Приближенная методика проектировочного баллистического расчета первых ступеней ракет-носителей

Abstract

The initial stages of development of new types of launch vehicles involve performing the so-called design ballistic calculations. Currently, the relevance of design ballistics tasks is noticeably increasing in connection with the problems of deep space exploration and the creation of a new generation of space rocket systems, requiring significant financial investment. When developing design methods, motion models should not be inferior in accuracy to the uncertainties of the source data, and the algorithm of the technique should reflect the relationship of design parameters with the flight characteristics of the rocket. These principles formed the basis of the proposed methods for ballistic calculations of the active section of the trajectory of the first stages of heavy and super heavy launch vehicles. The technique is based on the results of the analysis of numerous trajectories corresponding to variations of various studied factors. The trajectory calculations were carried out using the method of numerical integration of differential equations of motion in a wide range of variation of design ballistic parameters and boundary conditions. The analysis made it possible to identify some general patterns of the controlled motion and to obtain the structure of the calculated dependencies in an analytical form.