Abstract
The work presented in the following focuses on the description of a fairly complex physicsbased method for the computation of the structural weight of an aircraft wing. The wing sections are sized against bending, shear and torsion loads deriving by the application of aerodynamics loads (maneuver, gust), concentrated and distributed inertia loads, landing and taxi loads. The wing structure is discretized in a series of sections characterized by constant chord and c/t ratio. Each section is approximated as an assembly of spars, skin panels and stiffeners (booms). The spar caps and the stiffeners are assumed to carry only the bending load while the spar webs and skin panels are assumed to carry only the shear and torsion loads (effect of the ribs is neglected). Accurate predictions of wing weight, bending and torsional stiffness are possible by applying this method. The same approach is applied for the study of cantilever and strut-braced wings showing the potential for the method generalization to the analysis of any wing configuration and tail stabilizer.
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