摘要
将航天器铰接结构简化为具有局部铰链非线性约束的多自由度系统,提出了对该类非线性系统动力学特性进行分析的方法。即首先通过拟合模态方法建立铰接结构系统的非线性动力学模型,然后通过数值方法得到系统的非线性模态,并以之为基础对铰接结构的基频特性进行研究。
Space joint-dominated structrues are widely used in many core components of modern spacecraft, such as solar arrays, antennas, etc. The dynamic behavior of space joint-dominated structure has a great impact on the stabilities and dynamic behaviors of spacecraft system. In order to indicate the dynamic behavior of the joint-dominated structure and then model the spacecraft system perfectly, it is importance to model the nonlinear subsystem and investigate its nonlinear dyamic behavior. This paper presents an approach to model the nonlinear subsystem and analyze it based on nonlinear normal modes. The advantages of this approach are to consider the joint- dominated structure as a multi-degrees system with local nonlinear constrains and then define the nonlingar normal modes as a movement on the invariant manifolds.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2005年第3期19-27,共9页
Chinese Space Science and Technology
