摘要
基于运动学的相对运动数学模型,利用物理意义更明确的绕飞方程进行了小卫星绕飞轨道的设计。根据绕飞轨道方程,重点分析了4类常用的绕飞编队构型:同绕飞轨道编队、同面同绕飞中心编队、异面同绕飞中心编队和多绕飞中心编队,总结分析了各种编队轨道设计的约束条件,获得了一般规律性结论。最后通过仿真验证了所提出的绕飞编队轨道设计方法和结论的正确性。
Based on the kinematics model of relative motion, a flying-around equation with clear physical meaning is used to design the flying-around orbit of small satellite. Then the four common flying-around formations are analyzed and focused, including con-flying around orbit formation, coplanar concentric for- mation, non-coplanar concentric formation and multi-centric formation. This paper analyzes the constraints of the four formation orbits and draws the general conclusion of the flying-around orbit design. Simulation validates the correctness of the design examples for the formation and the applicability of the orbit design method.
出处
《航天控制》
CSCD
北大核心
2009年第6期33-37,共5页
Aerospace Control
关键词
小卫星
绕飞构型
编队飞行
轨道设计
Small satellite
Flying-around configuration
Formation flying
Orbit design
