Сквозная оптимизация траекторий выведения полезного груза на геостационарную орбиту с применением энергетических возможностей разгонного блока и собственной двигательной установки космического аппарата

Abstract

The article considers an approach for carrying out end-to-end flight trajectory numerical optimization of the multi stage orbital unit based on the maximum principle. The results of the practical application of this approach are presented on the example of a non-coplanar flight of an orbital unit, including the Briz-M upper stage and a spacecraft designed on the basis of the SS/L 1300 satellite platform, from a low reference orbit to a geostationary one. Four families of the problem extremals were obtained, corresponding to the “direct” launch and launch with “throw” of the spacecraft beyond the height of the geostationary orbit (bi-elliptic trajectories) with two and three perigee burns of the upper stage propulsion unit. The effect of the total duration of a non-coplanar flight from a low reference orbit to a geostationary one on the optimal trajectory parameters including the characteristics of the orbit part interfacing the sections where the upper stage propulsion system burns and the spacecraft own propulsion system burns were researched.