ИСТИНА

In this paper, the problem of launching two satellites into low-Earth orbit by means of impulsive maneuvers is considered. The maneuvers should be accomplished in a way to provide the change in the longitude of the ascending node of the orbits by 90⁰ and the difference in the value of the true anomaly of satellites by 180⁰. For this purpose, a 3-impulse maneuver was implemented and the transfer time was optimized, resulting in the problem solution using almost 10% less than the prespecified amount of fuel.