Design and Manufacturing Parameters of Integrated Joggled Composite Skins in Aerospace Structures

Muharrem Can; Özgür Karali

Makale detayları

Design and Manufacturing Parameters of Integrated Joggled Composite Skins in Aerospace Structures

Yazarlar:

Muharrem Can | Özgür Karali

Yayıncı:

Karyay Karadeniz Yayımcılık

Ana Başlıklar:

Havacılık Yapıları

Dergi:

Black Sea Journal of Engineering and Science Vol.8 Issue 4, pp.1050-1056

Belge Tipi:

Makale

Yayın Tarihi:

7/2025

Belge Dili:

Türkçe

Document ID (Org No.):

2001346246

pISSN:

2619-8991

Anahtar kelimeler:

Özet:

 Today, advanced composite materials are widely used in aerospace applications due to their high strength-to-weight ratios and low density. The design of aerospace structures must consider several parameters, including functionality, lightweight properties, strength, accessibility, and ease of maintenance. The limited internal volumes of aircraft make it essential to develop specialized design solutions for structural components. Aircraft require numerous access panels for maintenance and repair operations throughout their service life. However, these panels and their fasteners account for a significant portion of the total structural weight. This study focuses on designing integrated stepped structures for access panels on composite shells, eliminating the need for additional components, and identifies critical considerations during the design process. To ensure manufacturability, parameters that simplify production, reduce production time, and decrease costs have been evaluated. Consequently, a reduction in the number of fasteners and components has resulted in significant decreases in the aircrafts total structural weight, production time, and costs. The step ratio depthlength varies depending on the type of loading, and as this ratio decreases, the stress concentration also decreases. However, in some cases, these rates need to be increased in line with design requirements such as accessibility, lightness and aerodynamic continuity. In this study, a fuel tank access panel design with a 1:5 ratio, which is challenging to manufacture and reasonable for load transfer, has been applied. Manufacturing trials based on this ratio were conducted, yielding favorable results.

 Today, advanced composite materials are widely used in aerospace applications due to their high strength-to-weight ratios and low density. The design of aerospace structures must consider several parameters, including functionality, lightweight properties, strength, accessibility, and ease of maintenance. The limited internal volumes of aircraft make it essential to develop specialized design solutions for structural components. Aircraft require numerous access panels for maintenance and repair operations throughout their service life. However, these panels and their fasteners account for a significant portion of the total structural weight. This study focuses on designing integrated stepped structures for access panels on composite shells, eliminating the need for additional components, and identifies critical considerations during the design process. To ensure manufacturability, parameters that simplify production, reduce production time, and decrease costs have been evaluated. Consequently, a reduction in the number of fasteners and components has resulted in significant decreases in the aircrafts total structural weight, production time, and costs. The step ratio depthlength varies depending on the type of loading, and as this ratio decreases, the stress concentration also decreases. However, in some cases, these rates need to be increased in line with design requirements such as accessibility, lightness and aerodynamic continuity. In this study, a fuel tank access panel design with a 1:5 ratio, which is challenging to manufacture and reasonable for load transfer, has been applied. Manufacturing trials based on this ratio were conducted, yielding favorable results.

 Today, advanced composite materials are widely used in aerospace applications due to their high strength-to-weight ratios and low density. The design of aerospace structures must consider several parameters, including functionality, lightweight properties, strength, accessibility, and ease of maintenance. The limited internal volumes of aircraft make it essential to develop specialized design solutions for structural components. Aircraft require numerous access panels for maintenance and repair operations throughout their service life. However, these panels and their fasteners account for a significant portion of the total structural weight. This study focuses on designing integrated stepped structures for access panels on composite shells, eliminating the need for additional components, and identifies critical considerations during the design process. To ensure manufacturability, parameters that simplify production, reduce production time, and decrease costs have been evaluated. Consequently, a reduction in the number of fasteners and components has resulted in significant decreases in the aircrafts total structural weight, production time, and costs. The step ratio depthlength varies depending on the type of loading, and as this ratio decreases, the stress concentration also decreases. However, in some cases, these rates need to be increased in line with design requirements such as accessibility, lightness and aerodynamic continuity. In this study, a fuel tank access panel design with a 1:5 ratio, which is challenging to manufacture and reasonable for load transfer, has been applied. Manufacturing trials based on this ratio were conducted, yielding favorable results.

