Fatigue Analysis of an Aerospace Elastoplastic Structural Cylindrical Component with Hole under Cyclic Mechanical Load using COMSOL Multiphysics and Taguchi Method Optimization

Erkan Tur

Article Details

Fatigue Analysis of an Aerospace Elastoplastic Structural Cylindrical Component with Hole under Cyclic Mechanical Load using COMSOL Multiphysics and Taguchi Method Optimization

Authors:

Erkan Tur

Publisher:

Bayburt University

Main Topics:

Elektrik Mühendisliği | Makine Mühendisliği

Journal:

Bayburt Üniversitesi Fen Bilimleri Dergisi Vol.6 Issue 2, pp.151-171

Document Type:

Article

Publication Date:

12/2023

Document Language:

English

Document ID (Org No.):

2001307482

pISSN:

2667-579X

Keywords:

Abstract:

 This research study focuses on the fatigue behavior of an aerospace elastoplastic cylindrical structural component with a hole subjected to cyclic mechanical loads. In the demanding operational environment of aerospace applications, the structural components, particularly those with stress concentrators like holes, experience cyclic loading conditions, leading to fatigue failure over time. The key objective of this study is to gain insights into this fatigue behavior, and to develop an optimized set of design and operational parameters that can enhance the fatigue performance of these components. Utilizing the robust finite element analysis capabilities of COMSOL Multiphysics, a comprehensive model of the elastoplastic cylindrical component is developed. The model captures the intricate effects of the hole, a typical stress raiser, on the fatigue performance under various cyclic mechanical loading conditions. A detailed fatigue analysis is then performed using this model, providing valuable insights into the fatigue life and failure patterns of the component. To enhance the fatigue performance, the Taguchi method, a statistical approach, is employed. This method helps to identify and optimize the key design and operational parameters influencing the fatigue life. The parameters are optimized based on their signal-to-noise ratio, with an aim to maximize the fatigue life and ensure the structural integrity of the component under operational cyclic loads. The findings of this research hold significant implications for the design and manufacturing of aerospace structural components, with potential benefits of improved safety, enhanced durability, and reduced maintenance requirements. However, the results applicability might be limited by the complexity of real-world operational conditions and the assumptions made in the simulation model. Future studies can validate and enhance these results by incorporating more complex loading scenarios and real-world case studies.

 This research study focuses on the fatigue behavior of an aerospace elastoplastic cylindrical structural component with a hole subjected to cyclic mechanical loads. In the demanding operational environment of aerospace applications, the structural components, particularly those with stress concentrators like holes, experience cyclic loading conditions, leading to fatigue failure over time. The key objective of this study is to gain insights into this fatigue behavior, and to develop an optimized set of design and operational parameters that can enhance the fatigue performance of these components. Utilizing the robust finite element analysis capabilities of COMSOL Multiphysics, a comprehensive model of the elastoplastic cylindrical component is developed. The model captures the intricate effects of the hole, a typical stress raiser, on the fatigue performance under various cyclic mechanical loading conditions. A detailed fatigue analysis is then performed using this model, providing valuable insights into the fatigue life and failure patterns of the component. To enhance the fatigue performance, the Taguchi method, a statistical approach, is employed. This method helps to identify and optimize the key design and operational parameters influencing the fatigue life. The parameters are optimized based on their signal-to-noise ratio, with an aim to maximize the fatigue life and ensure the structural integrity of the component under operational cyclic loads. The findings of this research hold significant implications for the design and manufacturing of aerospace structural components, with potential benefits of improved safety, enhanced durability, and reduced maintenance requirements. However, the results applicability might be limited by the complexity of real-world operational conditions and the assumptions made in the simulation model. Future studies can validate and enhance these results by incorporating more complex loading scenarios and real-world case studies.

 This research study focuses on the fatigue behavior of an aerospace elastoplastic cylindrical structural component with a hole subjected to cyclic mechanical loads. In the demanding operational environment of aerospace applications, the structural components, particularly those with stress concentrators like holes, experience cyclic loading conditions, leading to fatigue failure over time. The key objective of this study is to gain insights into this fatigue behavior, and to develop an optimized set of design and operational parameters that can enhance the fatigue performance of these components. Utilizing the robust finite element analysis capabilities of COMSOL Multiphysics, a comprehensive model of the elastoplastic cylindrical component is developed. The model captures the intricate effects of the hole, a typical stress raiser, on the fatigue performance under various cyclic mechanical loading conditions. A detailed fatigue analysis is then performed using this model, providing valuable insights into the fatigue life and failure patterns of the component. To enhance the fatigue performance, the Taguchi method, a statistical approach, is employed. This method helps to identify and optimize the key design and operational parameters influencing the fatigue life. The parameters are optimized based on their signal-to-noise ratio, with an aim to maximize the fatigue life and ensure the structural integrity of the component under operational cyclic loads. The findings of this research hold significant implications for the design and manufacturing of aerospace structural components, with potential benefits of improved safety, enhanced durability, and reduced maintenance requirements. However, the results applicability might be limited by the complexity of real-world operational conditions and the assumptions made in the simulation model. Future studies can validate and enhance these results by incorporating more complex loading scenarios and real-world case studies.

