Bir insansız hava aracına ait kompozit kanadın tasarımı ve yapısal optimizasyonu
Design and structural optimisation of an UAV composite wing
- Tez No: 869888
- Danışmanlar: DR. ÖĞR. ÜYESİ ALAEDDİN BURAK İREZ
- Tez Türü: Yüksek Lisans
- Konular: Makine Mühendisliği, Savunma ve Savunma Teknolojileri, Uçak Mühendisliği, Mechanical Engineering, Defense and Defense Technologies, Aeronautical Engineering
- Anahtar Kelimeler: Belirtilmemiş.
- Yıl: 2024
- Dil: Türkçe
- Üniversite: İstanbul Teknik Üniversitesi
- Enstitü: Lisansüstü Eğitim Enstitüsü
- Ana Bilim Dalı: Savunma Teknolojileri Ana Bilim Dalı
- Bilim Dalı: Savunma Teknolojileri Bilim Dalı
- Sayfa Sayısı: 121
Özet
Hava araçları, kısa mesafelerden uzun mesafelere kadar farklı uçuş gereksinimlerini karşılamak üzere kullanılmaktadır. Bu çeşitlilik, havacılık endüstrisinin sürekli olarak gelişmesine ve hava araçlarının çeşitli alanlarda etkili bir şekilde kullanılmasına olanak tanımaktadır. Teknolojik ilerlemeler, hava araçlarının yakıt verimliliği, güvenlik ve çevresel etkiler gibi alanlarda sürekli olarak geliştirilmesine olanak tanır. Elektronik sistemlerin ve uçuş kontrol teknolojilerinin ilerlemesi, hava araçlarının daha güvenli ve etkili bir şekilde uçmasına yardımcı olur. İnsansız Hava Araçları da (İHA'ları da) bu çeşitlilik içinde önemli bir yer tutmaktadır. İHA'lar, uzaktan kumanda veya önceden belirlenmiş programlar doğrultusunda otonom olarak uçabilen araçlardır. Bu araçlar, askeri operasyonlardan güvenlik gözetimine, tarımsal faaliyetlerden bilimsel araştırmalara kadar geniş bir yelpazede görevleri yerine getirmektedirler. İHA'ların tasarımında öne çıkan faktörlerden biri, hafif ve dayanıklı malzemelerin kullanımıdır. Bu bağlamda, genellikle karbon fiber, cam fiber ve epoksi reçine gibi bileşenlerden oluşan kompozit yapısal hafif malzemeler tercih edilmektedir. Hafif malzemelerin kullanımı, İHA'ların daha az enerji harcayarak uzun uçuş süreleri elde etmelerine yardımcı olur. Bu özellikler, İHA'ların uzun süreli ve maliyetinin düşük olması gereken görevlerde diğer hava araçlarına göre avantajlı olmalarını sağlar. Bu çalışma kapsamında bir insansız hava aracına ait kompozit kanadın uçuşa elverişli olacak şekilde tasarımı yapılmıştır ve bu tasarımın yapısal optimizasyonu gerçekleştirilmiştir. Uçuşa elverişli olabilmesi için öncelikle İHA görev profiline uygun olacak iki boyutlu bir kanat profili seçilmiştir. Bu kanat profilinin ilgili kaldırma kuvvetini karşılayabilecek şekilde 8 metre uzunluk, 1.2 metre kök genişliği olan üç boyutlu kanat tasarlanmıştır. Tasarlanan bu üç boyutlu kanadın Ansys Fluent yazılımı yardımı ile akışkanlar mekaniği analizi yapılmıştır. Bu nümerik çalışma sonucunda oluşan basınç dağılımı kanat kabuğu uzunluk yönünde 10 eşit parçaya bölünerek yüzeylerin belirlenen noktalarda oluşturduğu yük ve momentler elde edilmiştir. Bu yükler yapısal olarak iki kiriş ve iki kabuktan oluşan kanat geometrisine Abaqus yazılımında yayılı yük ve moment olarak tanımlanmıştır. Kanat yapısı kiriş uçlarından 6 serbestlik derecesinde tutularak sınır koşulu analiz modeline tanımlanmıştır. 40 bölgeye bölünmüş kanat geometrisine tek yönlü fiber takviyeli polimer matrisli kompozit malzeme ile serim yapılmış ve analiz Hashin hasar kriterine bağlı olarak çözdürülmüştür. Hasar kriterleri sınır değerinde altında kalmış ve dayanımı sağlamıştır. Kanat yapısı uçuşa el verişli ve dayanımlı olarak tasarlanmış ve yapısal optimizasyon çalışmasına geçilmiştir. Bu aşamada oluşturulan analiz modeli Python programlama dilinde hazırlanmış olan kod yardımı ile Abaqus yazılımı bir alt yazılım halinde çalıştırılarak optimize edilmiştir. Bu optimizasyon çalışmasında kanat yapısal ağırlığı, 45 analiz adımı sonunda %34.7 oranında hafiflemiştir. Yapılmış olan bu analiz çalışmalarında oluşan en kalın kompozit serimi, plaka halinde el ile serim metodu kullanılarak üretilmiştir. Üretilen bu plakadan çekme ve basma numuneleri kesilerek testlere tabii tutulmuştur. Çıkan sonuçlar doğrultusunda çalışmanın deneysel doğrulanması yapılmıştır.
