Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Application of the aeroelastic analysis and design framework developed at Delft University Technology to a two aeroelastically tailored composite wings for flying demonstrator is presented. The objective process minimize structural mass wing while maintaining target cruise shape. For this purpose, jig shape parameterized becomes an integral part optimization, maintained by means constraint. Additionally strength, buckling, stability constraints, number other requirements have been introduced obtain feasible flight-worthy design. Two types were designed: reference wing. difference between in definition laminates comprising each was designed with symmetric-balanced laminates, symmetric-unbalanced used comparison performed terms laminate stiffness thickness distribution along span, twist, response covering elastic deformations, aerodynamic load distribution, root loads, showing significant reduction compared