Flight Dynamics and Structural Load Distribution for a Damaged Aircraft

When an aircraft is damaged, it can lead to asymmetries in the aerodynamics and inertia of the aircraft. These asymmetries complicate the modeling, ight simulation, and control of the aircraft. The aerodynamics is further complicated by the introduction of nonlinearities and coupling between longitudinal and lateral aerodynamic forces. Aerodynamic coe cients are calculated that account for these non-linearities and couplings. The method is able to utilize numerical or experimental data. In addition, the changes in the mass distribution, the center of gravity, and the inertia matrix are taken into account. The ight dynamics model is used to analyze the non-linear response, the linear stability and the ight loads for an aircraft.