Path: Orbit/OrbitCoord
% Convert the standard orbital element set into an Alfriend orbital element set
[a,i,W,w,e,M] -> [a,th,i,q1,q2,W]
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Form:
ela = El2Alfriend( el, nu )
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Inputs
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el (:,6) Standard orbital element set [a,i,W,w,e,M]
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Outputs
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ela (:,6) Alfriend orbital element set [a,th,i,q1,q2,W]
where: th = true latitude
q1 = e*cos(w)
q2 = e*sin(w)
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SC: BasicOrbit/M2Nu Math: Trigonometry/WrapPhase
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