In this work, mass minimization is done via an optimization of panel thickness distribution as opposed to fill-void techniques or methods of adding discrete stiffeners found in the literature or in practice. The thickness distribution and therefore optimization problem is further reduced in numerical order by utilizing a Galerkin projection of global thickness basis functions. The developed tool results in a 6-17% reduction in weight for an optimized panel for thermal buckling stability when compared to the optimally thin flat panel. |