In this work, a novel finite element approach for the computational aeroelastic analysis of flexible lifting structures in subsonic flow is presented. The numerical simulation of the fluid-structure interaction relies on the physical concept and mathematical formulation of an aeroelastic beam element, that is based on Euler-Bernoulli and De Saint-Venant theories for the structure dynamics and modified strip theory for the unsteady airload. An implementation of the unsteady vortex lattice method is used to correct standard strip theory in the time domain, considering the actual wing geometry and taking the aerodynamic effects of its sweep, aspect ratio and taper ratio into account. The effects of shed and trailed vorticity on the sectional load development and distribution are also accounted for, within a hybrid semi-analytical reduced-order aerodynamic model. Building on previous works, the present computational framework for aeroelastic modelling and simulations of flexible lifting structures is investigated and validated through a parametric stability assessment of swept tapered wings. The aeroelastic beam element proves to be an intuitive, reliable and efficient reduced-order tool, well suited for the preliminary multidisciplinary design and optimisation of flexible aircraft.

中文翻译：

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一种用于柔性亚音速机翼稳定性分析的精制气动弹性梁有限元


在这项工作中，提出了一种新颖的有限元方法，用于亚音速流中柔性升力结构的计算气动弹性分析。流-固耦合的数值模拟依赖于气动弹性梁单元的物理概念和数学公式，该单元基于结构动力学的 Euler-Bernoulli 和 De Saint-Venant 理论以及非定常空气载荷的修正条带理论。采用非定常涡旋晶格方法的实现在时域中纠正标准条带理论，考虑实际机翼几何形状并考虑其后掠、纵横比和锥度比的空气动力学效应。在混合半分析降阶空气动力学模型中，还考虑了脱落和拖曳涡度对截面载荷发展和分布的影响。在以往工作的基础上，通过后掠锥形翼的参数稳定性评估，研究和验证了目前用于柔性升力结构气动弹性建模和模拟的计算框架。事实证明，气动弹性梁单元是一种直观、可靠和高效的降阶工具，非常适合灵活飞机的初步多学科设计和优化。