Purpose

Aircraft wings, one of the most important parts of an aircraft, have seen changes in its topological and design arrangement of both the internal structures and external shape during the past decades. This study, a numerical, aims to minimize the weight of multilaminate composite aerospace structures using multiobjective optimization.

Design/methodology/approach

The methodology started with the determination of the requirements, both imposed by the certifying authority and those inherent to the light, aerobatic, simple, economic and robust (LASER) project. After defining the requirements, the loads that the aircraft would be subjected to during its operation were defined from the flight envelope considering finite element analysis. The design vector consists of material choice for each laminate of the structure (20 in total), ply number and lay-up sequence (respecting the manufacturing rules) and main spar position to obtain a lightweight and cheap structure, respecting the restrictions of stress, margins of safety, displacements and buckling.

Findings

The results obtained indicated a predominance of the use of carbon fiber. The predominant orientation found on the main spar flange was 0° with its location at 28% of the local chord, in the secondary and main web were ±45°, the skins also had the main orientation at ±45°.

Originality/value

The key innovations in this paper include the evaluation, development and optimization of a laminated composite structure applied to a LASER aircraft wings considering both structural performance and manufacturing costs in multiobjetive optimization. This paper is one of the most advanced investigations performed to composite LASER aircraft.

中文翻译：

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激光飞机机翼复合材料结构设计的多目标优化

目的

机翼是飞机最重要的部件之一，在过去的几十年里，其内部结构和外部形状的拓扑和设计布置都发生了变化。这项数值研究旨在使用多目标优化来最小化多层复合航空航天结构的重量。

设计/方法/方法

该方法首先确定要求，既是由认证机构强加的，也是轻型、特技、简单、经济和稳健 (LASER) 项目固有的要求。在定义了要求之后，考虑到有限元分析，飞机在其运行过程中将受到的载荷是从飞行包线中定义的。设计向量包括结构的每个层压板的材料选择（总共 20 个）、层数和铺设顺序（尊重制造规则）和主梁位置以获得轻质和廉价的结构，尊重应力限制，安全边际、位移和屈曲。

发现

获得的结果表明碳纤维的使用占优势。在主翼梁翼缘上发现的主要方向为 0°，其位置为局部弦的 28%，在次要腹板和主腹板中为 ±45°，蒙皮的主要方向也为 ±45°。

原创性/价值

本文的主要创新包括在多目标优化中考虑结构性能和制造成本，对应用于激光飞机机翼的层压复合材料结构进行评估、开发和优化。本文是对复合激光飞机进行的最先进的研究之一。