The solution of problems of ballistics on the basis of non-Keplerian intermediate orbits

Details The solution of problems of ballistics on the basis of non-Keplerian intermediate orbits The solution of problems of ballistics on the basis of non-Keplerian intermediate orbits

May 1981

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1981kosis..19..465l&link_type=abstract

Kosmicheskie Issledovaniia, vol. 19, May-June 1981, p. 465-467. In Russian.

Physics

Ballistic Trajectories, Earth Orbits, Low Thrust Propulsion, Spacecraft Motion, Geosynchronous Orbits, Harmonic Analysis, Kepler Laws, Thrust Vector Control

Scientific paper

The intermediate-orbit method is used to study the motion of a spacecraft in low earth orbit that uses a low-thrust propulsion unit to maneuver in a relatively small altitude range; the analysis is limited to the case of the tangential orientation of the low-thrust vector. The chosen intermediate orbit is a trajectory obtained from the solution of the partially averaged problem of six fixed centers, with allowance for the combined effect of zonal harmonics up to the eight harmonic. The formulas that are obtained can be used in various ballistic design calculations, e.g., the correction of quasi-geosynchronous and sun-synchronous orbits.

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