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http://dx.doi.org/10.5139/JKSAS.2002.30.1.056

Papers : Thermally Induced Vibration Analysis of Flexible Spacecraft Appendages  

Yun,Il-Seong
Song,O-Seop
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.30, no.1, 2002 , pp. 56-64 More about this Journal
Abstract
Thermally induced vibration response of composite thin-walled beams is investigated in this paper. The flexible spacecraft appendages modeled as thin-walled beam incorporates a number of nonclassical effects of transverse shear, primary and secondary warping, rotary inertia and anisotropy of constitute materials. Thermally induced vibration responds characteristics of a composite thin walled beam exhibiting the circumferantially uniform system(CUS) configuration are exploited in connection with the structural flapwise bending lagwise bending coupling resulting from directioal properties of fiber reinforced composite materials and ply stacking sequence. A coupled thermal structure gradient is investigated.
Keywords
Thermally Induced Vibration; Composite Material; Solar Heat Flux; Flutter; Stability;
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