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Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft

Piotr Reymer

Piotr Reymer

  • Air Force Institute of TechnologyWarsaw, Poland
  • Military University of TechnologyWarsaw, Poland
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Reymer, Piotr
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Kamil Kowalczyk

Kamil Kowalczyk

Air Force Institute of TechnologyWarsaw, Poland
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Kowalczyk, Kamil
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Marta Baran

Marta Baran

Air Force Institute of TechnologyWarsaw, Poland
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Baran, Marta
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Dominik Nowakowski

Dominik Nowakowski

Air Force Institute of TechnologyWarsaw, Poland
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Nowakowski, Dominik
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Michał Dziendzikowski

Michał Dziendzikowski

Air Force Institute of TechnologyWarsaw, Poland
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Dziendzikowski, Michał
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Andrzej Leski

Andrzej Leski

  • Military University of TechnologyWarsaw, Poland
  • Lukasiewicz Research Network – Institute of AviationWarsaw, Poland
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Leski, Andrzej
  
28 ott 2024
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Categoria dell'articolo: Research Article
Pubblicato online: 28 ott 2024
Pagine: 155 - 165
DOI: https://doi.org/10.2478/fas-2023-0010
Parole chiave
© 2023 Piotr Reymer et al., published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Figure 1.

Location of strain gauges during the OLM and the SLM14 sensor
Location of strain gauges during the OLM and the SLM14 sensor

Figure 2.

Technical drawing of the CT samples used in the test and the mount
Technical drawing of the CT samples used in the test and the mount

Figure 3.

Test specimen mounted in the test stand, shown during (with a COD gauge) and after the test.
Test specimen mounted in the test stand, shown during (with a COD gauge) and after the test.

Figure 4.

Crack propagation curves obtained for different load spectra
Crack propagation curves obtained for different load spectra

Linear regression model parameters for the SLMX14 equations using flight parameters

Independent variables R R2 free coefficient a b c
nz 0.9320 0.8686 -64.1018 388.8242 - -
nz, Hb 0.9459 0.8947 -113.747 368.296 0.046 -
nz, Hb, Vp 0.9742 0.9491 -231.156 332.524 0.032 0.726

Correlation matrix for the available flight parameters

Variable SLMX14 nz Hb VP dh dkl dl dv
SLMX14 1.00 0.93 0.43 0.61 0.37 -0.30 -0.03 -0.07
nz 0.93 1.00 0.29 0.39 0.28 -0.14 -0.08 -0.03
Hb 0.43 0.29 1.00 0.30 0.42 -0.49 0.09 0.17
VP 0.61 0.39 0.30 1.00 0.22 -0.46 -0.08 -0.15
dh 0.37 0.28 0.42 0.22 1.00 0.08 -0.04 0.22
dkl -0.30 -0.14 -0.49 -0.46 0.08 1.00 -0.00 0.15
dl -0.03 -0.08 0.09 -0.08 -0.04 -0.00 1.00 -0.15
dv -0.07 -0.03 0.17 -0.15 0.22 0.15 -0.15 1.00

Load sequence characteristics

Sequence SLMX14 nz nz+Hb nz+Hb + Vp
Number of cycles 52894 30434 28241 25348
SFH 270.6 266.7 267.7 271

Dimensions of the CT specimens used in the test

W [mm] B [mm] Width [mm] Height [mm] Holes [fi_mm] Notch [mm] CS [mm2] Precrack [mm] H [mm]
48 8 60 57.6 12 21.6 307.2 1 3
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