快速绕飞卫星空间圆编队设计方法  

Fast Fly Around Satellite Space Circle Formation Design

作　　者：王功波[1] 孟云鹤[1] 郑伟[1] 汤国建[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2010年第11期2465-2470,共6页Journal of Astronautics

基　　金：国家自然科学基金(10702078)

摘　　要：连续小推力条件下,针对圆参考轨道卫星,推导了满足快速绕飞条件的空间圆编队动力学模型。分析了一个绕飞周期内的燃耗情况。在绕飞周期确定的条件下,给出了最小燃耗的计算方法,并利用数值方法验证了所推导公式的正确性。计算结果表明,在高度为500km的圆轨参考道卫星实现周期为10分钟、半径100m的空间圆绕飞,一个绕飞周期所需最小速度增量约为4.77m/s。文章提出的基本设计原理并不局限于空间圆编队,也可用于其它快速绕飞编队的设计工作。A control law based on continuous low thrust is derived to realize fast fly around space circle formation flight on circle orbit.The fuel expenditure in a formation flight period is determined by analytical expression,and an optimality criterion is developed such that this fuel expenditure is minimized.Validity of the conclusion is proved by numerical method.Simulation results show that the minimum velocity increment is approximately 4.77m /s when the chief spacecraft＇s altitude orbit is 500km,with 10 min of formation flight period 10 minutes and 100m of circle radius.The control strategy presented in this paper can not only be used in fast space circle formation flight,but also be appropriate to other fast fly around formation flight.

关 键 词：连续小推力 快速绕飞 卫星编队 速度增量 

分 类 号：V448[航空宇航科学与技术—飞行器设计]