THE CALCULATION FEATURES OF FLYBY MANEUVERS OF A SPACE VEHICLE SEQUENTIALLY TAKING THE OBJECTS OF LARGE-SIZE SPACE DEBRIS TO LOW DISPOSAL ORBITS

摘要

The article regards the flyby problem concerned with large-size space debris (LSSD) objects in low Earth orbits. The data on overall sizes of known upper-stages and last stages of launch-vehicles make it possible to mark out five compact groups of such objects from the NORAD catalogue in 600-2000 km altitude interval. Flyby maneuvers are being executed by a single space vehicle (SV) which transfers the current captured LSSD object to the specially chosen circular or elliptical disposal orbit (DO) and after a time returns back to capture a new one. The flight is always to be realized when a value of the Right Ascension of the Ascending Node (RAAN) is approximately the same for the current DO and for an orbit of the following LSSD object.