Analysis of the Performance Potential of a Single Aisle Transport Aircraft with a New High-lift Differential Flap System

Abstract

This documentation deals with the development of a non-linear aircraft model of the Airbus A320 with Matlab/Simulink that provides the possibility to simulate differential and continuous flap setting as an improvement of present high-lift devices. As a second core theme of the presented diploma thesis, the validated simulation model is equipped with a newly developed controller for three-dimensional landing procedures. The first sections of the documentaiton concentrate on the high-lift system of the A320 with its five slats per wing as leading edge devices as well as in- and outboard, single-slotted flaps as trailing edge devices. It is shown that the advantages of this mechanically simpler but still aerodynamically effective construction outweigh their deficits in comparison to more complex constructions. The realisation of the slat/flap system and other control surfaces within the model as well as the implementation of the highly precise aerodynamic parameter calculation is explaned in detail. The validation of the Matlab/Simulink model with a non-linear Fortran model of the A320 proves the high quality of the developed simulation model. The second part of this documentation is dealing with the necessary autopilot functions during landing procedures and the consequent control structure. A controller for the precise guidance of the aircraft on a generated trajectory and simultaneous attitude stabilisation is designed and tested for differently curved approaches. The analysis of different simulations verify a very good quality of the navigational performance and mainly satisfying control results for the dynamic aircraft response. The documentation is rounded off by an outlook concerning possible improvements and modifications of both, the aircraft model and the controller for curved approaches.