The parameter’s optimization of the meteorological rocket’s correcting engine to reduce the zone of the used blocks’ falling

Abstract

On the example of the meteorological rocket MMR-06, the optimum parameters of the trajectory correction engine to reduce the zone of the used blocks’ falling was selected. It is shown that the optimum mass and optimal maneuvering time are achieved for engines with the medium-thrust. Low-thrust engines, despite the minimum weight, provide a long maneuver time and because of their large number, the total mass increases. The large-thrust engines are very heavy and capable of causing dangerous lateral overloads.