Gust load alleviation efficiency in an optimized composite wing through the integration of wingtip devices: Incorporating folding and twist strategies

ifasd2024 Tracking Number 14

This paper introduces an advanced numerical approach aimed at designing and optimizing high aspect ratio composite wings with passive control systems, specifically employing folding and twist wingtip devices. The primary objective is to enhance gust load alleviation performance in a baseline wing configuration. Recent studies show potential benefits from incorporating spring devices and wingtip variations to improve gust load alleviation during flight. The baseline wing is developed using an extensive multi-disciplinary optimization framework, considering aerostructural constraints and leveraging the anisotropic properties of composite materials. The proposed methodology integrates Finite Element (FE) software, an in-house Reduced Order Model (ROM) framework for nonlinear aeroelastic analyses, and Particle Swarm Optimization (PSO). Implemented in the Nonlinear Aeroelastic Simulation Software (NAS2) package, this approach facilitates the streamlined design of composite wings with optimized aeroelastic and structural performance. The paper offers two main contributions: it presents a Multidisciplinary Design Optimization (MDO) approach for high aspect ratio composite wings and assesses the effectiveness of Folding and Twist wingtip devices in reducing gust load on the baseline wing, with a focus on the root bending moment. The paper initially showcases the MDO of high aspect ratio composite wings, leading to the development of a baseline wing model. This phase involves considering a range of factors such as structural, composite material, aeroelastic, and manufacturing constraints. The primary goal is to minimize the wing's weight while maximizing its twist factor. After the initial study of MDO, the research evaluates the effectiveness of folding and twist wingtip devices in reducing gust load on the baseline wing, with particular attention to the root bending moment as an interesting quantity. The incorporation of these devices at the end of the baseline wing facilitates a detailed comparison of gust responses between the baseline wing and the wing equipped with the Folding and Twist wingtip devices This research contributes a robust numerical methodology for the holistic design of composite wings, addressing key challenges in aerospace engineering. The systematic approach presented here, combining multi-disciplinary optimization and innovative wingtip devices, serves as a valuable tool for designing lightweight composite wings with improved aeroelastic and structural performance, thus advancing the field of high aspect ratio wing configurations in aerospace engineering.