PSI - Issue 36

Available online at www.sciencedirect.com Available online at www.sciencedirect.com Sci nceD rect Structural Integrity Procedia 00 (2021) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2021) 000 – 000

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Procedia Structural Integrity 36 (2022) 92–99

© 2022 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the conference Guest Editors Abstract The paper deals with the problem of light aircraft structural health monitoring. The phenomenological basis and engineering decisions for methods to monitor accumulated fatigue damage and to register overstress of aircraft principal structural elements have been shown. The proposed fatigue indicator is lightweight and autonomous; the output information of the indicator reflects the inhering feature of the fatigue damage – appearance and growth of surface extrusions and intrusions. The overstress indicator simplicity and reliability of the action is provided by “fuse” principle of the design . © 2022 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) 1. Introduction Certification specifications for Light Sport Aeroplanes (CS-LSA) define the strength requirements for the Light Sport aircraft and confirm the importance of the fatigue analysis (EASA, 2018). Besides the CS-LSA recommendations to stress level for the Parts of Structure Critical to Safety, there are some requirements for the fatigue investigation: higher stress levels need further fatigue investigation using one or a combination of the following methods: (1) By a fatigue test, based on a realistic operating spectrum; (2) by a fatigue calculation using strength values which have been proved to be sufficient by fatigue tests of specimens or components. It is well known, that the trend currently exists to monitor metal fatigue by Structural Health Monitoring Systems. This approach is on the way to be implemented into contemporary large planes. There are many reasons to use fatigue 1st Virtual International Conference “In service Damage of Materials: Diagnostics and Prediction” Structural health monitoring for light aircraft M. Karuskevich a , T. Maslak a *, Ie. Gavrylov a , Ł . Pejkowski b , J. Seyda b a National Aviation University, Liubomyra Huzara Ave. 1, Kyiv 03058, Ukraine b Bydgoszcz U iversity of Science and Technology, S. Kaliski go 7, Bydgoszcz 85-796, Poland Abstract The paper deals with the problem of light aircraft structural health monitoring. The phenomenological basis and engineering decisions for methods o monitor accumulated fatigue damage and to registe overstr ss of aircraft pr ncipal structural eleme ts have been shown. The prop sed f tig e indicator s lightwei ht and autonomous; the output nformatio of the indic tor refl c the inh ring feature of the fatigue damage – appearance and rowth of surface extrusi ns and intrusions. The overstress indicator simplicity and reliability o the action is provided by “fuse” principle of the d sign . © 2022 The Authors. Publis d by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review u der re ponsibility of conference Guest Editors K ywords: Str ctural health monitoring; aircraft; deformation relief; overstress. 1. Introduction Certification specifications for Light Sport Aeroplanes (CS-LSA) define the strength requirements for the Light Sport air raft and conf rm the mportance of the fatigue analysis (EASA, 2018). B sides the CS- SA rec mmend tions to stress level for the P rts of Structure Critic l to Safety, there are some requirem nts for the fatigue i vestigation: higher stress levels need further fatigue investigation using one or a combination f ollowing me hods: (1) By a fa igue t st, bas d on a r alistic operating spectrum; (2) by a fatigue calculation using strength values which have been proved to be sufficient by fatigue te ts of specimens or components. It is well known, th t the trend currently exists to monitor metal fatigue by Structural Health Monitoring Sy tems. This approach is on the way to be implemen ed into contempor ry large planes. There are many reasons to use fatigue 1st Virtual International Conference “In service Damage of Materials: Diagnostics and Prediction” Structural health monitoring for light aircraft M. Karuskevich a , T. Maslak a *, Ie. Gavrylov a , Ł . Pejkowski b , J. Seyda b a National Aviation University, Liubomyra Huzara Ave. 1, Kyiv 03058, Ukraine b Bydgoszcz University of Science and Technology, S. Kaliskiego 7, Bydgoszcz 85-796, Poland Peer-review under responsibility of the conference Guest Editors Keywords: Structural health monitoring; aircraft; deformation relief; overstress.

* Corresponding author. Tel.:+38-066-336-7937. E-mail address: maslak@nau.edu.ua * Corresponding author. Tel.:+38-066-336-7937. E-mail address: maslak@nau.edu.ua

2452-3216 © 2022 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the conference Guest Editors 2452-3216 © 2022 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review u der responsibility of t conference Guest Editors

2452-3216 © 2022 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the conference Guest Editors 10.1016/j.prostr.2022.01.008