{
    "article_id": 1125,
    "public_id": "e5810e26-545b-48c8-8658-8b6530a47c20",
    "internal_identifier": null,
    "source_identifier": "42:130",
    "status": "published",
    "type": "research_article",
    "title": "Uçak Kanatlarının Tasarımı ve Sonlu Elemanlar Yöntemiyle Yapısal Analizi",
    "title_secondary": null,
    "abstract": "Kanat uçağın kaldırma kuvveti üreten bileşenidir. Kanat uçağın mevcut ağırlığından dolayı meydana gelen yer çekimi kuvvetini, ürettiği kaldırma kuvveti ile yener ve uçağın havada kalmasını sağlar. Kanat sahip olduğu aerodinamik profiller sayesinde kaldırma kuvveti üretir. Uçak kanadı için gerekenler yüksek rijitlik, yüksek dayanım, yüksek tokluk ve düşük ağırlıktır. Kaburga(Ribs) ve kiriş(Spars) kullanarak uçak kanadı tasarımı, 3D modelleme yazılımı CATIA V5R21 yardımıyla yapılmıştır. Uçak kanatları için kullanılan malzemeler çoğunlukla Alüminyum alaşımlarıdır. Bu araştırmada Alüminyum alaşımın Al 2024-T3 yanı sıra Epoxy Carbon UD1* (395 GPa), Epoxy S-Glass UD1*, Epoxy E-Glass UD1*, Epoxy Carbon Woven (395 GPa) gibi kompozit malzemeler kullanıldı. (1* UD: Unidirectional) Yük uygulanarak oluşan gerilmelerin belirlenmesi için statik analiz yapıldı. Kanadın üzerine gelen titreşimlerin frekanslarını, yönlendirilmiş deformasyonları ve frekanslardan kaynaklanan gerilmeleri belirlemek için, modal analiz yapıldı. Deformasyon ve yük çarpanını belirlemek için burkulma analizi yapıldı. Bütün sonuçlar kıyaslanarak kanat yapımı için en uygun malzemenin seçilmesi sağlandı. Analizlerin tamamı bir sonlu elemanlar paketi olan ANSYS programında yapıldı. Bütün analizler tamamlandıktan sonra literatürde yapılmış daha önceki testler ile kıyaslanarak farklı kanat profili ve malzemeler kullanmanın olumlu ve olumsuz yönleri belirlendi.  ",
    "language": "tr",
    "english_title": "Aircraft Wing Design and Structural Analysis Using Finite Element Method",
    "english_abstract": "The wing is the component of an aircraft that generates lift. The wing overcomes the gravitational force caused by the aircraft's weight with the lift it generates, enabling the aircraft to remain airborne. The wing generates lift thanks to its aerodynamic profiles. The requirements for an aircraft wing are high rigidity, high strength, high toughness, and low weight. Aircraft wing design using ribs and spars was performed using 3D modeling software CATIA V5R21. The materials used for aircraft wings are mostly aluminum alloys. In this research, in addition to the aluminum alloy Al 2024-\r\nT3, composite materials such as Epoxy Carbon UD1* (395 GPa), Epoxy S-Glass UD1*, Epoxy E-Glass UD1*, and Epoxy Carbon Woven (395 GPa) were used. (1* UD: Unidirectional)\r\nStatic analysis was performed to determine the stresses generated by applying load. Modal analysis was performed to determine the frequencies of vibrations acting on the wing, the directed deformations, and the stresses resulting from the frequencies. Buckling analysis was performed to determine the deformation and load factor. All results were compared to select the most suitable material for wing construction. All analyses were performed in the ANSYS program, a finite element package. After all analyses were completed, the advantages and disadvantages of using different wing profiles and materials were determined by comparing them with previous tests in the literature.",
    "doi": null,
    "doi_url": null,
    "resource_url": "https://www.set-science.com/a/e5810e26-545b-48c8-8658-8b6530a47c20",
    "pdf_url": "https://www.set-science.com/a/e5810e26-545b-48c8-8658-8b6530a47c20/pdf",
    "og_image": "https://www.set-science.com/assets/img/og-card-v2.png",
    "authors": [
        {
            "public_id": "9bf53598-344b-4863-afaf-ca514c8ce7c9",
            "given": "Özgün   ",
            "family": "GÜNAY",
            "full": "Özgün    GÜNAY",
            "literal": null,
            "orcid": null,
            "orcid_url": null,
            "email": "ozgungunayy@gmail.com",
