Rear fuselage stiffness design of T-tail

摘要

The present work is mainly involved in the fuselage stiffness design. It investigates a relationship between the flutter speed of a T-tail and fuselage support stiffness through optimization, which maximizes the critical flutter speed with the weight constraint. Circumferentially Uniform Stiffness and Cir-cumferentially Asymmetrical Stiffness composite thickness of the fuselage skin are taken as design variables. According to the flutter characteristics of a T-tail, 1-order complex respond surface of the generalized additional unsteady aerodynamic forces is constructed by least squares. It enters flutter solutions and improves computational efficiency. And the optimal results show CAS skin of the fuselage more obviously benefits aeroelastic tailoring than that of CUS, under the same weight. When the flutter speed is greater than 200 m/s, the stiffness distributions of the rear fuselage are suitable for the practical structures. This present research provides a reference for the detailed stiffness design of the rear fuselage.