Thermal Vibration Characteristics of a Thin Walled Composite Beam attached on Spacecraft

被引：0
|
作者：
Kim, Gyu-Sun
Song, Oseop
机构：
来源：
COMPOSITES RESEARCH | 2010年 / 23卷 / 06期
关键词：
Thermal Vibration; Space Structure; Composite Material; Spacecraft Jitter;
D O I：
暂无
中图分类号：
TB33 [复合材料];
学科分类号：
摘要：
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.
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收藏
页码：47 / 54
页数：8
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