哑铃型航天器刚-柔耦合动力学建模与仿真分析  

RIGID-FLEXIBLE DYNAMIC MODELING AND SIMULATION OF DUMBBELL SPACECRAFT

作　　者：王博洋 刘铸永[1] 郑鹏飞 Wang Boyang;Liu Zhuyong;Zheng Pengfei(School of Naval Architecture,Ocean&Civil Engineering,Shanghai Jiao Tong University,Shanghai,200240,China;Aerospace System Engineering,Shanghai 201109,China)

机构地区：[1]上海交通大学船舶海洋与建筑工程学院,上海200240 [2]上海宇航系统工程研究所,上海201109

出　　处：《动力学与控制学报》2021年第6期25-32,共8页Journal of Dynamics and Control

基　　金：国家自然科学基金项目(11772188);上海宇航系统工程研究所项目(20GFH-HT01-246)。

摘　　要：为满足深空探测的需求,需要构建一种全新的哑铃型航天器.由于构型和质量分布的差异,传统"中心刚体+柔性附件"动力学模型将不再适用,因此必须针对该构型建立一种高效准确的动力学模型.本文基于小变形假设,利用浮动坐标法,采用多体系统动力学单向递推组集方法,建立了哑铃型航天器的刚-柔耦合动力学模型.该模型考虑了哑铃型航天器的轨道-姿态-变形之间的耦合效应,保留了全部变形高次耦合项.通过采用本文方法建立的"刚体-桁架-刚体"模型和已有的两种哑铃型航天器模型,对典型算例进行动力学仿真和比较.仿真结果表明,本文模型很好地反映了哑铃型航天器的刚-柔耦合动力学特性,末端物体的转动惯量将会影响系统的动力学响应,不能简单忽略.本研究将为哑铃型航天器的总体设计,特别是控制规律的设计,提供重要的技术支持.A new configuration of spacecraft was designed for deep space exploration. Due to difference of configuration and mass distribution,the traditional dynamic modeling method is no longer suitable for this configuration. In order to satisfy the requirement of overall design of dumbbell spacecraft,an efficient and accurate dynamic model must be established for this configuration. In this paper,based on a small deformation assumption,a rigid-flexible coupling dynamic model of dumbbell spacecraft was established using a forward recursive method in the floating frame of reference formulation.The orbit-attitude-deformation coupling effects were taken into account,and all the high-order coupling terms of deformation were kept. The numerical simulations of the "rigid body-truss-rigid body" model proposed in this paper and two existing models were carried out,indicating that the inertia moment of the end object cannot be ignored,but the proposed model can capture the rigid-flexible coupling dynamics characteristics of dumbbell spacecraft well. This paper will provide an important technical support for the overall design,especially for the controller design of dumbbell spacecraft.

关 键 词：哑铃型航天器 刚-柔耦合动力学 多体系统 单向递推组集方法 数值仿真 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]