The modeling of unused propellant residues processes from a tank of rocket stage

摘要

In this article the physical modeling of processes related to the functioning of the active deorbiting systems ofthe rocket stage separating parts with liquid propulsion engine (LPE) after completing their mission from orbitsand deorbit trajectories is described. The technology of energy resources evaparation from liquid rocketpropellant components in the tanks based on the supply of hot gases and their subsequent utilization. Theorganization of the modeling process on the basis process separation into three stages, the use of model products(obtaining of heat carriers, evaporation, utilization) is proposed.