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首页> 外文期刊>International journal of structural integrity >Structural integrity aspects of a lightweight civil unmanned air vehicle
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Structural integrity aspects of a lightweight civil unmanned air vehicle

机译：轻型民用无人机的结构完整性方面

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Purpose - The purpose of this paper is to focus on the finite element (FE) analyses undertaken for aerodynamically and structurally optimized design of a modern, lightweight civil unmanned air vehicle (UAV) made fully of composite materials. Design/methodology/approach - The FE method has been applied to design and calculate the safety factors of all structural elements of the UAV. Fully parameterized design tools have been developed in the preliminary design phase, allowing automatic reshapes of the skin and the internal structural parts, wherever needed, to achieve optimal structural design, from the point of view of lightweight and structural integrity. Monotonic and fatigue tests have been performed on material specimens with various thicknesses and fibre textures, to verify the material properties used for the FE analyses. The load assumptions were in accordance with the valid international standards. Findings - The material tests confirmed the validity of the material properties used within the FE calculations. The calculated safety factors were acceptable for all structural elements and components of the UAV. As a result, a lightweight, structurally optimized design has been achieved, considering the international, standardized specifications assumptions and fulfilling the safety requirements. Practical implications - Design engineers may use the outcomes of this work as a guide to achieve optimal lightweight structures ensuring its operational strength using composite, lightweight materials. Originality/value - A new, structurally optimized, lightweight aircraft design has been developed, able to accommodate heavy electronic payloads while being able to fly for over ten hours without refuelling. This medium altitude long endurance airplane can overview forests, seas and human trafficking autonomously and economically.
机译：目的-本文的目的是集中进行有限元（FE）分析，以对完全由复合材料制成的现代轻型民用无人机（UAV）进行空气动力学和结构优化设计。设计/方法/方法-有限元方法已用于设计和计算无人机所有结构元件的安全系数。在初步设计阶段已经开发了完全参数化的设计工具，从轻巧和结构完整性的角度出发，可以在需要时自动对蒙皮和内部结构零件进行自动重塑，以实现最佳的结构设计。已经对具有不同厚度和纤维质地的材料样本进行了单调和疲劳测试，以验证用于有限元分析的材料特性。负载假设符合有效的国际标准。发现-材料测试证实了有限元计算中所用材料特性的有效性。计算得出的安全系数对于无人机的所有结构元件和组件都是可以接受的。结果，考虑到国际标准化规格假设并满足安全要求，实现了轻巧，结构优化的设计。实际意义-设计工程师可以将这项工作的成果作为指导，以实现最佳的轻质结构，从而确保使用复合轻质材料的操作强度。独创性/价值-已开发出一种经过结构优化的新型轻型飞机设计，能够容纳沉重的电子负载，同时能够飞行十多个小时而无需加油。这种中等高度的长寿命飞机可以自主和经济地观察森林，海洋和人口贩运。

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