Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft
Military aircraft are subjected to highly variable and unpredictable loads due to diverse mission profiles, armament configurations, and individual piloting styles. This variability complicates the definition of precise load spectra, particularly in cases where data loss occurs due to Flight Data Re...
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| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
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Sciendo
2024-10-01
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| Series: | Fatigue of Aircraft Structures |
| Subjects: | |
| Online Access: | https://doi.org/10.2478/fas-2023-0010 |
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| _version_ | 1846143476605911040 |
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| author | Reymer Piotr Kowalczyk Kamil Baran Marta Nowakowski Dominik Dziendzikowski Michał Leski Andrzej |
| author_facet | Reymer Piotr Kowalczyk Kamil Baran Marta Nowakowski Dominik Dziendzikowski Michał Leski Andrzej |
| author_sort | Reymer Piotr |
| collection | DOAJ |
| description | Military aircraft are subjected to highly variable and unpredictable loads due to diverse mission profiles, armament configurations, and individual piloting styles. This variability complicates the definition of precise load spectra, particularly in cases where data loss occurs due to Flight Data Recorder (FDR) malfunctions or data mishandling. This paper investigates the use of different flight parameters, such as load factor (nz), barometric height (Hb), and horizontal velocity (Vp), to define load sequences for the PZL-130 “Orlik” TC-II military trainer aircraft. These sequences were then used to evaluate crack propagation using Compact Tension (CT) specimens. The results show that the incorporation of additional flight parameters improves the accuracy of crack propagation predictions when compared to direct strain measurements. This study highlights the potential of using available flight data to develop reliable load spectra for fatigue life estimation in military aircraft, even when direct load measurements are not financially feasible. |
| format | Article |
| id | doaj-art-0b7a652a6f11474cb8959110d1d88954 |
| institution | Kabale University |
| issn | 2300-7591 |
| language | English |
| publishDate | 2024-10-01 |
| publisher | Sciendo |
| record_format | Article |
| series | Fatigue of Aircraft Structures |
| spelling | doaj-art-0b7a652a6f11474cb8959110d1d889542024-12-02T12:05:36ZengSciendoFatigue of Aircraft Structures2300-75912024-10-0120231515516510.2478/fas-2023-0010Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer AircraftReymer Piotr0Kowalczyk Kamil1Baran Marta2Nowakowski Dominik3Dziendzikowski Michał4Leski Andrzej51Air Force Institute of Technology, Ks. Bolesława 6, 01-494Warsaw, Poland1Air Force Institute of Technology, Ks. Bolesława 6, 01-494Warsaw, Poland1Air Force Institute of Technology, Ks. Bolesława 6, 01-494Warsaw, Poland1Air Force Institute of Technology, Ks. Bolesława 6, 01-494Warsaw, Poland1Air Force Institute of Technology, Ks. Bolesława 6, 01-494Warsaw, Poland2Military University of Technology, gen. Sylwestra Kaliskiego 2, 00-908Warsaw, PolandMilitary aircraft are subjected to highly variable and unpredictable loads due to diverse mission profiles, armament configurations, and individual piloting styles. This variability complicates the definition of precise load spectra, particularly in cases where data loss occurs due to Flight Data Recorder (FDR) malfunctions or data mishandling. This paper investigates the use of different flight parameters, such as load factor (nz), barometric height (Hb), and horizontal velocity (Vp), to define load sequences for the PZL-130 “Orlik” TC-II military trainer aircraft. These sequences were then used to evaluate crack propagation using Compact Tension (CT) specimens. The results show that the incorporation of additional flight parameters improves the accuracy of crack propagation predictions when compared to direct strain measurements. This study highlights the potential of using available flight data to develop reliable load spectra for fatigue life estimation in military aircraft, even when direct load measurements are not financially feasible.https://doi.org/10.2478/fas-2023-0010fatigue crack propagationflight parametersload sequence |
| spellingShingle | Reymer Piotr Kowalczyk Kamil Baran Marta Nowakowski Dominik Dziendzikowski Michał Leski Andrzej Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft Fatigue of Aircraft Structures fatigue crack propagation flight parameters load sequence |
| title | Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft |
| title_full | Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft |
| title_fullStr | Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft |
| title_full_unstemmed | Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft |
| title_short | Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft |
| title_sort | crack propagation tests for load sequences developed using different flight parameters of a trainer aircraft |
| topic | fatigue crack propagation flight parameters load sequence |
| url | https://doi.org/10.2478/fas-2023-0010 |
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