Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards
To achieve the commercialization of electric vertical takeoff and landing (eVTOL) aircrafts, which have recently garnered attention as the next-generation means of transportation, objective certification based on rigorous procedures is essential. With the advancement of structural analysis technolog...
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| Format: | Article |
| Language: | English |
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MDPI AG
2024-01-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/11/1/91 |
| _version_ | 1797344925549854720 |
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| author | Young-Cheol Kim Dong-Hyeop Kim Sang-Woo Kim |
| author_facet | Young-Cheol Kim Dong-Hyeop Kim Sang-Woo Kim |
| author_sort | Young-Cheol Kim |
| collection | DOAJ |
| description | To achieve the commercialization of electric vertical takeoff and landing (eVTOL) aircrafts, which have recently garnered attention as the next-generation means of transportation, objective certification based on rigorous procedures is essential. With the advancement of structural analysis technology, aircraft airworthiness standards recommend a combination of testing and analytical methods to demonstrate structural integrity. In this study, we propose analytical techniques for demonstrating the structural integrity of components for eVTOL aircrafts in accordance with airworthiness standards. We evaluated the static structural integrity and fatigue safety of an electro-mechanical actuator. Multibody dynamics analysis was performed to calculate the loads for application in finite element analysis. Subsequently, static analysis and fatigue analysis based on finite element analysis were conducted to calculate the safety margin and fatigue life of all key components. Therefore, we have confirmed the feasibility of utilizing analytical methods for the structural integrity assessment of aircraft components. We propose the utilization of the technique introduced in this study as one of the approaches for demonstrating compliance with airworthiness standards for eVTOL aircrafts through the application of analytical methods. |
| first_indexed | 2024-03-08T11:09:56Z |
| format | Article |
| id | doaj.art-fa4682c02bff45d98a00f81caa3056d3 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-08T11:09:56Z |
| publishDate | 2024-01-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-fa4682c02bff45d98a00f81caa3056d32024-01-26T14:14:11ZengMDPI AGAerospace2226-43102024-01-011119110.3390/aerospace11010091Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification StandardsYoung-Cheol Kim0Dong-Hyeop Kim1Sang-Woo Kim2School of Aerospace and Mechanical Engineering, Korea Aerospace University, Goyang-si 10540, Gyeonggi-do, Republic of KoreaSchool of Aerospace and Mechanical Engineering, Korea Aerospace University, Goyang-si 10540, Gyeonggi-do, Republic of KoreaSchool of Aerospace and Mechanical Engineering, Korea Aerospace University, Goyang-si 10540, Gyeonggi-do, Republic of KoreaTo achieve the commercialization of electric vertical takeoff and landing (eVTOL) aircrafts, which have recently garnered attention as the next-generation means of transportation, objective certification based on rigorous procedures is essential. With the advancement of structural analysis technology, aircraft airworthiness standards recommend a combination of testing and analytical methods to demonstrate structural integrity. In this study, we propose analytical techniques for demonstrating the structural integrity of components for eVTOL aircrafts in accordance with airworthiness standards. We evaluated the static structural integrity and fatigue safety of an electro-mechanical actuator. Multibody dynamics analysis was performed to calculate the loads for application in finite element analysis. Subsequently, static analysis and fatigue analysis based on finite element analysis were conducted to calculate the safety margin and fatigue life of all key components. Therefore, we have confirmed the feasibility of utilizing analytical methods for the structural integrity assessment of aircraft components. We propose the utilization of the technique introduced in this study as one of the approaches for demonstrating compliance with airworthiness standards for eVTOL aircrafts through the application of analytical methods.https://www.mdpi.com/2226-4310/11/1/91airworthiness standardelectro-mechanical actuatornumerical approachstructural analysisfatigue evaluation |
| spellingShingle | Young-Cheol Kim Dong-Hyeop Kim Sang-Woo Kim Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards Aerospace airworthiness standard electro-mechanical actuator numerical approach structural analysis fatigue evaluation |
| title | Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards |
| title_full | Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards |
| title_fullStr | Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards |
| title_full_unstemmed | Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards |
| title_short | Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards |
| title_sort | evaluation of the multiaxial fatigue life of electro mechanical actuator for aircraft blade pitch control based on certification standards |
| topic | airworthiness standard electro-mechanical actuator numerical approach structural analysis fatigue evaluation |
| url | https://www.mdpi.com/2226-4310/11/1/91 |
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