A qualitative study of the characteristics of the heliocentric motion of a spacecraft with a low piecewise-constant thrust

Details A qualitative study of the characteristics of the heliocentric motion of a spacecraft with a low piecewise-constant thrust A qualitative study of the characteristics of the heliocentric motion of a spacecraft with a low piecewise-constant thrust

May 1989

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1989kosis..27..357i&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 27, May-June 1989, p. 357-367. In Russian.

Physics

Interplanetary Trajectories, Low Thrust Propulsion, Satellite Orbits, Spacecraft Propulsion, Trajectory Optimization, Transfer Orbits, Electric Propulsion, Jet Propulsion, Numerical Integration

Scientific paper

The transfer characteristics of a spacecraft from satellite orbit to the orbit of a small planet are studied. A low-thrust electrojet propulsion unit is used in the heliocentric-motion segment. Control regimes using constant thrust and constant jet acceleration in two boundary regions separated by passive flight are discussed. The optimal geocentric energy of the spacecraft at the end of acceleration at the earth is determined.

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