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Fatigue life prediction in frequency domain using thermal-acoustic loading test results of titanium specimen

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Abstract

High supersonic vehicles are exposed to high temperature generated by aerodynamic heating. Thermal protection system structures are used on the skin of the fuselage and wings to prevent the transfer of high temperatures into the interior of the vehicle. Thin skin panels can be exposed to acoustic loads by high power engine noise and jet flow noise, which can cause sonic fatigue damage. Therefore, it is necessary to examine the behavior of supersonic/hypersonic vehicle skin structures under thermal-acoustic loads and to predict fatigue life. In this paper, thermal-acoustic testing of titanium specimens under thermal-acoustic load was performed. The response stress history of the specimen was obtained, and the fatigue life was predicted using the time and frequency domain fatigue life prediction method. The effect of the mean stress on the predicted results of the time and frequency domian fatigue life was analyzed. Stress history was generated using a sine series of random phases from stress PSD without phase information. The fatigue life in the generated stress history was predicted using the time and frequency domain fatigue life prediction methods. As the temperature increased, the mean stress of the response stress and the error in the frequency domain fatigue life prediction results increased. The error in the frequency domain fatigue life prediction results with the mean stress effect were greatly reduced by considering the completely reversed stress.

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Abbreviations

a(k):

Best fitting parameters (Wirsching Light)

b :

Benasciutti Tovo method parameter

b(k):

Best fitting parameters (Wirsching Light)

C :

S-N curve coefficient

D :

Damage intensity

f :

Frequency

G 1 :

Dirlik method parameter

G 2 :

Dirlik method parameter

G 3 :

Dirlik method parameter

K Gebber :

Gerber transformation coefficient

K Goodman :

Goodman transformation coefficient

k :

S-N slope coefficient

m i :

i-th spectral moment

\({N_{{f_i}}}\) :

i-th number of cycles to failure

N i :

i-th number of cycles

P DK :

Cycle amplitude probability density function (Dirlik)

Q :

Dirlik method parameter

R :

Dirlik method parameter

S XX :

Power spectral density

t :

Time

Z :

Dirlik method parameter

α i :

Irregularity factor

Γ:

Euler gamma function

ε :

Spectral width

θ k :

Phase

ν 0 :

Rate of zero crossings

ν P :

Rate of peaks

ρ WL :

Empirical correction factor (Wirsching Light)

σ a :

Alternating stress

σ cr :

Completely reversed stress

σ m :

Mean stress

σ u :

Ultimate strength

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Acknowledgments

This work was supported by the Agency for Defense Development (ADD-06-201-801-014), Republic of Korea.

Author information

Authors and Affiliations

  1. Department of Aerospace Engineering, Chungnam National University, Daejeon, Korea

    Eun-Su Go, Mun-Guk Kim & In-Gul Kim

  2. Agency for Defense Development, Daejeon, Korea

    Min-Sung Kim

Authors
  1. Eun-Su Go
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  2. Mun-Guk Kim
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  3. In-Gul Kim
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  4. Min-Sung Kim
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Corresponding author

Correspondence to In-Gul Kim.

Additional information

Eun-Su Go is a Ph.D. student of Department of Aerospace Engineering, Chungnam National University, Daejeon, Republic of Korea. His research interests include impact behavior of composite materials, design and testing of composite structures, and thermal-acoustic fatigue life prediction of aircraft structures.

Mun-Guk Kim received his M.S. degree in Dept. of Aerospace Engineering, Chungnam National University, Daejeon, Republic of Korea. His research interests include pyroshock simulation test, impact behavior of composite materials, thermal-acoustic test, and design and testing of composite structures.

In-Gul Kim is a Professor of Department of Aerospace Engineering, Chungnam National University, Daejeon, Republic of Korea. He received his Ph.D. in Engineering Science & Mechanics from Pennsylvania State University. His research interests include impact behavior of composite materials, structural health monitoring, and design and testing of composite structures.

Min-Sung Kim is Principal Researcher of Aerospace Technology Research Institute, Agency for Defense Development, Daejeon, Republic of Korea. He received his Ph.D. in Aerospace and Mechanical Engineering from Korea Aerospace University. His research interests include smart skin structures, fatigue behavior of metal and composite materials, and analysis and testing of aircraft structures.

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Go, ES., Kim, MG., Kim, IG. et al. Fatigue life prediction in frequency domain using thermal-acoustic loading test results of titanium specimen. J Mech Sci Technol 34, 4015–4024 (2020). https://doi.org/10.1007/s12206-020-2212-y

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  • DOI: https://doi.org/10.1007/s12206-020-2212-y

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