Path: Orbit/OrbitManeuver
% Plans delta-v maneuvers to correct triaxial motion.
Generates plots when called with no outputs.
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Form:
[lonD0, lon0, dv, dvP, te, a] = TrxCntrl( eLon, lonTol )
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Inputs
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eLon East longitude of station (deg)
lonTol Longitude tolerance (deg)
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Outputs
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lonD0 Initial longitude rate at lon0
lon0 Starting longitude (will be ±lonTol)
dv Total delta-v requirement per year (m/sec)
dvP Delta-v per maneuver (split into two) (m/sec)
te Time between maneuvers (days)
a Apparent acceleration (rad/day^2)
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References: Michielsen, H.F., E.D. Webb, Stationkeeping of Stationary
Satellites Made Simple, pp. 706-709.
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Orbit: GravityModels/LoadGEM Orbit: GravityModels/NormalizationMatrix Orbit: GravityModels/UnnormalizeGravity Orbit: OrbitManeuver/DVGeoTrx Orbit: OrbitMechanics/AGravity SC: SCMat/GEMT1 Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TextS Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Analysis/PDAL Math: Analysis/SCHarm Math: Linear/DupVect Math: Linear/Factorl
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