辐射开环绳系卫星编队自旋展开动力学与控制策略  

Dynamics and control during spinning deployment for hub-and-spoke configured multi-tethered satellite formation

作　　者：苏飞[1] 翟光[1] 张景瑞[1] 张尧[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空学报》2016年第9期2809-2819,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11102018);国家"863"计划(2013AA7042018)~~

摘　　要：提出了圆轨道辐射开环绳系卫星编队的展开控制策略。首先采用拉格朗日方程建立了辐射开环绳系卫星编队的展开动力学模型,分析了主星姿态与绳长在展开过程的动力学耦合关系;随后以建立的动力学模型为基础,分别研究了编队在重力梯度力补偿和无补偿两种情况下的自旋展开控制策略,通过规划绳系释放速度、主星自旋角速度等变量,实现了绳系编队的有效展开;最后搭建了编队自旋展开的动力学模型,通过数值仿真对所提出的展开策略进行验证,仿真结果表明:在重力梯度力矩补偿和无补偿的情况下,所提出的展开控制策略能够保证编队稳定展开。The deployment strategies for＂hub-and-spoke＂configured tethered satellite formation are investigated in circular orbit.Firstly,the deployment dynamics model is established based on Lagrangian method under some reasonable assumptions.The dynamical coupling between the attitude of central body and the tether length is analyzed,and then the deployment strategies for the cases with and without gravity gradient compensation are developed.By planning the deployment rate and angular velocity of central body,the successful deployments are achieved.Finally,some mathematical simulations for the proposed strategies are implemented.The simulation results indicate that using the proposed deployment strategies,the configuration can be maintained effectively and steadily.

关 键 词：绳系卫星编队 主星姿态 重力梯度力 自旋展开 构型稳定 

分 类 号：V445.4[航空宇航科学与技术—飞行器设计]