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
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eq Elements vector [a,P1,P2,Q1,Q2,l]
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Outputs
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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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