Unsteady Aeroservoelastic Modeling of Flexible Wing Generic Transport Aircraft with Variable Camber Continuous Trailing Edge Flap

摘要

This paper presents a coupled flight dynamic and aeroservoelastic model of the NASA Generic Transport Model with increased wing flexibility and a continuous trailing edge flap system. The continuous trailing edge flap consists of multiple segments that are connected using a flexible skin material. Dynamic models of the aircraft, flexible wing, and flap system are aerodynamically coupled. Aerodynamics of the aircraft are modeled using a 3D vortex-lattice method. Unsteady aerodynamics of the flexible wing and flap system are modeled using modified strip theory based on quasi-steady vortex-lattice results and indicial concepts with unsteady aerodynamic corrections. The frequency-independent aeroelastic state-space system is formulated by means of aerodynamic lag states. A method for the realization of spatial turbulence and its application to flight dynamic simulation of flexible aircraft are described. The unsteady gust responses of the elastic aircraft and the flap system are also modeled using an indicial function approximation of the unsteady aerodynamic response. Compressibility effects on the unsteady aerodynamics are taken into account throughout the modeling effort using methods by Beddoes and Leishman et al. and a comparison is made with unsteady aerodynamics in incompressible flow. Simulation results, including flight dynamic and elastic responses, and aerodynamic hinge moments, are shown for flight dynamic maneuvers and gust profiles.