Physics
Scientific paper
Mar 1994
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994cosre..31..457l&link_type=abstract
Cosmic Res., Vol. 31, No. 5, p. 457 - 470
Physics
Space Missions: Control Systems
Scientific paper
Special trajectories for insertion into a halo orbit near the L2 point of the Earth-Sun system through the use of a close fly-by of the Moon are analyzed. The suitability of such trajectories for the implementation of the Relict-2 project depends strongly on the requirements imposed on the control system which implements the trajectory. In the analysis of this problem in the present paper, allowance is made for errors in the insertion of the spacecraft in the trajectory near the Earth, measurement errors, and errors in the execution of the corrections. A primary measure of the quality of the control is the expenditure of characteristic velocity required to implement the control during the insertion of the spacecraft in the halo orbit. An approximately optimum control scheme is proposed. Control characteristics are calculated for flight trajectories with launches in October and November of 1994.
Lidov M. L.
Lyakhova V. A.
Teslenko N. M.
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