Özet (Çeviri)
Aircrafts are utilized to meet diverse flight requirements, ranging from short to long distances. This diversity enables continuous development in the aviation industry, allowing effective utilization of aircraft in various fields. This diversity enables continuous development in the aviation industry, allowing effective utilization of aircraft in various fields such as passenger transportation, cargo logistics, aerial firefighting, and military operations. The adaptability of aircraft to multifaceted roles has spurred innovation in their design and functionality over the years. Ongoing technological advancements facilitate the continuous improvement of aircraft in areas such as fuel efficiency, safety, and environmental impact. Advances in electronic systems and flight control technologies contribute to safer and more efficient aircraft operations. Unmanned Aerial Vehicles (UAVs) also play a significant role within this diversity. UAVs, capable of flying autonomously based on remote control or pre-determined programs, fulfill a wide range of tasks from military operations to security surveillance, agricultural monitoring, and scientific research. A key factor in the design of UAVs is the utilization of lightweight and durable materials. In this context, composite materials, typically composed of components such as carbon fiber, glass fiber, and epoxy resin, are preferred as structural lightweight materials. These materials not only provide high strength-to-weight ratios but also contribute to the overall durability and efficiency of UAVs. The use of lightweight materials assists UAVs in achieving longer flight durations with reduced energy consumption, which is crucial for extending operational ranges and improving cost-effectiveness. These features provide UAVs with significant advantages, particularly in tasks requiring prolonged and cost-effective operations compared to other aircraft. By integrating advanced composite materials, UAVs can maintain high performance and reliability, making them indispensable tools in various fields. Prior to the commencement of this design study, an extensive characterization of the selected carbon fiber reinforced polymer (CFRP) material was meticulously carried out. This comprehensive characterization process involved a series of essential mechanical tests, specifically tensile and compressive tests, to accurately determine the material properties. These tests were designed to evaluate and quantify the CFRP material's performance under various loading conditions, providing crucial data on its tensile strength, compressive strength, and elasticity. The detailed results from these tests offered a thorough understanding of the material's mechanical behavior, ensuring that its suitability for the intended application was thoroughly assessed and validated. The strength and elasticity values obtained from this characterization were integral to informing and guiding the subsequent phases of the design and optimization process. In the scope of this study, the design of a composite wing for an unmanned aerial vehicle was conducted to make it flight-worthy, and structural optimization of this design was performed. To ensure flight-worthiness, a two-dimensional wing profile suitable for the UAV mission profile was initially selected. The selected wing profile serves as a critical component in optimizing lift, minimizing drag, and ensuring the UAV's adherence to the intended mission objectives. The wing geometry was designed based on literature review, considering requirements for a takeoff speed of 42.5 m/s and a cruising altitude of 2000 feet. This approach involved consulting existing research and relevant sources in the field to ensure that the specified parameters align with established principles and standards in aeronautical engineering. A three-dimensional wing with a length of 8 meters and a root width of 1.2 meters was then designed to meet the relevant lift force requirements. Fluid mechanics analysis of this designed three-dimensional wing was conducted using the Ansys Fluent program. In the fluid mechanics analysis, the wing geometry was placed within a spherical flow domain, and far-field boundary conditions were defined. The far-field boundary conditions are specified to represent the conditions at a sufficient distance from the wing, allowing for an accurate representation of the aerodynamic interactions. The pressure distribution obtained from this numerical study was divided into 10 equal parts along the length of the wing shell, generating loads and moments at the volume center on the surfaces. These loads were structurally defined as distributed loads and moments on the wing geometry consisting of two beams and two shells using the Abaqus program. The wing structure was constrained at the beam ends with six degrees of freedom, and the analysis model was defined with boundary conditions. Unidirectional carbon polymer matrix composite