微纳卫星共面伴飞相对运动椭圆短半轴最省燃料控制.

It is essential to save fuel in orbit control for micro/nano satellite due to the lack of resources. The influences of control direction and control time on the relative ellipse semi-minor axis in in-plane companion-flying satellites were studied based on the Hill equation. Both theoretical analysis and simulation results show that the most efficient control method of relative ellipse semi-minor axis is to impose control parallel to the lateral direction on the top or bottom points while the control quantity ∣ΔV∣⩽nb/2 is certain and the relative ellipse semi-minor axis will change ∣Δb∣ = 2∣ΔV∣/n at the same time. [ABSTRACT FROM AUTHOR]