Session 2: Optimisation

Multidisciplinary design optimisation of actively controlled composite wings is a significant challenge because of the very large design space in terms of design variables and constraints. On the other hand, the computational complexity and time required for the aeroservoelastic analysis of a transport aircraft wing is high. This contradiction between computational time, computational accuracy and the number of required analyses can be solved with multi-fidelity analysis. This type of analysis is traditionally sequential in the design process of an aircraft. We would like to share our views on multi-fidelity analysis in this presentation where will make a case for continuous exchange of information between the various fidelity levels of a given discipline.

Potential and limitations within conceptual aircraft design for the optimization of a flexible wing with and without load alleviation.

Load alleviation is a technology that enhances fuel efficiency of an aircraft by reducing the wing mass. Reducing aerodynamic loads on the transonic, swept outer wing allows for high aspect ratio wings in novel designs. Load alleviation impacts the optimal wing layout and should be considered already in the conceptual design phase.

This talk shows a conceptual aircraft design process integrating relevant disciplines through simplified but physics-based models. In particular the flexible wing is integrated. The results of a surrogate based optimization for a long range aircraft with and without load alleviation are shown, the technology potential and limitations within the design space discussed. An outlook on the related work in the UPwing EU-project will be provided, focusing on assessment and optimization of high aspect- ratio, flexible wings for a short-medium range aircraft.

Bilevel Multidisciplinary Design Optimization Illustrated on High-Aspect Ratio Strut-Braced Wings