Bir Kanadın Çok Disiplinli Tasarım Optimizasyonu
Bir Kanadın Çok Disiplinli Tasarım Optimizasyonu
Dosyalar
Tarih
Yazarlar
Güler, Hakan
Süreli Yayın başlığı
Süreli Yayın ISSN
Cilt Başlığı
Yayınevi
Fen Bilimleri Enstitüsü
Institute of Science And Technology
Institute of Science And Technology
Özet
Bu çalışmada görev ve performans gereksinimleri verilen bir uçak kanadının aerodinamik, yapısal ve mukavemet disiplinleri altında tasarım optimizasyonu yapılmıştır. Başlangıç tasarım aşamasında öncelikle çok disiplinli optimizasyona (MDO) ilk girdiyi verecek sabitler ve değişkenlerin kabulü ve tespiti yapılmıştır. Bir çok istatistiksel veriye ve tecrübeye dayalı bu işlem geleneksel tasarım olarak da adlandırılabilir. Bu ilk tasarım aşamasından sonra kanat haricindeki gövde, kuyruk, iniş takımları gibi elemanlar sabit tutulmuş ve uçak performansının başlıca unsuru olan kanadın tasarım metodu üzerinde durulmuştur. Kanadın yapısal modelinde kanadın yarısı için ince cidarlı ankastre beam yaklaşımı yapılmış, taşıma ve sürükleme kuvvetlerinin hesaba katılmasıyla kanat kökünde oluşan maksimum normal gerilme ve burulma gerilmesi tespit edilmiştir. Kanat kesit atalet momentlerinin hesaplanmasında profil eğrisi küçük lineer parçacıklara bölünerek hesaplanmıştır. Çalışmanın sonunda ADS optimum tasarım programı üzerine bir program yazılmış ve optimizasyon gerçekleştirilmiştir. Optimizasyon stratejisi olarak genişletilmiş ceza fonksiyonunun kullanılmasıyla kısıtlamalı problem kısıtlamasız hale getirilmiş, optimizasyon tekniği olarak Davidon-Fletcher-Powell yöntemi, tek boyutlu araştırma yönü olarak altın bölüm yöntemi ve polinomsal interpolasyon kullanılmıştır.
In this study, for given mission requirements, design optimization of awing under aerodynamic, structural and performance disciplines was performed. At the beginning of the design process, design constants and variables which will be the initial data for multi disciplinary optimization(MDO) were determined. This prosses is called as traditional design. After this step, keeping the effects of the components such as fuselage, tail and landing gears have been fixed and the wing design, which is most dominant feature effecting overall performance of the aircraft, was emphasized. While establishing the structural model of the wing, only half of the wing was considered. Additionaly, the wing was modelled as a thin walled closed section beam which is cantilevered. Then the normal and the shear strains and stresses at the cantilever point were calculated knowing lift and drag forces. Cross sectional inertia moments of the beam were calculated by dividing the actual cord of the wing into small lineer elements. At the conclusion stage of the study, a computer program was written based on ADS optimum design software and multi disciplinary optimization process was performed. The constraint problem was transformed to sequential unconstraint problem by using extended penalty function method, Davidon-Fletcher-Powell method was used as an optimization technic and Golden Section Method followed by polynomial interpolation was used as one dimensional search method.
In this study, for given mission requirements, design optimization of awing under aerodynamic, structural and performance disciplines was performed. At the beginning of the design process, design constants and variables which will be the initial data for multi disciplinary optimization(MDO) were determined. This prosses is called as traditional design. After this step, keeping the effects of the components such as fuselage, tail and landing gears have been fixed and the wing design, which is most dominant feature effecting overall performance of the aircraft, was emphasized. While establishing the structural model of the wing, only half of the wing was considered. Additionaly, the wing was modelled as a thin walled closed section beam which is cantilevered. Then the normal and the shear strains and stresses at the cantilever point were calculated knowing lift and drag forces. Cross sectional inertia moments of the beam were calculated by dividing the actual cord of the wing into small lineer elements. At the conclusion stage of the study, a computer program was written based on ADS optimum design software and multi disciplinary optimization process was performed. The constraint problem was transformed to sequential unconstraint problem by using extended penalty function method, Davidon-Fletcher-Powell method was used as an optimization technic and Golden Section Method followed by polynomial interpolation was used as one dimensional search method.
Açıklama
Tez (Yüksek Lisans) -- İstanbul Teknik Üniversitesi, Fen Bilimleri Enstitüsü, 1999
Thesis (M.Sc.) -- İstanbul Technical University, Institute of Science and Technology, 1999
Thesis (M.Sc.) -- İstanbul Technical University, Institute of Science and Technology, 1999
Anahtar kelimeler
Kanat,
Çok disiplinli optimizasyon,
Wing,
Multi disciplinary optimization