Calculations are given for Halo satellite orbit control. Previous truncated analytical descriptions were limited and lead to an acceleration error averaging about .000001, which is the 'cost' of a very tight control to the nominal path. The stationkeeping problem is posed so as to permit a looser, optimal three-axis control.
Investigation of halo satellite orbit control
01.10.1973
Report
Keine Angabe
Englisch
Sun-Earth L1 Region Halo-to-Halo Orbit and Halo-to-Lissajous Orbit Transfers
British Library Conference Proceedings | 2004
|Optimal Approach to Halo Orbit Control
AIAA | 2003
|NTRS | 1972
|Direct lunar halo orbit transfers
Online Contents | 2008
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