layup was meticulously applied to the wing geometry, meticulously divided into 40 regions to ensure comprehensive coverage. This detailed partitioning allowed for a nuanced analysis of the structural response across different segments of the wing, providing valuable insights into localized behaviors and performance characteristics. The analysis, conducted utilizing sophisticated computational techniques, was rigorously solved based on the Hashin damage criteria, a robust methodology for assessing material failure in composite structures. Throughout the analysis process, meticulous attention was paid to ensuring the structural integrity of the wing under various loading conditions. The application of the Hashin damage criteria served as a critical tool in this regard, providing a quantitative measure of material damage and allowing for proactive mitigation strategies to be implemented. Remarkably, the examination of the analysis outcomes revealed that the Hashin damage criterion values consistently remained below the designated threshold of 0.8, affirming the structural robustness of the wing design. Upon further scrutiny of the analysis results, a noteworthy observation emerged: in the context of compressive loads, the wing structure exhibited a tendency to approach the defined limit more closely. This nuanced exploration underscores the inherent resilience of the wing, particularly in withstanding compressive forces, as evidenced by the Hashin damage criterion values maintaining close proximity to the established threshold. This resilience is a testament to the effectiveness of the design approach and material selection, highlighting the successful integration of advanced engineering principles into the development of the UAV wing structure. The wing structure was designed to be flight-worthy and durable, leading to the initiation of structural optimization studies. In this phase, an analysis model created with the Python programming language was executed as a subroutine under the Abaqus software for optimization. This optimization process has been conducted using the single objective method. In this method, the objective is to reduce the weight. While fulfilling this objective, the Hashin damage criterion value has been constrained to a limit of 0.8, as previously mentioned. Additionally, the lay-up has been ensured to be symmetric and balanced. During the optimization process, the developed code scrutinizes the Hashin criterion values in pre-defined regions on the wing. Upon identifying values significantly exceeding the set threshold during this examination, the code dynamically introduces additional composite layers in the direction of the effective load. Conversely, if values considerably below the threshold are encountered, the code initiates the removal of composite layers aligned with the effective load direction. This iterative procedure is meticulously designed to guide the Hashin criterion values towards convergence with the specified threshold. Through this method, the optimization code actively seeks to enhance the overall structural integrity of the wing by iteratively adjusting the composition of composite layers based on the Hashin criterion evaluations. In the optimization study, the structural weight of the wing reduced by 34.7% after 45 analysis steps. The thickest composite laminate developed in this analysis comprises 18 plies and follows a unidirectional fiber orientation. Each ply, consisting of carbon fibers embedded in a polymer matrix, was meticulously layered during the manual hand lay- up process to ensure a precise unidirectional arrangement. This specific configuration enhances the laminate's mechanical properties, particularly its strength along the chosen fiber direction. Tension and compression specimens were then carefully cut from this composite plate to represent different orientations and positions within the laminate structure. These specimens underwent a series of experimental tests, exposing them to varying mechanical stresses in both tension and compression scenarios. In tensile tests, lower strength values were observed compared to the analysis, while in compression tests, higher strength values were observed relative to the analysis. This discrepancy is thought to be due to the thickness in characterization tests being significantly lower than the final thickness. As the thickness increased, the tensile strength of the matrix decreased, while the compressive strength increased. Discontinuities within the matrix contributed to this effect; in the direction of compression, they enhanced strength by alleviating discontinuities, whereas in the direction of tension, they increased stress concentrations, thereby reducing strength. The comprehensive testing regime aimed to evaluate the laminate's response under different loading conditions, providing valuable insights into its mechanical behavior.
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