The selection of the operational orbit of Cluster and its relation with the new magnetic field models are reviewed and the optimization of a multiple maneuver control stategy to achieve the required three dimensional spacecraft configuration is analyzed. The optical solution is based on the transfer of each spacecraft from the departure orbit to the final orbit by performing two maneuvers per spacecraft. A recursive quadratic optimization method was used for the solution of the constrained nonlinear optimization.
3-D Configuration of the Cluster Mission
1991
9 pages
Report
Keine Angabe
Englisch
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