摘要
研究了基于C-W方程的航天器共面圆型快速绕飞问题。分析了2种受迫快速绕飞方法:第1种方法基于C-W方程的解析解,设计了轨道平面内近圆拼接绕飞轨迹,给出了拼接绕飞所需的控制脉冲;第2种方法设计了任意周期的圆型绕飞相对运动参考轨迹,并利用PD控制律对其跟踪。并给出了2种受迫绕飞方法的固定推力形式的控制律。精确轨道仿真结果表明2种方法都能实现对目标航天器轨道平面内的近圆型绕飞。相对于参考轨迹绕飞,拼接绕飞为非标准圆型轨迹,且绕飞周期固定,但是实现拼接绕飞所需的推力器控制开关机次数较少,速度增量也较小。
The spacecraft in-plane circular fast fly-around based on C-W equation is studied in this paper.Two methods for the forced fly-around are presented.In the first method,the natural elliptical trajectories in plane which are obtained based on C-W equation are stitched to be a nearly circular fly-around trajectory.And then the control impulses for stitching fly-around are calculated.In the second method,a reference fly-around trajectory is designed regarding the desired fly-around radius and period.The proportional-differential （PD） control law is used to track the reference trajectory accurately.The control laws of these two forced fly-around are obtained under the assumption of constant thrust.The orbital simulation results show that the both methods can accomplish the fast forced fly-around in plane.By comparing with the reference trajectory fly-around,the trajectory of stitching fly-around is not a standard circle corresponding to a fixed fly-around period.But the on-off times and the velocity increment of thrust for the stitching fly-around control are less than that for the reference trajectory fly-around control.
出处
《航天控制》
CSCD
北大核心
2014年第1期68-72,78,共6页
Aerospace Control
基金
国家自然科学基金资助项目(11172036)
