Set-up of a generic aeroelastic simulation model for demonstration and software testing purposes

Kurzfassung

This thesis presents the development and comprehensive analysis of an open-source aeroelastic model for the Douglas DC-3 with some modifications. The model serves as a platform for software testing, capturing essential aeroelastic phenomena. It features a conventional configuration with two engines, control surfaces, and a wing with a leading-edge sweep angle of 15.5°, dihedral angle of 5°, aspect ratio of 9.2, and cambered airfoil, operating in a subsonic regime. The development process included finite element modeling using beam elements, aerodynamic modeling with the Doublet Lattice Method (DLM), and mass modeling, including a complex fuel mass model. Four distinct mass configurations were analyzed. Trim case analyses were performed using both Loads Kernel and SOL144 in MSC Nastran, revealing significant differences between rigid and flexible configurations. Maneuver load analyses were conducted exclusively using Loads Kernel. Additionally, gust loads were studied using the (1-cos) Discrete Gust Model, demonstrating coupling with the short-period mode due to high static margin. Flutter checks showed matching results between Loads Kernel and MSC Nastran, with flutter speeds of 195 m/s and 203 m/s, respectively, confirming the model's plausibility for aeroelastic analysis.