 Günümüzde ileri kompozit malzemeler, yüksek mukavemet ve düşük yoğunluk oranları nedeniyle havacılık uygulamalarında yaygın olarak kullanılmaktadır. Havacılık yapılarının tasarımında fonksiyonellik, hafiflik, dayanım, erişim kolaylığı ve bakım kolaylığı gibi birçok parametre dikkate alınmalıdır. Hava araçlarının sınırlı hacimlere sahip olması, yapısal parçaların tasarımında özel çözümlerin geliştirilmesini zorunlu hale getirmiştir. Bu araçlarda, ömürleri boyunca gerekli bakım ve onarım işlemlerine erişimi sağlamak için çok sayıda erişim kapağı bulunmaktadır. Aynı zamanda, bu kapaklar ve bağlayıcılar toplam yapısal ağırlığın önemli bir kısmını oluşturur. Bu çalışmada, kompozit kabuk yapılar üzerinde yer alan erişim kapaklarının ek bir parçaya ihtiyaç duyulmadan bütünleşik basamaklı yapıda tasarlanması ve bu tasarım sürecinde dikkat edilmesi gereken unsurlar ele alınmıştır. Tasarımların üretilebilir olması gerekliliği göz önünde bulundurularak, üretim kolaylığı sağlayacak, üretim sürelerini ve maliyetlerini azaltacak parametreler incelenmiştir. Sonuç olarak, azaltılan bağlayıcı ve parça sayısıyla hem toplam uçak yapısal ağırlığında hem de üretim süresi ve maliyetlerinde önemli bir azalma elde edilmiştir. Yükleme çeşidine göre basamak oranı derinlikuzunluk değişkenlik göstermektedir ve bu oran azaldıkça gerilme birikmesi de azalmaktadır. Ancak erişim, hafiflik ve aerodinamik süreklilik gibi tasarım gereksinimleri doğrultusunda bazı durumlarda bu oranın artırılması gerekmektedir. Çalışma kapsamında üretimi zor ve yük aktarımı konusunda makul bir basamak oranı olan 1:5lik orana sahip bir yakıt tankı erişim kapağı tasarıma uygulanmıştır. Üretim denemeleri de bu basamak oranı üzerinden gerçekleştirilmiş ve olumlu sonuçlar elde edilmiştir.

Makale detayları

Design and Manufacturing Parameters of Integrated Joggled Composite Skins in Aerospace Structures

Yazarlar:

Muharrem Can | Özgür Karali

Yayıncı:

Karyay Karadeniz Yayımcılık

Ana Başlıklar:

Havacılık Yapıları

Dergi:

Black Sea Journal of Engineering and Science Vol.8 Issue 4, pp.1050-1056

Belge Tipi:

Makale

Yayın Tarihi:

7/2025

Belge Dili:

Türkçe

Document ID (Org No.):

2001346246

pISSN:

2619-8991

Composite

Joggle

Aerospace

DesignKompozit

Basamak

Havacılık

Tasarım

Sayı

Makale detayları

Yazarlar: Muharrem Can | Özgür Karali

Yayıncı: Karyay Karadeniz Yayımcılık

Ana Başlıklar: Havacılık Yapıları

Dergi: Black Sea Journal of Engineering and Science Vol.8 Issue 4, pp.1050-1056

Belge Tipi: Makale

Yayın Tarihi: 7/2025

Belge Dili: Türkçe

Document ID (Org No.): 2001346246

pISSN: 2619-8991

Sayı

Yazarlar:

Muharrem Can | Özgür Karali

Yayıncı:

Karyay Karadeniz Yayımcılık

Ana Başlıklar:

Havacılık Yapıları

Dergi:

Black Sea Journal of Engineering and Science Vol.8 Issue 4, pp.1050-1056

Belge Tipi:

Makale

Yayın Tarihi:

7/2025

Belge Dili:

Türkçe

Document ID (Org No.):

2001346246

pISSN:

2619-8991