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- W2084196942 abstract "Thermal vibration characteristics of a thin walled composite beam attached on spacecraft are investigated in this paper. The composite beam is assumed to have a thin CUS(circumferentially uniform stiffness) wall and modeled with several composite materials which are already space qualified such as T300/Epoxy, YS90AEpoxy. Steady state angle and peak to peak error in spacecraft attitude angle and tip displacement of composite beams are evaluated as a performance index for thermal vibration characteristics. Evaluation results shows that composite beam made out of YS90A has nearly 2 times better than T300 in terms of peak to peak attitude error angle." @default.
- W2084196942 created "2016-06-24" @default.
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- W2084196942 date "2010-12-31" @default.
- W2084196942 modified "2023-09-26" @default.
- W2084196942 title "Thermal Vibration Characteristics of a Thin Walled Composite Beam attached on Spacecraft" @default.
- W2084196942 cites W2046505022 @default.
- W2084196942 doi "https://doi.org/10.7234/kscm.2010.23.6.047" @default.
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