A Physics-Based Approach for Aeroservoelastic Wing Sizing in Conceptual Aircraft Design

Abstract

In many cases wing sizing in conceptual aircraft design is carried out by semi-empirical methods, or with static load cases and a rigid airframe structure. But the disciplines aerodynamics, structures and flight dynamics catch the impact of dynamic aircraft behavior on the mass of the flexible wing only when assessed combined. By taking coupled physics effects into account at the early design stage, technologies like gust and maneuver load alleviation can be evaluated. Overall aircraft efficiency benefits are expected. This paper presents a process for the integration of flight control and aeroelasticity into conceptual aircraft design. The process uses the tool ASWING to perform an unsteady lifting linean open source simulation library are used to perform a controlled six-degree-of-freedom flight simulation. The use case is set up for a long range transport aircraft design. Elements of an open source simulation library are used to perform a controlled six-degree-of-freedom flight simulation. The sizing process is calibrated with higher fidelity structure model. A dynamic validation of the lower fidelity behavior is provided by a higher fidelity approach, using unsteady Reynolds-Averaged NavierStokes equations coupled with a structural modal ansatz in a free flight simulation. The presented process enables the assessment of how specific flight control laws and layouts change the optimum aircraft design.