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Design and optimization of a wing structure for a UAS class I 145 kg

2017Master thesis Open access
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datacite.subject.fosEngenharia e Tecnologia::Engenharia dos Materiaispt_PT
dc.contributor.advisorInfante, Virgínia
dc.contributor.advisorDuarte, Diogo
dc.contributor.authorSilva, João
dc.date.accessioned2018-06-21T09:44:01Z
dc.date.available2018-06-21T09:44:01Z
dc.date.issued2017
dc.date.submitted2017
dc.descriptionAlferes Aluno ENGAER 137735-D. Estabelecimentos de ensino superior: AFA/ISTpt_PT
dc.description.abstractIn the context of air power in a Global scale, unmanned aerial systems (UAS) are a present and future necessity, reason why, they are part of the Portuguese Air Force (FAP) strategic vision and part of the Portuguese National Strategy for the Sea 2013-2020. Since 2008 the FAP has been developing UAS ever more capable and, nowadays, some of its experimental platforms are already being used operationally, both nationally and internationally. In order to expand their use, in a safe and responsible manner, for search and surveillance missions over the vast area under Portugal’s jurisdiction, there is the necessity to manufacture new platforms capable of fulfilling all the operational and airworthiness requirements and to establish procedures for their eventual mass production. In light of these necessities, the present master’s thesis consists of the design and optimization of the structure of the wing of a new operational platform with a maximum take-off weight of 145 kg (UAS class I). Parallelly to the operational use, this platform will also play the fundamental role of being the test model – at a reduced scale – for a large UAS (class II), currently in development by a consortium between the FAP, national companies and the Portuguese National Ministry of Defense (MDN). The wing design and optimization process, involved determining the loads acting on the structure (definition of the aircraft’s flight envelope and identification of the wing’s critical loading condition), planning the general shape and components layout, choosing materials (composites – manufacturing of specimens and experimental testing to obtain their properties), and then, shaping, sizing and optimizing its many components to give every part just enough strength without excess weight and also to reduce costs. All design decision were fundamented based on regulations (e.g. the NATO STANAG AEP-83), structural design manuals, books and scientific articles, in order to guarantee the certification of the structure in terms of airworthiness. The optimization process used / created – “chain top-down approach” – proved to be simple and effective and consisted in an individual but interconnected optimization, of each component, following a hierarchical sequence, in accordance with the structural importance of each one. All the geometric models produced (3D) and all the structural analysis performed (numerical analysis resorting to the discretization of the structure using finite elements – FEA), were achieved by using the software SolidWorks 2016 x64 Edition. The final wing model obtained, fulfilled every structural requisite (capable of enduring between - 1.5 and 4 G’s with a wing tip displacement < 5% of half-wing span), perational requisite (capable of carrying up to 10 kg of suspended payload from each half-wing), and weight requisite (mass < 26.2 kg), with a manufacturing cost, in terms of materials, close to 3000 €.pt_PT
dc.identifier.urihttp://hdl.handle.net/10400.26/23156
dc.language.isoporpt_PT
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/pt_PT
dc.subjectAir powerpt_PT
dc.subjectFAPpt_PT
dc.subjectUAS class Ipt_PT
dc.subjectWing structural designpt_PT
dc.subjectStructural optimizationpt_PT
dc.subjectCompositespt_PT
dc.subjectPoder aéreopt_PT
dc.subjectFAPpt_PT
dc.subjectUAS class Ipt_PT
dc.subjectDesign estrutural de asapt_PT
dc.subjectOtimização estruturalpt_PT
dc.subjectCompósitospt_PT
dc.titleDesign and optimization of a wing structure for a UAS class I 145 kgpt_PT
dc.typemaster thesis
dspace.entity.typePublication
rcaap.rightsopenAccesspt_PT
rcaap.typemasterThesispt_PT
thesis.degree.grantorAcademia da Força Aérea
thesis.degree.nameA thesis to obtain the Master Degree in Military Science Aeronautical Engeneeringpt_PT

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