Thermal stresses in the structural elements of the supersonic aircraft cockpit

Belov, V. V.

doi:10.1063/1.5117457

Cited by 1 publication

(2 citation statements)

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“…where σ th is the threshold stress, n is the true stress exponent, Q is the true activation energy, the rest symbols in Equation (2) have the same meanings as indicated in Equation (1). Assuming that σ th independent of the creep stress, if an appropriate value of n can be fitted to a straight line through the data points in the plot of .…”

Section: Creep Mechanism and Threshold Stressmentioning

confidence: 99%

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Creep Behavior and Microstructural Evolution of Al–Cu–Mg–Ag Alloys with Various High Cu Contents

Peng

Wang

Yang

et al. 2021

Metals

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The creep behavior and microstructural evolution of three Al–Cu–Mg–Ag alloys with Cu content around its solid solubility limit in Al (5.65 wt %) were investigated at 180–240 °C and applied stress of 150–300 MPa. The creep resistance of aged alloy, which is mainly determined by the number density of Ω phase, is the best for 6.00 wt % Cu, better for 5.30 wt % Cu, and the worst for 5.65 wt % Cu. After solid-solution treatment, the lowest Cu content in the Al matrix for the alloy with 5.65 wt % Cu is observed due to the existence of more residual phases. It results in the lowest number density of Ω phase the following aging and poor creep resistance. Increasing temperature from 180 to 240 °C at the same stress (225 MPa), the steady creep rate of alloys increases by 225 times, which is apparently larger than that (26 times) for increasing stress from 225 to 300 MPa at the same temperature (180 °C). It indicates that the coarsening of the Ω phase with increasing temperature should be more serious than that with increasing stress. The creep mechanism of Al–Cu–Mg–Ag alloy can be attributed to the dislocation climb with the existence of threshold stress.

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Section: Creep Mechanism and Threshold Stressmentioning

confidence: 99%

“…With the fast development of aerospace industries, the requirements of the hightemperature performance of supersonic aircraft are increasing [1,2]. The temperature for the covering skin of supersonic aircraft can reach 150 • C in service and even reach 300 • C in some extreme cases, and then it is prone to creep fracture [3,4].…”

Section: Introductionmentioning

confidence: 99%