An approximate determination of the characteristic velocity losses and the positioning of the end of the launching phase of the first stages of launch vehicles

Abstract

At the initial stage of the creation of new types of launch vehicles, the so-called design ballistic calculations are carried out. The main purpose of these calculations - is to make the choice of optimal combinations of the main design parameters. Currently, the relevance of the project ballistics tasks has grown significantly in the connection with the research of the new generation of launch vehicles, which are related to both the problems of deep space exploration and the creation of low-orbit satellite constellations of small spacecraft. In the process of the design methods developing, models of motion should not be inferior to the uncertainties of the source data. So, the algorithms of these methods should reflect the correlation of design parameters with the flight characteristics of the launch vehicle. Above principles were put as the basis of the proposed correlations linking the values of the trajectory variables at the end of the launching phase of the first stages of launch vehicles with the main design parameters. The calculated dependences are based on the results of the analysis of a large number of trajectories, which are corresponding to variations of different studied factors. The calculations were carried out by the method of numerical integration of differential equations of motion in a wide range of variation of the source data. The analysis done gave us the possibility to identify some general patterns of controlled motion of a material point and to obtain the structure of calculation formulas in an analytical form.