            "corresponding": true,
            "sequence": "first",
            "affiliations": [
                {
                    "name": "Gazi Üniversitesi",
                    "department": null,
                    "country": null,
                    "country_code": null,
                    "ror": null,
                    "ror_url": null
                }
            ]
        },
        {
            "public_id": "2b351255-46e4-41d2-84b6-242e1f463a19",
            "given": "Mahmut   ",
            "family": "ÖZBAY",
            "full": "Mahmut    ÖZBAY",
            "literal": null,
            "orcid": null,
            "orcid_url": null,
            "email": "ozgungunayy@gmail.com",
            "corresponding": false,
            "sequence": "additional",
            "affiliations": [
                {
                    "name": "Gazi Üniversitesi",
                    "department": null,
                    "country": null,
                    "country_code": null,
                    "ror": null,
                    "ror_url": null
                }
            ]
        }
    ],
    "keywords": [
        "Kaburga(Ribs) ve Kiriş(Spars) kullanan Uçak Kanadı",
        "Statik analiz",
        "Modal analiz",
        "Burkulma Analizi"
    ],
    "translations": [
        {
            "language": "en",
            "title": "Aircraft Wing Design and Structural Analysis Using Finite Element Method",
            "abstract": "The wing is the component of an aircraft that generates lift. The wing overcomes the gravitational force caused by the aircraft's weight with the lift it generates, enabling the aircraft to remain airborne. The wing generates lift thanks to its aerodynamic profiles. The requirements for an aircraft wing are high rigidity, high strength, high toughness, and low weight. Aircraft wing design using ribs and spars was performed using 3D modeling software CATIA V5R21. The materials used for aircraft wings are mostly aluminum alloys. In this research, in addition to the aluminum alloy Al 2024-\r\nT3, composite materials such as Epoxy Carbon UD1* (395 GPa), Epoxy S-Glass UD1*, Epoxy E-Glass UD1*, and Epoxy Carbon Woven (395 GPa) were used. (1* UD: Unidirectional)\r\nStatic analysis was performed to determine the stresses generated by applying load. Modal analysis was performed to determine the frequencies of vibrations acting on the wing, the directed deformations, and the stresses resulting from the frequencies. Buckling analysis was performed to determine the deformation and load factor. All results were compared to select the most suitable material for wing construction. All analyses were performed in the ANSYS program, a finite element package. After all analyses were completed, the advantages and disadvantages of using different wing profiles and materials were determined by comparing them with previous tests in the literature.",
            "keywords": [
                "Aircraft Wing Using Ribs and Spars: Static Analysis",
                "Modal Analysis",
                "Buckling Analysis"
            ]
        }
    ],
    "subjects": [],
    "subject_names": [],
    "published_date": "2019-06-01",
    "published_year": "2019",
    "received_date": null,
    "accepted_date": null,
    "volume": "4",
    "issue": null,
    "page_first": "660",
    "page_last": "666",
    "article_number": null,
    "conference": {
        "short_name": "ISAS2019-ENS",
        "full_title": "3rd International Symposium on Innovative Approaches in Scientific Studies (Engineering and Natural Sciences)",
        "name": "3rd International Symposium on Innovative Approaches in Scientific Studies (Engineering and Natural Sciences)",
        "acronym": "ISAS2019-ENS",
        "location": "Ankara, Türkiye",
        "start_date": "2019-04-19",
        "end_date": null,
        "public_id": "ed3b36e9-38cf-4aeb-a135-833c969cc89f"
    },
    "proceedings": {
