Structural integrity aspects of a lightweight civil unmanned air vehicle
International Journal of Structural Integrity
ISSN: 1757-9864
Article publication date: 5 December 2016
Abstract
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.
Keywords
Acknowledgements
The work presented in this paper is a part of the 11SYNERGASIA_9_629 “Hellenic Civil Unmanned Air Vehicle – HCUAV” research project, implemented within the framework of the National Strategic Reference Framework (NSRF) and through the Operation Programme “Competitiveness & Entrepreneurship – SYNERGASIA 2011”. The research project is co-financed by National and Community Funds, 25 per cent from the Greek Ministry of Education and Religious Affairs – General Secretariat of Research and Technology and 75 per cent from EU – European Social Fund.
Citation
Giannakis, E. and Savaidis, G. (2016), "Structural integrity aspects of a lightweight civil unmanned air vehicle", International Journal of Structural Integrity, Vol. 7 No. 6, pp. 773-787. https://doi.org/10.1108/IJSI-11-2015-0055
Publisher
:Emerald Group Publishing Limited
Copyright © 2016, Emerald Group Publishing Limited