Loads and Structural Optimization Process for Composite Long Range Transport Aircraft Configuration

Abstract

Background: The consideration of composite design in an early design phase has become more and more necessary in aircraft design. In the scope of multidisciplinary optimisation, a composite aeroelastic reference model is often desired to investigate multidisciplinary effects on a near-industrial application. Objective: The aim is to generate a benchmark aeroelastic model by developing a robust design process for composite configurations. Method: This is done by using a continuous gradient based optimisation with lamination parameters as design variables followed by a discrete stacking sequence retrieval combined with a comprehensive load analysis routine comprising manoeuvre, gust, landing loads and a manoeuvre loads alleviation system. Simulation Models: The process utilises a GFEM/Dynamic, a DLM and a condensed FEM model based on the reference XRF1 configuration. Results: Results presented show the optimised wing-box design, comparing the effect of a manoeuvre load alleviation system, the effect of including blending constraints in the optimisation, and the change of the structrual design when moving to a stacking sequence design.