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

Abstract

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