Analysis of slender thin-walled anisotropic box-beams including local stiffness and coupling effects

• Published in: Aircraft Engineering and Aerospace Technology 2014-07, Vol.86 (4), p.345-355
• Main Authors: Cestino, Enrico, Frulla, Giacomo
• Format: Article
• Language: English
• Subjects: Aeroelastic stability; Aeroelasticity; Aerospace engineering; Aircraft; Aluminum; Anisotropy; Approximation; Beam theory (structures); Box beams; Composite beams; Composite wings; Configurations; Coupling; Couplings; Design analysis; Design engineering; Design modifications; Dynamic stability; Engineering; Equivalence; Fiber composites; Finite element method; Hypotheses; Mathematical analysis; Mathematical models; Preliminary designs; Sandwich structures; Stiffness; Structural weight; Theory; Weight reduction; Wing boxes
• ISSN: 1748-8842; 0002-2667; 1758-4213
• DOI: 10.1108/AEAT-10-2012-0159

Purpose – This study aims to analyse slender thin-walled anisotropic box-beams. Fiber-reinforced laminated composites could play an important role in the design of current and future generations of innovative civil aircrafts and unconventional unmanned configurations. The tailoring characteristics of these composites not only improve the structural performance, and thus reduce the structural weight, but also allow possible material couplings to be made. Static and dynamic aeroelastic stability can be altered by these couplings. It is, therefore, necessary to use an accurate and computationally efficient beam model during the preliminary design phase. Design/methodology/approach – A proper structural beam scheme, which is a modification of a previous first-level approximation scheme, has been adopted. The effect of local laminate stiffness has been investigated to check the possibility of extending the analytical approximation to different structural configurations. The equivalent stiffness has been evaluated for both the case of an isotropic configuration and for simple thin-walled laminated or stiffened sections by introducing classical thin-walled assumptions and the classical beam theory for an equivalent system. Coupling effects have also been included. The equivalent analytical and finite element beam behaviour has been determined and compared to validate the considered analytical stiffness relations that are useful in the preliminary design phase. Findings – The work has analyzed different configurations and highlighted the effect of flexural/torsion couplings and a local stiffness effect on the global behaviour of the structure. Three types of configurations have been considered, namely, a composite wing box configuration, with and without coupling effects; a wing box configuration with sandwich and cellular constructions; and a wing box with stiffened panels in a coupled or an uncoupled configuration. An advanced aluminium experimental test sample has also been described in detail. Good agreement has been found between the theoretical and numerical analyses and the experimental tests, thus confirming the validity of the analytical relations. Practical implications – The equivalent beam behaviour that has been determined and the stiffness calculation procedure that has been derived could be useful for future dynamic and aeroelastic analyses. Originality/value – The article presents an original derivation of the sectional characteristics of a thin-wa