 Bu araştırma çalışması, döngüsel mekanik yüklere maruz kalan bir deliği olan havacılık elastoplastik silindirik yapısal bileşenin yorulma davranışına odaklanmaktadır. Havacılık uygulamalarının zorlu çalışma ortamında, yapısal bileşenler, özellikle delikler gibi gerilim yoğunlaştırıcılara sahip olanlar, döngüsel yükleme koşullarına maruz kalırlar ve bu da zamanla yorulma arızasına yol açar. Bu çalışmanın temel amacı, bu yorulma davranışı hakkında bilgi edinmek ve bu bileşenlerin yorulma performansını artırabilecek optimize edilmiş bir tasarım ve işletim parametreleri seti geliştirmektir. COMSOL Multiphysicsin sağlam sonlu eleman analiz yeteneklerinden yararlanılarak, elastoplastik silindirik bileşenin kapsamlı bir modeli geliştirildi. Model, çeşitli döngüsel mekanik yükleme koşulları altında yorulma performansı üzerindeki tipik bir gerilim artırıcı olan deliğin karmaşık etkilerini yakalar. Daha sonra, bu model kullanılarak, bileşenin yorulma ömrü ve arıza modellerine ilişkin değerli bilgiler sağlayan ayrıntılı bir yorulma analizi gerçekleştirilir. Yorulma performansını artırmak için istatistiksel bir yaklaşım olan Taguchi yöntemi kullanılır. Bu yöntem, yorulma ömrünü etkileyen temel tasarım ve işletim parametrelerinin belirlenmesine ve optimize edilmesine yardımcı olur. Parametreler, yorulma ömrünü en üst düzeye çıkarmak ve operasyonel döngüsel yükler altında bileşenin yapısal bütünlüğünü sağlamak amacıyla sinyal-gürültü oranlarına göre optimize edilmiştir. Bu araştırmanın bulguları, gelişmiş güvenlik, artırılmış dayanıklılık ve azaltılmış bakım gereksinimleri gibi potansiyel faydalarla birlikte, havacılık yapısal bileşenlerinin tasarımı ve üretimi için önemli çıkarımlara sahiptir. Ancak, sonuçların uygulanabilirliği, gerçek dünya işletim koşullarının karmaşıklığı ve simülasyon modelinde yapılan varsayımlar ile sınırlı olabilir. Gelecekteki çalışmalar, daha karmaşık yükleme senaryoları ve gerçek dünya vaka incelemelerini birleştirerek bu sonuçları doğrulayabilir ve geliştirebilir.

Article Details

Fatigue Analysis of an Aerospace Elastoplastic Structural Cylindrical Component with Hole under Cyclic Mechanical Load using COMSOL Multiphysics and Taguchi Method Optimization

Authors:

Erkan Tur

Publisher:

Bayburt University

Main Topics:

Elektrik Mühendisliği | Makine Mühendisliği

Journal:

Bayburt Üniversitesi Fen Bilimleri Dergisi Vol.6 Issue 2, pp.151-171

Document Type:

Article

Publication Date:

12/2023

Document Language:

English

Document ID (Org No.):

2001307482

pISSN:

2667-579X

Structural Design

Elastoplastic Behavior

Cylindrical Structural Components

Fatigue Analysis

Finite Element Analysis (FEA)

Cyclic Mechanical LoadYapısal Tasarım

Elastoplastik Davranış

Silindirik Yapısal Bileşenler

Yorulma Analizi

Sonlu Elemanlar Analizi (FEA)

Döngüsel Mekanik Yük

Issues

Article Details

Authors: Erkan Tur

Publisher: Bayburt University

Main Topics: Elektrik Mühendisliği | Makine Mühendisliği

Journal: Bayburt Üniversitesi Fen Bilimleri Dergisi Vol.6 Issue 2, pp.151-171

Document Type: Article

Publication Date: 12/2023

Document Language: English

Document ID (Org No.): 2001307482

pISSN: 2667-579X

Issues

Authors:

Erkan Tur

Publisher:

Bayburt University

Main Topics:

Elektrik Mühendisliği | Makine Mühendisliği

Journal:

Bayburt Üniversitesi Fen Bilimleri Dergisi Vol.6 Issue 2, pp.151-171

Document Type:

Article

Publication Date:

12/2023

Document Language:

English

Document ID (Org No.):

2001307482

pISSN:

2667-579X