Gust Loads Calculation for a Flying Wing Configuration

Abstract

This work presents results of dynamic 1-cos gust load simulations for a flying wing configuration. The in-house toolbox Loads Kernel is used for the loads analysis of the free flying aircraft. Flight mechanical characteristics are captured application of a non-linear equation of motion in the time domain. The underlying aerodynamic methods are the Vortex Lattice and the Doublet Lattice Method with a rational function approximation (RFA) for unsteady simulations in the time domain. The structural model was created using DLR's parametric ModGen/Nastran design process. The structure is optimized for minimum structural weight with typical design load cases including maneuver, gust and landing loads. In this paper, the focus lies on gust encounters and the flight characteristics of the MULDICON, which differs from classical configurations. It involves a pitching motion and a pronounced penetration effect when the aircraft enters the gust field. Finally, a flight controller is designed to increase the pitching stability. It is shown that the loads during a gust encounter increase moderately. The influence on the structural weight is small as the layout is very robust and the required material thickness is below the minimum thickness in most areas.