Dynamic aeroelastic optimization of composite wings including fatigue considerations

The COVID-19 pandemic had a significant impact on the aviation industry with more than 60% reduction in the passenger traffic in the year 2020 compared to year 2019. The passenger traffic which is now expected to reach the 2019 level only around the year 2024 will still continue to grow but at a lower pace compared to the pre pandemic levels....

Design and testing of aeroelastically tailored composite wing under fatigue and gust loading including effect of fatigue on aeroelastic performance

The aim of the paper is to experimentally validate a numerical design methodology for optimizing composite wings subject to gust and fatigue loading requirements and to assess the effect of fatigue on the aeroelastic performance of the wing. Traditionally, to account for fatigue in composite design, a knockdown factor on the maximum stress...

Multi-Fidelity Design of an Aeroelastically Tailored Composite Wing for Dynamic Wind-Tunnel Testing

Aeroelastic tailoring offers an effective way to exploit the anisotropic properties of the composite materials used in lightweight aerospace structures. This paper presents a design methodology for experimental wings that employ a typical wingbox structure. The proposed methodology combines three different analysis tools: Proteus, a low-fidelity...

Aeroelastic optimization of composite wings including fatigue loading requirements

An analytical model to predict the fatigue life of a composite laminate is formulated. The model calculates stresses in each ply using classical lamination theory, degrades the residual strength using the linear wear-out law and predicts failure based on Tsai Wu failure theory. The cycles to failure are predicted using the updated cycle-by...

Preliminary aeroelastic design of composite wings subjected to critical gust loads

Including a gust analysis in an optimization framework is computationally expensive as the critical load cases are not known a priori and hence a large number of points within the flight envelope have to be analyzed. Model order reduction techniques can provide significant improvement in computational efficiency of an aeroelastic analysis. In...

Streamlining Cross-Organizational Aircraft Development: Results from the AGILE Project

The research and innovation AGILE project developed the next generation of aircraft Multidisciplinary Design and Optimization processes, which target significant reductions in aircraft development costs and time to market, leading to more cost-effective and greener aircraft solutions. The high level objective is the...

Dynamic aeroelastic tailoring of a strut braced wing including fatigue loads

High aspect ratio strut braced aircraft can significantly reduce the induced drag. The inherent anisotropic behaviour of the composite material along with their weight saving potential can improve the performance of the aircraft during the flight. Thus, a composite strut braced aircraft is one of the promising candidates to achieve the...

Aeroelastic optimization of composite wings subjected to fatigue loads

An analytical model to predict the fatigue life of a composite laminate is discussed. It is based on the method developed by Kassapoglou to predict fatigue failure. The analytical model calculates stresses in each ply using classical lamination theory, degrades the residual strength using the linear degradation law and predicts failure based...

Including aeroelastic tailoring in the conceptual design process of a composite strut braced wing

High aspect ratio strut braced aircraft can significantly reduce the induced drag. The inherent anisotropic behaviour of the composite material along with their weight saving potential can improve the performance of the aircraft during the flight. Thus, a composite strut braced aircraft is one of the promising candidates to achieve the targets...

Preliminary aeroelastic design framework for composite wings subjected to gust loads

Including a gust analysis in an optimization framework is computationally inefficient as the critical load cases are not known a priori and hence a large number of points within the flight envelope have to be analyzed. Model order reduction techniques can provide significant improvement in computational efficiency of an aeroelastic analysis. In...