The aim of passive load alleviation via aeroelastic tailoring is the identification of the potential of different tailoring technologies. Hereby, detailed structural constraints like strength and stiffness are considered and sensitivities of structural design parameters regarding mass, bending and twist stiffness are identified. Especially a comprehensive consideration of structural details is aimed to evaluate the feasibility for load control.
Passive load alleviation through stiffened panels in post-buckling regime aims the determination of a meaningful area of application for post-buckled stiffened panel on wing covers. In order to achieve that, a new methodological approach for analysis and sizing has to be aimed and extensive knowledge about behavior of bond lines in unconventional structural environments has to be gained.
A technology assessment will assess the technological benefit for the overall aircraft. Furthermore, baseline models, including the structural technologies, for future, disciplinary investigations are developed and shared with other projects