A low-thrust guidance algorithm suitable for operational use was formulated. A constrained linear feedback control law was obtained using a minimum terminal miss criterion and restricting control corrections to constant changes for specified time periods. Both fixed- and variable-time-of-arrival guidance were considered. The performance of the guidance law was evaluated by applying it to the approach phase of the 1980 rendezvous mission with the comet Encke. (Author)
Guidance Strategies and Analysis for Low Thrust Navigation
1973
27 pages
Report
No indication
English
Navigation and Guidance for Low-Thrust Trajectories, LOTNAV
British Library Conference Proceedings | 2004
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