TOPEX/POSEIDON orbit maintenance maneuver designThe Ocean Topography Experiment (TOPEX/POSEIDON) mission orbit requirements are outlined, as well as its control and maneuver spacing requirements including longitude and time targeting. A ground-track prediction model dealing with geopotential, luni-solar gravity, and atmospheric-drag perturbations is considered. Targeting with all modeled perturbations is discussed, and such ground-track prediction errors as initial semimajor axis, orbit-determination, maneuver-execution, and atmospheric-density modeling errors are assessed. A longitude targeting strategy for two extreme situations is investigated employing all modeled perturbations and prediction errors. It is concluded that atmospheric-drag modeling errors are the prevailing ground-track prediction error source early in the mission during high solar flux, and that low solar-flux levels expected late in the experiment stipulate smaller maneuver magnitudes.
Document ID
19900059738
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bhat, R. S. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Frauenholz, R. B. (JPL Pasadena, CA, United States)
Cannell, Patrick E. (Sterling Federal Systems, Inc. Pasadena, CA, United States)