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It is essential to save fuel in orbit control for micro/nano companion satellite due to the lack of resources. The minimum fuel control strategy of the relative ellipse phase in in-plane companion-flying was studied based on the Hill equation and the extreme value theory of dual function. When the phase needed to change is acute angle, and the velocity increment is less than the result that multiplies half of orbit's mean angular by the relative ellipse semi-minor axis (ΔV < 0.5 nb), the theoretical analysis results show that the most efficient control method of the relative ellipse phase is impulsive control parallel to the lateral direction, the velocity increment is the result that multiplies half of orbit's mean angular, the relative ellipse semi-minor axis by the absolute of phase's cosine (ΔV = 0.5 nb | cos Θ |), and the phase will be the left (the phase is π/2) or right (the phase is - π/2) point of relative ellipse after control. The relative ellipse semi-minor axis can be reduced at the same time. When the phase needed to change is not acute angle, it is needed to be divided into several acute angles for saving fuel. Furthermore, the orbit control strategy of a companying satellite s phase control was gained by applying the theory. [ABSTRACT FROM AUTHOR]

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]

Currently, the most commonly used pattern in space target observation of space-based optical system is natural intersection mode which needs a long coverage period, and the effect of atmosphere radiation of the earth on space target observation is not estimated. Based on the characteristics of space-based platforms on sun-synchronous orbit, several observation modes for GEO targets were planned and analyzed, transforming the effect of atmosphere radiation of earth on space target observation into a camera off-axis angle constraints, which is valuable for engineering application. The observation efficiency was evaluated from several aspects such as attitude modes, coverage time and observing arc. Both theoretical analysis and simulation results show that the regional staring mode has a big advantage for GEO object observation. The coverage time is less than 24 hours, while the attitude mode is comparatively simple, and the observing arc is longer. [ABSTRACT FROM AUTHOR]