Using the Properties K-Orthogonality for the Transformation of the Transition Matrix Between States of the Spacecraft

摘要

The article is devoted to theoretical approaches to the use of differential matrix systems for calculating the aerodynamic maneuver of satellites. The algorithm for changing the inclination of the orbital plane and the longitude of the ascending node is presented. The authors analyzed the curvature of the descent trajectory in the atmosphere to change the longitudinal and lateral descent range, taking into account the expansion of the entrance corridor. Parameters of variation of the orbital phase for phasing with another spacecraft are presented in differential matrix form, for example, when transporting a spacecraft to a meeting point with a space station. The differential matrix equation takes into account small changes in all the orbital elements for the transition to a new given orbit or for the correction of the original orbit. A priori, several of the required combinations of altitude and flight speed were selected for optimal control, the corresponding values of the parameters of the space environment in front of the satellite are determined. The parameters of the evolution of the orbits are analytically presented, which make it possible to find regions of stability on the plane of the parameters of the major semiaxis and inclination for different quantities. In this paper, the authors show analytically that the use of trajectories of a multipulse transition to high circular orbits of satellites with large inclinations increases the final mass of the satellite, and also allows the satellite to be brought to final orbits with given distance values at the point of application of the intermediate pulse.