Abstract. A method of control over spacecraft during its long-range convergence with orbital object is considered. Angular movement dynamics of the spacecraft with a jet engine rigidly fixed on its body is taken into account. The current control action is calculated with consideration for the influence of noncentral gravitational field, the piecewise continuous jet engine operation, and restrictions on characteristic velocity. Values of equivalent coplanar motion parameters of the spacecraft used for calculations are predicted for the time of passage of the opposite point of the line of apsides. Results of computer simulations are presented to confirm the efficiency of the algorithms developed using the proposed method.

Keywords: spacecraft, long-range guidance, continuous jet engine operation, limited stock of characteristic velocity

References:

1. Avksent'ev A.A.Journal of Instrument Engineering, 2016, no. 2(59), pp. 128–133. (in Russ.)
2. Vlasov S.A., Mamon P.A. Teoriya poleta kosmicheskikh apparatov (Theory of Flight of Spacecrafts), St. Petersburg, 2007, 435 p. (in Russ.)
3. Avksent'ev A.A.Journal of Instrument Engineering,2016, no. 5(59), pp. 364−369. (in Russ.)
4. Branets V.N., Shmyglevskiy I.P. Primenenie kvaternionov v zadachakh orientatsii tverdogo tela (Application of Quaternions in Problems Orientation of a Solid State), Moscow, 1973, 320 р. (in Russ.)
5. Avksent'ev A.A., Efimov V.P., Kotyashov E.V. XXXIV Vserossiyskaya konferentsiya po problemam nauki i tekhnologiy, posvyashchennoy 90-letiyu so dnya rozhdeniya akademika V.P.Makeeva (XXXIV All-Russian Conf. on problems of science and technology, devoted to the 90th anniversary since the birth of academician V.P. Makeev), Аbstracts of Papers, Moscow, 2014, рр. 151−155. (inRuss.)