The interaction between active aeroelastic control and structural tailoring in aeroservoelastic wing design

Abstract This paper presents an analysis of the interaction and trade-off between active aeroelastic control passive structural tailoring on a free-flying fully flexible aircraft model. Both technologies are included in preliminary design typical transport configuration with conventional surface layout containing trailing edge surfaces spoilers. The is facilitated by exploiting anisotropic properties composite materials to steer static dynamic behaviour. Active implemented scheduled deflections redistributing aerodynamic loads during manoeuvres achieve manoeuvre load alleviation feed-forward law for gust alleviation. panel-based modelling spoiler improved correction spatial distribution boundary condition derived from higher fidelity simulation data. optimisation laws requires consideration constraints actuation system, namely rate deflection saturation, nonlinear manner. alleviation, investigated basis results different aeroservoelastic optimisations. Therefore primary wing structure simultaneously optimised individual being activated or deactivated, resulting eight structures. combined optimisations reveal significant differences. potentials can only be optimally exploited simultaneous optimisation. concludes study sensitivity major findings respect knockdown factor failure applied material properties. A substantial shift effectiveness observed increased allowables more hence less stiff designs.