文章导读
总览 评价 闫玉龙 ， 岳宝增 * ， 刘峰 （ 北京理工大学宇航学院，北京 100081； ） 摘要： 本文基于能量-Casimir法研究了含有柔性附件的充液航天器系统的稳定性。首先，将燃料晃动和柔性附件分别简化为弹簧-质量块模型和剪切梁模型，建立了航天器系统的刚-
闫玉龙， 岳宝增*， 刘峰
（
北京理工大学宇航学院，北京 100081； ）
摘要：
本文基于能量-Casimir法研究了含有柔性附件的充液航天器系统的稳定性。首先，将燃料晃动和柔性附件分别简化为弹簧-质量块模型和剪切梁模型，建立了航天器系统的刚-液-柔耦合模型，通过分析主刚体、液体燃料和柔性附件各部分的动能和势能，推导得到系统的能量-Casimir函数；接着，计算能量-Casimir函数的一阶变分和二阶变分，从而推导出航天器系统姿态非线性稳定的条件；最后通过数值计算，得到了的参数空间中系统的稳定和不稳定区域。研究结果显示，航天器刚体的转动惯量、剪切梁的长度、航天器自旋角速度以及储液腔的充液比对航天器的姿态稳定性有较大的影响。
关键词：
动力学与控制；能量-Casimir法；液体晃动；非线性稳定
Yan Yulong， Yue Baozeng*， Liu Feng
（
School of Areospace Engineering ,Beijing Institute of Technology, Beijing 100081； ）
Abstract：
In this paper, the stability of liquid filled spacecraft with flexible appendage was researched by using energy-Casimir method. Liquid sloshing dynamics simplified by spring-mass model, and flexible appendage modeled as a linear shear beam. Rigid-liquid-flexible coupling dynamic of spacecraft was built. The Hamiltonian and Casimir function were derived by analyzing energy function of rigid body, liquid sloshing and flexible appendage. The condition of nonlinear stability of coupling spacecraft system was derived by the calculation of the first and second variation of Casimir function which we added to the Hamiltonian. The stable and unstable region of the parameter space were given in the final section by numerical computation. Related results shown that inertia matrix, the length of shearing beam, spacecraft spinning rate, and filled ratio of liquid fuel tank have strong influence on the stability of coupled spacecraft system.
Tag：
点此返回栏目查看更多>>>参考论文
