Stability of nonlinear vibrations of a deploying flexible beam from a spacecraft

被引：0
|
作者：
J. Li
Zh. Wang
机构：
[1] Dept. of Engineering Mechanics,
[2] Tsinghua University,undefined
[3] Beijing 100084,undefined
[4] China,undefined
[5] e-mail: Lijunf@mail.tsinghua.edu.cn,undefined
来源：
Zeitschrift für angewandte Mathematik und Physik ZAMP | 1999年 / 50卷
关键词：
Key words. Spacecraft, deploying flexible beam, rigid-flexible coupled system, partial stability.;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
In this paper, stability of a complex spacecraft is studied by the use of two new models. The first, is a rigid-flexible model, which consists of a rigid body and a deploying flexible beam; while the second, includes a liquid filled rigid body with a deploying flexible beam. In particular, the deploying beam in both models is assumed to have a finite deflection profile. It has been proved that nonlinear transverse vibrations of a beam are stable when undergoing uniform extension or retrieval.
引用
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页码：999 / 1005
页数：6
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