The effect on fatigue life for dynamic behavior of external fuel tank horizontal fin

Kim, Geun-Won; Shin, Kisu

doi:10.5139/jksas.2012.40.3.209

Cited by 2 publications

(2 citation statements)

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“…1 Kang et al conducted a study that involved a crack analysis and redesign of a F-5 EFT horizontal fin, 2 and Lee et al undertook a predictive study of the aero-elastic properties of a F-5 horizontal fin according to the shapes of external attachments. 3 Kim and Shin studied the effects of the dynamic behavior of the horizontal fin of an EFT on the fatigue life, 4 and Kang et al conducted an aircraft safety analysis by studying the longitudinal stability and release trajectories of an EFT. 5 In addition, Uhm et al performed a numerical analysis and structural tests of a wing support structure, 6 and Lee et al investigated a simplified model of external attachments as part of an the analysis of aircraft dynamics.…”

Section: Introductionmentioning

confidence: 99%

Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Kim

An³

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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An external fuel tank, one of the main components of an aircraft, is a component that extends the range of the aircraft and that should be separable from the aircraft in emergency situations. During flight, if structural damage occurs in an external fuel tank, the survivability of the aircraft may be catastrophically affected. Therefore, the structural integrity of such external fuel tanks must be proven under flight-load conditions applied to the external fuel tank during flight. This study presents the results of a structural test conducted to verify the structural integrity of an external fuel tank for flight-load conditions. In the main text, the process of converting the six-component flight load into a test load is described, and a whiffle tree application plan is presented for efficient testing. Then, the reliability of the test load was confirmed by comparing it with the required flight load. As a result of the structural test, the test loads were stably controlled. It was also confirmed that the internal pressure of the test specimen measured in real time during the test was maintained well within the required pressure range and that the behavior of the EFT was suitably predicted through a numerical analysis. After the structural test, it was found through an inspection that the test specimen did not undergo serious structural damage under the required flight-load condition. In conclusion, through structural testing, it was validated that the newly developed external fuel tank had sufficient structural integrity under all required flight-load conditions.

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Section: Introductionmentioning

confidence: 99%

Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Kim

An³

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

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“…Various fatigue damage models ap-plied to fatigue damage analysis of a broadband response spectrum were introduced, and numerical comparative studies for selecting fatigue damage models suitable for riser fatigue analysis were conducted [4,5] Eight types of PSD analysis methods were introduced, and their accuracies and errors were analyzed [6,7]. Four types of PSD analysis methods used for the frequency domain fatigue analysis were compared, and the fatigue life of the aircraft was predicted using Dirlik and Benasciutti-Tovo methods [8] Time domain and frequency domain fatigue analysis were performed for a F-5 plane and compared [9]. A gearbox housings of high-speed trains were analyzed by time domain, frequency domain, and time-frequency domain analysis [10].…”

Section: Introductionmentioning

confidence: 99%

Comparison of Fatigue Analysis Results in the Frequency Domain using PSD data and specific load

Jang¹,

Cho²,

Lee³

et al. 2019

J. ICT des. eng. technol. sci.

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This study investigated the axial sensitivity of the aircraft structure to fatigue. Fatigue analysis for an aircraft needs to be done during a design stage to prevent fatigue failure during operation. Fatigue analysis can be done in a time domain or a frequency domain, and frequency domain analysis is more frequently used. Frequency domain analysis for an aircraft normally uses PSD data translated from the vibration experienced for its whole lifetime. If vibration information is insuf icient in the PSD, it is supplemented by adding speci ic loads. In this study, the analysis was done using the PSD data with 7 different additional loads. The life was sensitive to the magnitude and direction of the load, and some loads increase the life. It was found that the aircraft structure is safe from fatigue failure. Since the fatigue test has not yet been carried out, further testing should be done. Also, further study will investigate how to quantify the sensitivity ratio of direction and magnitude of loads under various conditions.

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The effect on fatigue life for dynamic behavior of external fuel tank horizontal fin

Cited by 2 publications

References 0 publications

Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Validation of the structural integrity of an aircraft external fuel tank through a structural test under flight-load conditions

Comparison of Fatigue Analysis Results in the Frequency Domain using PSD data and specific load

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