CEq2C:

Path: Orbit/OrbitCoord

% Transformation matrix from equinoctial to cartesian coordinates.
   The equinoctial elements are
     a   - semimajor axis
     P1  - esin(W+w)
     P2  - ecos(W+w)
     Q1  - tan(i/2)sinW
     Q2  - tan(i/2)cosW
     l   - W + w + M
   
   Since version 1.
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   Form:
   c = CEq2C( eq )
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   ------
   Inputs
   ------
   eq                    Elements vector [a,P1,P2,Q1,Q2,l]

   -------
   Outputs
   -------
   c               (3,3) Transformation matrix

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   References: Battin, R.H., An Introduction to the Methods and Mathematics
               of Astrodynamics, AIAA, New York, 1987, p. 494.
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