摘要
针对三星编队飞行问题,提出一种绳系控制方法,在自旋刚体卫星的平衡分析的基础上,建立了Thomson和Likins-Pringle平衡构形的绳系三星编队模型,通过对编队系统的稳定性分析得到了两种构形下的稳定条件,并给出了三种控制策略用以解决Likins-Pringle构形不能满足平衡条件的问题。最后经过仿真验证了理论分析的正确性,并对三种控制策略进行了检验,结果表明Thomson构形无须辅助手段,在满足特定条件下可以稳定运行,Likins-Pringle构形采用弹簧系统和喷气辅助绳系控制时满足特定条件也可以稳定运行。
A tethered control method was studied in order to solve three satellites formation flying problem. Based on the equilibrium analysis of spinning rigid body satellite, the Thomson and Likins-Pringle equilibrium modeling of three satellites formation flying using tethers were established. The equilibrium conditions were obtained through equilibrium analysis of formation system, and then three control methods were presented to solve disequilibrium problem of Likins- Pringle equilibrium system. Simulation results demonstrate that the Thomson equilibrium system will be in steady-spin motion with specific conditions, and Likins-Pringle equilibrium system will operate steadily using spring system and tethers added with thrusters control methods under specific conditions.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2011年第1期76-83,共8页
Chinese Space Science and Technology
基金
国家自然科学基金(60974107)
南京航空航天大学基本科研业务费专项(NS2010219)
关键词
编队飞行
绳系控制
平衡构形
微小卫星
Formation flying Tethered. control Equilibrium modeling Micro-satellite