        "title": "3rd International Symposium on Innovative Approaches in Scientific Studies (Engineering and Natural Sciences)",
        "series_title": "Setsci conference indexing system",
        "publisher": "SET Technology",
        "isbn": null,
        "eisbn": null,
        "issn": "2618-6446",
        "eissn": null,
        "doi": null,
        "doi_prefix": null,
        "slug": "setsci-volume-4-2019-legacy-42",
        "public_id": "24d215ef-a545-4351-9725-6e9bdb167b3c",
        "url": "https://www.set-science.com/p/setsci-volume-4-2019-legacy-42"
    },
    "license": {
        "name": "CC BY 4.0",
        "url": "https://creativecommons.org/licenses/by/4.0/",
        "code": "CC-BY-4.0",
        "open_access": true
    },
    "copyright": {
        "holder": "SET Technology",
        "year": "2019"
    },
    "funding_statement": null,
    "funders": [],
    "references": [
        {
            "order": 1,
            "raw": "1. https://www.cpdlr.com/notes-articles-engineering/285-design-and-structural-validation-of-aircraft-wing.html\r\n\r\n2. The International Journal of Engineering And Science (IJES) \" Finite Element Analysis of Aircraft Wing Using Composite Structure Dr.R.Rajappan, V.Pugazhenthi\"\r\n\r\n3. International Journal of Application or Innovation in Engineering & Management (IJAIEM) \"Statistic and Dynamic Analysis of Typical Wing Structure of Aircraft using Nastran. Mr. Pritish Chitte, Mr. P. K. Jadhav, Mr. S. S. Bansode\"\r\n\r\n4. IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE)\" Finite Element Analysis of Carbon Fiber Reinforced Aircraft Wing Kirankumar Reddy , Sunil Manganshetty\"\r\n\r\n5. Amrutha P Kurian et al Int. Journal of Engineering Research and Applications \" Linear Static Analysis of CFRP Aircraft Wing Dr. Alice Mathai, Amrutha P\r\nKurian, Bia Jacob \"\r\n\r\n6. International Journal of Innovative Research in Science, Engineering and Technology Vol. 2, Issue 6, June 2013 “optimization of aircraft wing with composite material Shabeer KP1, Murtaza M A \"\r\n\r\n7. International Journal of Research in Engineering and Technology \" stress analysis and fatigue life prediction of wingfuselage lug joint attachment bracket of a\r\ntransport aircraft Sriranga B.k, Kumar. R\"\r\n\r\n8. Design and Structural Analysis of the Ribs and Spars of Swept Back Wing by Mohamed Hamdan A, Nithiya kalyani, International Journal of Emerging Technology\r\nand Advanced Engineering, (ISSN 2250-2459, ISO 9001:2008 Certified Journal, Volume 4, Issue 12, December 2014)\r\n\r\n9. Optimal Topology of Aircraft Rib and Spar Structures Under Aeroelastic Loads by Bret K. Stanford, Peter D. Dunning, Journal of Aircraft\r\n\r\n10. Two‐Spar Wing Stress Analysis: An Investigation into the Effect of Flexibility of Ribs by W.J. Goodey, M.A., A.F.R. Ae.S, Aircraft Engineering and Aerospace\r\nTechnology, ISSN: 0002-2667\r\n\r\n11. Statistic and Dynamic Analysis of Typical Wing Structure of Aircraft using Nastran by Mr. Pritish Chitte, Mr. P. K. Jadhav, Mr. S. S. Bansode, International Journal of Application or Innovation in Engineering & Management(IJAIEM), Volume 2, Issue 7, July 2013\r\n\r\n12. J Schijve 2009 Fatigue Damage in Aircraft Structures Not Wanted but Tolerated, International Journal of Fatigue .31,998-1011\r\n\r\n13. Aircraft Design: A Conceptual Approach by Daniel P. Raymer Page 332-333\r\n\r\n14. Theory Of Wing Sections by Ira H. Abbott and Albert E. Von Doenhoff\r\n\r\n15. Aircraft Wing Panel Buckling Analysis: Efficiency by approximations by C.B. York and F.W. Williams (1 January 1998)",
            "doi": null,
            "title": null,
            "authors": null,
            "source": null,
            "year": null,
            "volume": null,
            "pages": null
        }
    ],
    "statements": {
        "acknowledgements": null,
        "conflict_of_interest": null,
        "data_availability": null,
        "ai_disclosure": null
    },
    "credit": [],
    "history": {
        "published": "2019-06-01"
    }
}