New concept of multidisciplinary optimization for weight saving and stiffness improvement of a morphing variable span of tapered wing MVSTW - application to the UAS-S4

Abstract

This thesis presents a new approach of multidisciplinary numerical optimization used to develop a lightweight morphing wing based on data from an Unmanned Aerial System (UASS4). The optimal design for the UAS-S4 wing was determined, in order to achieve a high level of performance. The computation and selection of appropriate manufacturing materials were also considered. The methodology, design tools, and results were obtained via ComputerAided Design (CAD), Computer Aided Engineering (CAE), and MATLAB software. The first phase included a design and development comparative study of a Morphing Variable Span of the Tapered Wing (MVSTW) for an Unmanned Aerial System UAS-S4. The main objective was to analyze, and to compare the wing aerodynamic properties for various span lengths and sweep angles, and to determine its most efficient geometric design. This design can be employed for aircraft roll motion control instead of its conventional control mechanism, and is more sensitive to changes in the angle of its inner section influencing the aerodynamic characteristics. The second phase presented the topology optimization and evaluated the feasibility of internal wing components. Topology optimization was performed to place the wing components within its fixed and moving segments done in aluminum alloy 2024-T3. According to research findings, the fixed and moving segments should be designed with two spar and seven ribs configurations with their support components in the high-strain region. The third phase discusses the integration of structural sizing, topology, and aerodynamic optimization for MVSTW with the objective of reducing its weight. The optimization techniques considered the aerodynamic load distribution along the wingspan at its full wingspan extension and maximum speed. The wing components were optimized for size and topology optimization, and were designed using aluminum alloy 2024-T3. Weight savings of up to 51.2% and 55.7% were obtained for the fixed and moving wing sections, respectively, according to the optimization results. The fourth phase is a continuation of earlier phases performed for the multidisciplinary numerical optimization for the of MVSTW design to minimize its weight using composite materials. By integrating simultaneous material, structural size, and topological optimizations according to aerodynamic analyses, a computational environment for multidisciplinary optimization was considered to determine if morphing wings optimization was feasible. The MVSTW weight could be significantly decreased by using of the multidisciplinary numerical optimization methods.

Date	29 Aug 2022
Original language	American English
Awarding Institution	École de technologie supérieure
Supervisor	Ruxandra Botez (Supervisor) & Thien-My Dao (Co-supervisor)