Path: FormationFlying/Transformation
% Computes mean orbital elements from reference ECI position and velocity
Since version 7.
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Form:
[elRefMean, dElMean] = ECI2MeanElements(xRefECI, xRelECI, J2);
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Note: it is assumed that all inputs have the same time-tag.
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Inputs
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xRefECI (6,1) reference position & velocity in ECI frame
xRelECI (6,:) relative positions & velocities in ECI frame
J2 (1) size of J2 perturbation
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Outputs
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elRefMean (1,6) mean orbital elements of the reference orbit
dElMean (:,6) mean orbital element differences
NOTE: Both element sets are in Alfriend format [a,theta,i,q1,q2,W]
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References: Terry Alfriend, Texas A&M University
Joe Mueller, Princeton Satellite Systems
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FormationFlying: Transformation/Osc2Mean Orbit: OrbitCoord/El2Alfriend Orbit: OrbitCoord/OrbElemDiff SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag Math: Trigonometry/WrapPhase
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