FIELD: space technology.
SUBSTANCE: invention relates to space technology, and more specifically to the convergence of space objects. The method for controlling the movement of a space object (SO) when approaching another space object (ASO) includes putting the SO into a reference orbit with a deviation from the plane of the orbit of the ASO by the longitude of the ascending node of the orbit by an amount of ΔλAN and by an inclination by an amount of Δi, but with a given mismatch by the argument of latitude ΔФ, and applying approach pulses to the SO for docking with the ASO. At the same time, after placing the SO into the reference orbit, it is transferred to an intermediate orbit, coplanar and coelliptic with respect to the orbit of the ASO with a height difference of ΔН, which is determined taking into account the actual value of ΔФ. The transition is carried out by applying pulses ΔVi. Next, a ΔVTRANS pulse is applied to the SO, directed along the velocity vector of the SO, for the transition of the space object to the orbit of a meeting with another space object, and then the spacecraft is connected to the ASO.
EFFECT: reduction in the number of turns before docking is achieved.
1 cl, 5 dwg
