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

Fatigue of Aircraft Structures
Volume 2022 (2022): Issue 14 (December 2022)
By:
Open Access
|Nov 2023

Figures & Tables

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 dataβ-10%β-5%ββ+5%β+10%
[m]W0.02180.02180.02180.02180.02180.0218
[m]T0.0050.0050.0050.0050.0050.005
[-]SMF0.0720.0720.0720.0720.0720.072
[MPa]E720007200072000720007200072000
[-]n0.330.330.330.330.330.33
[MPa]YLD319319319319319319
[MPam-2]KIC36.7536.7536.7536.7536.7536.75
[MPam-2]KC74.72274.72274.72274.72274.72274.722
[-]C1.71E-101.7073E-101.7073E-101.71E-101.7073E-101.7073E-10
[-]n3.3533.3533.3533.3533.3533.353
[-]p0.50.50.50.50.50.5
[-]q111111
[-]Cth1.51.51.51.51.51.5
[-]Alpha1.51.51.51.51.51.5
[h]SFH7454.9611040.339026.147454.966240.395251.65
7454.9648.09%21.08%0.00%-16.29%-29.55%

Initial data used in the analysis

initial data
[m]W0.0218
[m]T0.005
[-]SMF0.072
[MPa]E72000
[-]ν0.33
[MPa]YLD319
[MPam-2]KIC36.75
[MPam-2]KC74.722
[-]C1.71E-10
[-]n3.353
[-]p0.5
[-]q1
[-]Cth1.5
[-]Alpha1.5
[h]SFH7454.96
DOI: https://doi.org/10.2478/fas-2022-0002 | Journal eISSN: 2300-7591 | Journal ISSN: 2081-7738
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Language: English
Page range: 8 - 17
Published on: Nov 28, 2023
Published by: Institute of Aviation
In partnership with: Paradigm Publishing Services
Publication frequency: 1 issue per year
Keywords:
sensitivity analysis,
crack propagation,
full scale fatigue test
Related subjects:
Engineering,
Introductions and overviews,
Engineering, other

© 2023 Piotr Reymer, Andrzej Leski, Marcin Kurdelski, published by Institute of Aviation
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

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