The design procedure of the aerodynamic maneuver for the fall location changing of the carrier rocket stage

Abstract

The procedure of the computation of the program trajectory of the spent stage descending to the impact point and stabilization about the program trajectory considered. The requirements to gas-jet-propelled stabilization system and the operating cycle gasification board system for residual fuel used for the stabilization formulated. The stabilization processes calculations, evaluation of displacement spent stage descending location about the initial trajectory for example first stage separable part of the carrier rocket "Soyuz-2.1.v" at various descending trajectory synthesis schemes.