Calculation of optimum transfers from high-elliptic orbits to geostationary orbits using a stationary plasma engine

Cite item

Full Text



The paper presents solutions of the problem of choosing flights of a spacecraft from high elliptic orbits to a geostationary orbit using a stationary plasma engine. The problem of optimal variation of the semi-major axis, eccentricity and inclination, minimizing the discrepancies in these elements with the use of a locally optimal control law that ensures a joint change of these parameters is also solved. An algorithm for determining the weighting coefficients is given; the algorithm ensures simultaneous fulfillment of boundary conditions for the semi-major axis, eccentricity and inclination is given. The results of numerical simulation based on the results of optimization of flights of a communication satellite from a highly elliptical orbit to the geostationary orbit are presented. Based on the results of numerical simulation, plots of the orbit parameters against time are constructed. The results of the data obtained make it possible to draw a conclusion about the possibility of applying a scheme of joint changes in the orbit parameters.

About the authors

A. A. Kvetkin

Samara National Research University

Author for correspondence.


Russian Federation

A. V. Kolesov

Samara National Research University

ORCID iD: 0000-0002-6972-6649

Postgraduate Student

Russian Federation


  1. Space technology / ed. by H.S. Seifert. New York: Jon Wiley and Sons, 1959. 750 p.
  2. Grodzovskiy G.L., Ivanov Yu.N., Tokarev V.V. Mekhanika kosmicheskogo poleta. Problemy optimizatsii [Space flight mechanics. Optimization problems]. Moscow: Nauka Publ., 1975. 702 p.
  3. Ishkov S.A., Salmin V.V. Optimization of trajectories and parameters of interorbital transport vehicles with low thrust engines. Cosmic Research. 1989. V. 27, Iss. 1. P. 42-53. (In Russ.)
  4. Salmin V.V., Petrukhina K.V., Kvetkin A.A. Calculation of suboptimal high-elliptical orbit to geostationary orbit transfers for spacecraft with low thrusters. Space Engineering and Technology. 2019. No. 4 (27). P. 94-108. (In Russ.). doi: 10.33950/spacetech-2308-7625-2019-4-94-108
  5. Moiseev N.N. Elementy teorii optimal'nykh system [Elements of the theory of optimal systems]. Moscow: Nauka Publ., 1975. 528 p.
  6. Popovich P.R., Skrebushevskiy B.S. Ballisticheskoe proektirovanie kosmicheskikh sistem [Ballistic design of space systems]. Moscow: Mashinostroenie Publ., 1987. 240 p.

Supplementary files

Supplementary Files

Copyright (c) 2023 VESTNIK of Samara University. Aerospace and Mechanical Engineering

Creative Commons License
This work is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License.

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies