Fatigue life prediction in frequency domain using thermal-acoustic loading test results of titanium specimen
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DOI 10.1007/s12206-020-2212-y
Journal of Mechanical Science and Technology 34 (10) 2020 Original Article DOI 10.1007/s12206-020-2212-y Keywords: · Fatigue analysis · Thermal-acoustic load · Thermal-acoustic test · Thermal protection system
Fatigue life prediction in frequency domain using thermal-acoustic loading test results of titanium specimen Eun-Su Go1, Mun-Guk Kim1, In-Gul Kim1 and Min-Sung Kim2 1
Correspondence to: In-Gul Kim [email protected]
Citation: Go, E.-S., Kim, M.-G., Kim, I.-G., Kim, M.S. (2020). Fatigue life prediction in frequency domain using thermal-acoustic loading test results of titanium specimen. Journal of Mechanical Science and Technology 34 (10) (2020) ?~?. http://doi.org/10.1007/s12206-020-2212-y
Received April 27th, 2020 Revised
June 4th, 2020
Accepted June 4th, 2020 † This paper was presented at ICMR2019, Maison Glad Jeju, Jeju, Korea, November 27-29, 2019. Recommended by Guest Editor Insu Jeon
2
Department of Aerospace Engineering, Chungnam National University, Daejeon, Korea, Agency for Defense Development, Daejeon, Korea
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 thermalacoustic 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.
1. Introduction
© The Korean Society of Mechanical Engineers and Springer-Verlag GmbH Germany, part of Springer Nature 2020
The temperature of the skin of the fuselage and wings of a high supersonic vehicle is raised to approximately 300 °C by aerodynamic heating during high speed flight. To prevent the transfer of high temperatures into the interior of the vehicle, those structures are designed using a thermal protection system. The thermal protection system consists of outer skin panels and b
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