Loads analysis and structural optimization of a high aspect ratio, composite wing aircraft

Abstract Composite structures have shown a prominent impact in the aircraft structural design. With an increasing shift towards incorporating more composite materials primary structure it is imperative to corresponding design tools simplify process. In present work, simplified implementation for optimization has been developed within DLR-AE (German Aerospace Centre, Institute of Aeroelasticity) automated aeroelastic framework cpacs-MONA. This paper presents results high aspect ratio wing model DLR project ATLAs. The generation almost all involved simulation models this study done using in-house tool ModGen. An trim analysis conducted various manoeuvre and gust conditions. A load selection process used determine most relevant sizing cases. comparison made between aluminium demonstrate favourable strength weight wing. alleviation procedure introduced calculation show further savings when utilized due reduction span wise bending moment.