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

页码：999 / 1005

页数：6

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