A method of optimizing the apogee burns to maximize the worst-case beginning of life mass for a geosynchronous satellite is presented. Optimizing the worst-case rather than the nominal transfer strategy results in a reduction in the propellant mass required for the maneuver. A computer program written to implement the algorithm is described and the results of two case studies are presented. One of these case studies employs a single apogee engine burn with the thrust vector following a slew about a single spacecraft axis. The second employs a multiburn apogee engine maneuver with an inertially fixed thrust vector. Both cases show significant reductions in the propellant required for the 99th percentile case.
Optimization of Worst Case Perigee Raising Strategy
1986
7 pages
Report
Keine Angabe
Englisch
Perigee Attitude Maneuvers of Geostationary Satellites During Electric Orbit Raising
Online Contents | 2017
|Perigee Attitude Maneuvers of Geostationary Satellites During Electric Orbit Raising
Online Contents | 2017
|Perigee Attitude Maneuvers of Geostationary Satellites During Electric Orbit Raising
Online Contents | 2017
|Perigee attitude maneuvers of geostationary satellites during electric orbit raising
BASE | 2017
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