Математическая модель продольного движения космического аппарата на различных участках его полета

Abstract

The article studies the spacecraft stability at small and large angles of attack under the influence of disturbances arising from aerodynamic drag, wind speed and linear thrust eccentricity caused by deviations (misalignment) of the installation angle of the booster engine of the spacecraft. Possible use of spacecraft with opening braking surfaces when moving in the atmosphere is described. A mathematical model of disturbed motion of the spacecraft at various stages of its flight to the destination planet has been developed. The resulting mathematical model was used in the studies of the launch of a spacecraft from an inclined, vertical launch facilities and descent for landing on the surface without taking into account the operation of braking engines. The parameters of the trajectories of a spacecraft with a booster in the pitch plane are calculated depending on the flight altitude and the inclination of the launch pad.