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.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2010年第11期2465-2470,共6页
Journal of Astronautics
基金
国家自然科学基金(10702078)
关键词
连续小推力
快速绕飞
卫星编队
速度增量
Continuous low thrust
Fast fly around
Satellite formation flight
Velocity increment