Multi-Disciplinary and Multi-Objective Optimization for the design of a Over-the-Wing-Nacelle aircraft and a High-Altitude Long-Endurance unmanned vehicle
CHALLENGE - There is a need for the multidisciplinary optimization approach in the aerospace engineering industry due to complexity and narrow margins in design parameters. In an integrated computational environment, an unconventional aircraft design process is carried out in this work.
SOLUTION - An over the wing Nacelle is the model in the first example. The software modeFRONTIER was chosen as the optimization driver to help choose the best design, handling 77 design variables. FemWing is the chosen aerostructural tool for the MDO, which automatically performs high-fidelity analyses. FemWing improvements allow the management of extremely unconventional geometries. Objectives of the study are minimum empty weight and minimum fuel weight. The optimization of a solar powered HALE vehicle, or high-altitude, long-endurance unmanned vehicle is demonstrated in the second example. Objectives are maximum lift to drag ratio, minimum structural weight and maximum solar ﬂux. The entire optimization environment is made up of modeFRONTIER, FemWing, MSC Nastran, and Sunwing.
BENEFITS - MDO has been successfully applied for the preliminary design of two different aircraft by using the Pareto approach. MOGA II in modeFRONTIER is used in the explicit MOO, or multi-objective optimization process. The final HALE design shows marked improvement of +37% in lift to drag ratio.