Modeling and Simulation of Longitudinal Control Surfaces for a Flexible Generic Wide Body Aircraft

Aspects of the development process of a flight simulation environment within a Simulink Project are presented. In particular, special attention is given to the control surfaces for longitudinal motion for three different trailing-edge control surface configurations, which differ in number and spanwise size of the individual surfaces. The entire modeling and simulation process consists of four main parts: The selection of the geometry, the generation of consistent aerodynamic and structural models using CEASIOM, the computation of aerodynamic derivatives as well as structural normal modes with DATCOM and FEMAP, respectively, and finally the modeling of the interaction between the aerodynamic and structural states as presented in [1]. The performances of the implemented surfaces, when driven by a preliminary controller, are evaluated for gust load alleviation. The greatest decrease in the gust wing-bending moment is achieved by the configuration with the smallest and most numerous trailing-edge control surfaces.