Modified Fourier–Galerkin Solution for Aerospace Skin-Stiffener Panels Subjected to Interface Force and Mixed Boundary Conditions

Abstract

Aeronautical stiffened panels composed of thin shells and beams are prone to deformation or buckling due to the combined loading, functional boundary conditions and interface forces between joined parts in the assembly processes. In this paper, a mechanical prediction model of the multi-component panel is presented to investigate the deformation propagation, which has a significant effect on the fatigue life of built-up structures. Governing equations of Kirchhoff–Love shell are established, of which displacement expressions are transformed into Fourier series expansions of several introduced potential functions by applying the Galerkin approach. This paper presents an intermediate quantity, concentrated force at the joining interface, to describe mechanical interactions between the coupled components. Based on the Euler–Bernoulli beam theory, unknown intermediate quantity is calculated by solving a 3D stringer deformation equation with static boundary conditions specified on joining points. Compared with the finite element simulation and integrated model, the proposed method can substantially reduce grid number without jeopardizing the prediction accuracy. Practical experiment of the aircraft panel assembly is also performed to obtain the measured data. Maximum deviation between the experimental and predicted clearance values is 0.193 mm, which is enough to meet the requirement for predicting dimensional variations of the aircraft panel assembly.

A Review on Variation Modeling of Aircraft Assembly

“…Furthermore, they established an analytical model describing an aircraft thin-walled panel (see Figure 16) under positioning variation and clamping force [86]. After combining the separate part variation models with process analysis, the effects of connection coupling between stringer and skin were integrated into the variation modeling [87].…”

Effects of general boundary conditions on vibro-acoustic responses of the panel-cavity system induced by a turbulent boundary layer

“…While the structural boundary condition of these plate-liked structures in the aircraft are not limited to classical boundary conditions and considered as elastic restraints generally (Aloufi et al, 2017; Hou et al, 2019; Sachau and Baschke, 2017) in real engineering industry. Furthermore, wall impedance of the cabin hardly works as standard rigid or soft walls for existing acoustic decorations inside the cabin.…”