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Sensitivity Analysis of the Nasgro Equation Based on the PZL-130 TC-II Orlik Trainer Aircraft Full Scale Fatigue Test

Piotr Reymer

Piotr Reymer

Military University of TechnologyWarsaw, Poland
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Reymer, Piotr
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Andrzej Leski

Andrzej Leski

  • Łukasiewicz Research Network, Institute of AviationWarsaw, Poland
  • Air Force Institute of TechnologyWarsaw, Poland
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Leski, Andrzej
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Marcin Kurdelski

Marcin Kurdelski

Air Force Institute of TechnologyWarsaw, Poland
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Kurdelski, Marcin
  
28 nov 2023
Sensitivity Analysis of the Nasgro Equation Based on the PZL-130 TC-II Orlik Trainer Aircraft Full Scale Fatigue Test's Cover Image
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Categoría del artículo: research article
Publicado en línea: 28 nov 2023
Páginas: 8 - 17
DOI: https://doi.org/10.2478/fas-2022-0002
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© 2022 Piotr Reymer et al., published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Figure 1.

Test specimen mounted in the test rig and the right front wing spar with installed strain gages.
Test specimen mounted in the test rig and the right front wing spar with installed strain gages.

Figure 2.

Depiction of the PZL-130 load spectrum used during the test.
Depiction of the PZL-130 load spectrum used during the test.

Figure 3.

Location of the CP2 – lower flange of the rear spar near rib No. 2. CP2, critical point No. 2.
Location of the CP2 – lower flange of the rear spar near rib No. 2. CP2, critical point No. 2.

Figure 4.

Global-local model approach.
Global-local model approach.

Figure 5.

Global strain fields and local stresses indicating crack initiation locations.
Global strain fields and local stresses indicating crack initiation locations.

Figure 6.

Cross section of the damaged structure with the initiation and assumed crack propagation.
Cross section of the damaged structure with the initiation and assumed crack propagation.

Figure 7.

Estimated β factor along crack length.
Estimated β factor along crack length.

Figure 8.

Final results depicting sensitivity of the estimation on input data change. SFH, simulated flight hours; SMF, stress multiplication factor.
Final results depicting sensitivity of the estimation on input data change. SFH, simulated flight hours; SMF, stress multiplication factor.

Exemplary results obtained for β value variations

input data β-10% β-5% β β+5% β+10%
[m] W 0.0218 0.0218 0.0218 0.0218 0.0218 0.0218
[m] T 0.005 0.005 0.005 0.005 0.005 0.005
[-] SMF 0.072 0.072 0.072 0.072 0.072 0.072
[MPa] E 72000 72000 72000 72000 72000 72000
[-] n 0.33 0.33 0.33 0.33 0.33 0.33
[MPa] YLD 319 319 319 319 319 319
[MPam-2] KIC 36.75 36.75 36.75 36.75 36.75 36.75
[MPam-2] KC 74.722 74.722 74.722 74.722 74.722 74.722
[-] C 1.71E-10 1.7073E-10 1.7073E-10 1.71E-10 1.7073E-10 1.7073E-10
[-] n 3.353 3.353 3.353 3.353 3.353 3.353
[-] p 0.5 0.5 0.5 0.5 0.5 0.5
[-] q 1 1 1 1 1 1
[-] Cth 1.5 1.5 1.5 1.5 1.5 1.5
[-] Alpha 1.5 1.5 1.5 1.5 1.5 1.5
[h] SFH 7454.96 11040.33 9026.14 7454.96 6240.39 5251.65
7454.96 48.09% 21.08% 0.00% -16.29% -29.55%

Initial data used in the analysis

initial data
[m] W 0.0218
[m] T 0.005
[-] SMF 0.072
[MPa] E 72000
[-] ν 0.33
[MPa] YLD 319
[MPam-2] KIC 36.75
[MPam-2] KC 74.722
[-] C 1.71E-10
[-] n 3.353
[-] p 0.5
[-] q 1
[-] Cth 1.5
[-] Alpha 1.5
[h] SFH 7454.96
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