充液挠性航天器俯仰运动分岔特性初步研究  

BIFURCATION OF A LIQUID-FILLED SPACECRAFT WITH ELASTIC APPENDAGES

作　　者：吕敬[1] 李俊峰[1] 王天舒[1] 岳宝增[2] 

机构地区：[1]清华大学航天航空学院,北京100084 [2]北京理工大学理学院,北京100081

出　　处：《工程力学》2008年第4期200-203,共4页Engineering Mechanics

基　　金：国家自然科学基金项目(10172048,10302013,10572022)

摘　　要：该文考虑了带弹性帆板与液体燃料的航天器做俯仰运动时刚-液-弹之间的相互耦合作用,采用已推导的刚-液-弹耦合系统非线性动力学方程组,应用多尺度法解析分析耦合系统的液体一阶主共振,利用奇异性理论对分岔方程进行分析,得到多种分岔模式,随后根据该文研究的耦合系统物理系数范围,确定只存在滞后点分岔,表现为幅频曲线软、硬特性的转换现象。The coupling dynamics of the pitching of spacecraft, the sloshing of liquid fuel and the vibration of elastic appendages are investigated. The coupling dynamics equations deduced by using H-O principle are adopted. The multiple scale method is proposed to analyze the primary resonance of the rigid-liquid-elastic coupling system. The bifurcation analysis is given by means of singularity theory. The hysteresis bifurcation is found in the desired coupling system, it is represented by the amplitude-frequency response switches between soft and hard spring types at the critical depth.

关 键 词：俯仰 刚-液-弹耦合系统 多尺度 分岔 软、硬特性 

分 类 号：V249.122.2[航空宇航科学与技术—飞行器设计] V233.91