Optimization of Flights between the Orbits of Artificial Satellites of Two Planets Using a Combination of High and Low Thrusts
Tóm tắt
The problem of optimization of the trajectory of an interplanetary flight of a multistaged spacecraft using jet engines with high and low thrust is considered. The issues concerning the problem of choosing the main design parameters of a multistage spacecraft are touched upon. A mathematical model of start-to-finish optimization of all segments of the interplanetary flight trajectory is proposed. Using this model the specific features of flights to the orbits of satellites of Jupiter and Mars are studied.
Tài liệu tham khảo
Keldysh, M.V., Izbrannye trudy. Raketnaya tekhnika i kosmonavtika (Selected Papers on Rocketry and Astronautics), Moscow: Nauka, 1988.
Il'in, V.A. and Kuzmak, G.E., Optimal'nye perelety kosmicheskikh apparatov (Optimal Transfer Maneuvers of Spacecraft), Moscow: Nauka, 1976.
Fedotov, G.G., Possibilities of Combining High-and Low-Thrust Engines in Flights to Mars, Kosm. Issled., 2001, vol. 39, no. 6, pp. 613–621.
Konstantinov, M.S., Popov, G.A., and Fedotov, G.G., The Use of a Solar Electrojet Propulsion System for Jupiter Satellite Injection, Kosm. Issled., 2002, vol. 40, no. 2, pp. 201–208.
Eneev, T.M., Konstantinov, M.S., Egorov, V.A., et al., Some Methodical Problems of Low-Thrust Trajectory Optimization, Preprint of Keldysh Inst. of Applied Mathematics, Russ. Acad. Sci., Moscow, 1996, no. 110.